초록 ▼

A rocket launch system includes a tubular rocket launcher carriage with electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage is co

A rocket launch system includes a tubular rocket launcher carriage with electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage is conveyed to a docking station supported into the stratosphere by a pair of secondary cables suspended under an attachment frame for tensioning balloons. The carriage is engaged by a carriage end gripper guided by two sets of secondary cables and two sets of tertiary cables and lifted by a lower hoist guided by the secondary cables to a lift ring assembly. This lower hoist is supported by an upper hoist suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring guided by two secondary cables, is elevated further, rotated in azimuth and elevation, and rocket ejection occurs from a launch tube during freefall of the carriage, with engine ignition occurring at a safe distance. The carriages have traction drives which grip cables from which they derive power and rotate to drive the carriage from the low altitude to the high altitude. The traction drives rotate in the opposite direction as the carriage descends the cable following the launch of a rocket under gravitational force. The kinetic energy of the traction drive is converted to electrical energy which is fed back to the cables during descent of the carriage.

대표청구항 ▼

1. A rocket launch system comprising: at least one electric power line for carrying electrical power from a source of electrical power from a remote electric power system on the earth, the electric power being withdrawable along said at least one electric power line, said at least one power line hav

1. A rocket launch system comprising: at least one electric power line for carrying electrical power from a source of electrical power from a remote electric power system on the earth, the electric power being withdrawable along said at least one electric power line, said at least one power line having a low end portion for being positioned at a low altitude and a high end portion for extending into high altitudes;at least one rocket-transporting device line for transporting a rocket-transporting device between a low altitude and a high altitude, said at least one rocket-transporting device line having a low end portion for being positioned at a low altitude and a high end portion for extending into higher altitudes; andlighter-than-air balloons connected to said at least one power line and said at least one rocket-transporting device line for holding said at least one electric power line and said at least one rocket-transporting device line upwards to a high altitude. 2. A rocket launch system according to claim 1 wherein said at least one electric power line comprises three electric power lines and said at least one rocket-transporting device line comprises three rocket-transporting device lines, and said respective three electric power lines and said respective three rocket-transporting device lines are integrally combined into three power and transporting primary cables. 3. A rocket launch system according to claim 2 wherein said three power and transporting primary cables carry three-phase electrical power. 4. A rocket launch system according to claim 3 wherein said lighter-than-air balloons are operatively attached to said three power and transporting primary cables intermittently along the length of said three power and transporting primary cables to support cumulatively said three power and transporting primary cables, and any other structure carried by said three power and transporting primary cables which is utilized in the launch of a rocket. 5. A rocket launch system according to claim 4 and further including: at least one large harness for being operatively attached to said lighter-than-air balloons; said rocket launch system further including;basal connectors extending from said respective large harnesses to said respective lighter-than-air balloons to connect said lighter-than-air balloons to said respective large harnesses, said respective basal connections being tangent to said respective lighter-than-air balloons. 6. A rocket launch system according to claim 3 and further including: respective sets of spacer assemblies located intermittently along said three power and transporting primary cables, each of said set of spacer assemblies having cable-engaging structure for engaging each of said three power and transporting primary cables of said three power and transporting primary cables to maintain a spaced separation between said three power and transporting primary cables, and wherein said lighter-than-air balloons are respectively, operatively connected to at least one of said spacer assemblies. 7. A rocket launch system according to claim 3 for receiving a rocket-transporting device having a particular structure for holding a rocket, said rocket launch system further comprising: a docking station operatively connected to said three power and transporting primary cables at a terminal position along the length of said three power and transporting primary cables, said docking station being structured to receive a rocket-transporting device as part of a preparation for a launch of a rocket being transported in a rocket-transporting device. 8. A rocket launch system according to claim 7 and further comprising power and guiding secondary cables operatively attached to said docking station and being extendable to a higher altitude than the altitude of said docking station, said rocket launch system further comprising lighter-than-air balloons operatively connected to said power and guiding secondary cables for holding and tensioning said power and guiding secondary cables aloft above said power and transporting primary cables. 9. A rocket launch system according to claim 8 and further comprising: a lift ring assembly in operative engagement with said power and guiding secondary cables for deriving electrical power from and being guided by said power and guiding secondary cables, said lift ring assembly being positionable above said docking station and being both operatively engageable with a rocket-transporting device disposed in said docking station for lifting the rocket-transporting device out of said docking station, and comprising a rocket-transporting device pivoting assembly for being tilted to a desired rocket launch angle. 10. A rocket launch system according to claim 9 wherein said rocket-transporting device pivoting assembly is a tubular ring configured to surround and operatively engage a rocket-transporting device, and being tiltable to orient a rocket-transporting device disposed in said rocket-transporting device pivoting assembly and any rocket disposed in the rocket-transporting device to a desired launch angle. 11. A rocket launch system according to claim 10 and further comprising: a lower hoist assembly located above said lift ring assembly when said rocket launch system is in operation;a set of tertiary cables extending from said lower hoist assembly for being operationally connectable to and supporting said lift ring assembly; anda rocket-transporting device end gripper disposable between said lower hoist assembly and said lift ring assembly and being operatively attached to said lower hoist assembly, said end gripper being releasably and lockably engageable with a rocket-transporting device in said lift ring assembly, said lower hoist assembly lifting said end gripper for lifting a rocket-transporting device into engagement with said rocket-transporting device pivoting assembly prior to the launching of a rocket from a rocket-transporting device disposed in said lift ring assembly. 12. A rocket launch system according to claim 7 and further incorporating: a launcher based on the ground for launching respective rocket-transporting devices, said launcher including: a turntable mechanism for receiving respective rocket-transporting devices for delivering to said docking station, said turntable mechanism comprising: a turntable base; anda turret assembly mounted on said turntable base, the low end portion of said power and transporting primary cables being connected to said turret assembly, and moving structure for transporting respective rocket-transporting devices from and to said turret assembly along said primary cables. 13. A rocket launch system according to claim 12 wherein said turret assembly comprises: a rotatable turntable rotatable with respect to said turntable base, said rotatable turntable comprising: a rotatable turntable orifice for receiving respective rocket-transporting devices;a lower guide tube mounted on said rotatable turntable, said lower guide tube comprising: a lower guide tube orifice alignable with and having a size corresponding to said rotatable turntable orifice, said lower guide tube receiving respective rocket-transporting devices, said lower guide tube comprising: lower guide tube carriage guides for locating the respective rocket-transporting devices in said lower guide tube orifice;a secondary guide structure comprising: an integral tube having an integral tube orifice and internal carriage guides alignable with said lower guide tube carriage guides; andprimary cable connecting structure for connecting said primary cables to said secondary guide structure; anda rotational drive system assembly for rotating said lower guide tube with respect to said secondary guide structure to align said lower guide tube orifice and said integral tube orifice, and to align said lower guide tube guide structure and said secondary guide structure;said rotatable turntable rotating said lower guide tube and said secondary guide structure in a desired direction for the movement of a respective rocket-transporting device. 14. A rocket launch system according to claim 13 wherein the respective rocket-transporting devices have respective longitudinal axes and a set of external recesses extending along the length of the respective rocket-transporting devices, and said lower guide tube carriage guides and said secondary guide structure are internal carriage guides for being received by the set of external recesses in the respective rocket-transporting devices. 15. A rocket launch system according to claim 13 wherein one of said turntable and said turntable base comprises: a perimetrical portion and a flat surface;a vertical, annular flange extending from said perimetrical portion; anda horizontal, annular flange extending from said vertical, annular flange and having an upper, lower and radial surfaces of said vertical, annular flange rotatable about respective radial axes; wherein wheels are mounted for engagement by said turntable and said turntable base; and the other of said turntable and said turntable base comprises: a vertical, annular, tubular part concentric with the other of said turntable and said turntable base; anda horizontal, annular flange extending from said vertical, annular tubular part, said horizontal, annular flange and said other of said turntable and turntable base having surfaces for engagement by said respective wheels for reducing the friction between said turntable and said turntable base upon the relative rotation thereof. 16. A rocket launch system according to claim 13 wherein each of said turntable and said turntable base has a perimetrical end portion for receiving a rolling bearing, and one of said turntable and said turntable base further comprises a vertical, annular part extending from said perimetrical end portion and a horizontal, annular flange extending from said vertical part and having annular bearing surfaces for receiving rolling bearings; and the other of said turntable and said turntable base comprises a vertical, annular part concentric with the other of said turntable and said turntable base and a horizontal, annular flange extending from said vertical, annular part, and having annular bearing surfaces; androlling bearings disposed between said horizontal, annular flange and both of said annular, horizontal flanges and said horizontal, annular flange in said annular bearing surfaces;said rolling bearings reducing the friction between said turntable and said turntable base upon the relative rotation therebetween and resisting axial compressive and tensile forces as well as forces perpendicular to the axis of rotation and combinations thereof. 17. A rocket launch system according to claim 13 wherein said turret assembly further comprises: a yoke including: a pair of spaced apart arms pivotally mounted on said turntable; said lower guide tube being pivotally mounted between said pair of spaced apart arms, said lower guide tube and said secondary guide structure being pivotally mounted between said pair of spaced apart arms, the axes of rotation of said turntable and said lower guide tube intersecting orthogonally. 18. A rocket launch system according to claim 17 wherein said integral tube is located at a fixed distance from the common pivot of said integral tube and lower guide tube, said secondary guide tube structure being counterbalanced about the horizontal pivot of said secondary guide structure, said secondary guide structure being alignable with the upper end of said lower guide tube to render said integral tube and said lower guide tube coaxial, and said secondary guiding structure and said lower guide tube guiding structure in alignment. 19. A rocket launch system according to claim 13 wherein the respective rocket-transporting devices comprise: electrically powered traction drives for engaging said respective primary cables for transporting the respective rocket-transporting devices;wherein said lower guide tube guiding structure and said secondary guide structure are electrically energized to transmit electrical power to said traction drives. 20. A rocket launch system according to claim 13 and further including: an elevating assembly for moving a rocket-transporting device into said turret assembly, said elevating assembly being engageable with the respective rocket-transporting devices for moving the respective rocket-transporting devices into said turret assembly. 21. A rocket launch system according to claim 20 wherein said elevating assembly comprises: a hydraulic cylinder;a hydraulic piston operatively disposed inside said hydraulic cylinder;a hydraulic piston rod connected to said hydraulic piston and being axially movable with respect to said hydraulic cylinder;an upper swiveling assembly operatively mounted on said hydraulic piston for receiving the respective rocket-transporting devices and aligning the rocket-transporting devices with said rotatable turntable orifice; anda rotary drive for rotating said upper swiveling assembly. 22. A rocket launch system according to claim 21 wherein said upper swiveling assembly comprises: a rotatable bed for receiving the respective rocket-transporting devices and rotating the rocket-transporting devices to align the respective rocket-transporting devices with said rotatable turntable orifice. 23. A rocket launch system according to claim 22 wherein said upper swiveling assembly further comprises a table portion mounted on said rotatable bed for receiving for further conveyance respective rocket-transporting devices. 24. A rocket launch system according to claim 23 wherein said elevating assembly further comprises a non-rotating bed fixed to said piston rod; said rotatable bed being mounted on said non-rotating bed. 25. A rocket launch system according to claim 24 wherein said upper swiveling assembly receives respective rocket-transporting devices from lateral conveying devices having a set of lateral conveying device wheels, and said table portion is associated with tracks located on the ground and aligned with the set of lateral conveying device wheels for enabling the lateral conveying devices to be received on said table portion of said elevating assembly. 26. A rocket launch system according to claim 25 wherein the respective lateral conveying devices and said table portion include attaching structure for releasably attaching the respective lateral conveying devices to said table portion, the lateral conveying devices, said table portion and attaching structure being located on the ground. 27. A rocket launch system according to claim 26 wherein said attaching structure comprises: a selected one of the group consisting of alignment pins and fractional rotation twist pins extending from the upper surface of said table portion for being received in corresponding sockets in the respective lateral conveying devices; andalignment pin sockets and fractional rotation pin sockets in said table portion for receiving corresponding tapered alignment pins and corresponding fractional rotation twist pins extending from the respective lateral conveying devices. 28. A rocket launch system according to claim 25 and further including: a pathway located on the ground and having a set of tracks engageable by the set of wheels of the lateral conveying device for conveying respective rocket-transporting devices to said table portion for transfer to said elevating system. 29. A rocket launch system according to claim 28 and further comprising: a rocket storage structure located on the ground loading for rockets to be launched from said rocket launch system, loaded in respective rocket-transporting devices. 30. A rocket launch system according to claim 29 wherein said rocket storage structure comprising: storage racks separated by blast-resistant partition walls. 31. A rocket launch system according to claim 30 and further including: a rocket loading system located on the ground for removing respective rocket-transporting devices from said rocket storage structure; andassembly bays; said rocket loading system moving respective rocket-transporting devices to respective assembly bays. 32. A rocket launch system according to claim 31 wherein said rocket loading system comprises: a transverse loader movable on the ground with respect to the respective assembly bays;a set of tracks located on the ground upon which said transverse loader travels; anda guide assembly for guiding said transverse loader and components of said transverse loader. 33. A rocket launch system according to claim 32 wherein said transverse loader moves longitudinally with respect to the assembly bays, and said transverse loader comprises: an elevator assembly on the ground movable transversely on said transverse loader and vertically for receiving respective rocket-transporting devices at a relatively high elevation and lowering the respective rocket-transporting devices into the respective assembly bays. 34. A rocket launch system according to claim 33 wherein said guide assembly comprises: wheeled trucks movable on the ground on said set of tracks and carrying said transverse loader along said set of tracks; andrails located on the ground and extending across said transverse loader, said elevator assembly being movable along said rails. 35. A rocket launch system according to claim 34 and further including an elevator assembly wheeled truck for carrying said elevator assembly along said rails. 36. A rocket launch system according to claim 35 wherein said elevator assembly includes: a guide support apparatus mounted on said elevator assembly wheeled truck and extending in a vertical direction; andan elevator operatively coupled to said guide support apparatus, said elevator having electro-mechanical structures for moving said elevator on said guide support apparatus;said elevator assembly lifting rockets and carriages from said storage racks and lowering the respective rockets and carriages into said respective assembly bays; and said transverse loader moving respective rockets and carriages between said racks and said assembly bays. 37. A rocket launch system according to claim 36 wherein the respective rockets include elevator assembly attachment receptacles; and wherein said elevator assembly further comprises: a grasping assembly for operatively engaging the elevator assembly attachment receptacles for respective rockets disposed in said respective assembly bays for enabling said elevator assembly to lift the respective rockets from said respective assembly bays. 38. A rocket launch system according to claim 37 wherein said elevator assembly further comprises: depending legs attached to said elevator, said legs being movable with said elevator at different locations around the respective rockets for operative engagement with the respective receptacles of the respective rockets;guides for guiding said depending legs into the respective receptacles; andleg attachment apparatus for releasably holding said respective legs to the respective receptacles. 39. A rocket launch system according to claim 38 wherein the respective receptacles include: fractional rotation twist-lock pin sockets; and said leg attachment apparatus comprises: fractional rotation twist-lock pins for securely and releasably attaching the respective rockets to said elevator assembly. 40. A rocket launch system according to claim 36 wherein said transverse loader further comprises stabilizing arm assemblies mounted on said elevator assembly for engaging and stabilizing the respective rockets disposed in said elevator assembly. 41. A rocket launch system according to claim 40 wherein said stabilizing arm assemblies comprise arms with structure for engaging the respective rockets, and actuators attached to said respective arms for operating said respective arms to engage and release the respective rockets. 42. A rocket launch system according to claim 41 and further comprising: a main pathway located on the ground and extending in operative proximity to said rocket storage structure and said assembly bays; andrails located on the ground disposed in said main pathway upon which lateral conveying devices can move for transporting rocket-transporting devices. 43. A rocket launch system according to claim 42 and further including: bay pathways located on the ground and leading from said respective assembly bays to said main pathway; andrails located on the ground in said bay pathways for operative intersection with said rails in said main pathway. 44. A rocket launch system according to claim 43, wherein said assembly bays are located below ground surface, and have the shape of an inverted frustum and made of a concrete material for limiting the effects of damage due to the detonation of rocket propellant by deflecting the blast upwardly and laterally. 45. A rocket launch assembly according to claim 44 and further including slidable blast covers slidable over said respective assembly bays for protecting against damage in the event of an accidental blast in said bay. 46. A rocket launch system according to claim 31 and further comprising lateral conveying devices for moving rocket-transporting devices between said rocket storage structure, said assembly bays and said table portion, said lateral conveying device comprising wheels for operatively engaging said set of tracks. 47. A rocket launch system according to claim 46 wherein the respective rocket-transporting devices have a base end proximal a rocket contained in the respective rocket-transporting devices, and wherein said base end is stably received in said lateral conveying device to hold the respective rocket-transporting devices in an upright position, and said rocket-transporting device is releasably locked in said receiving structure. 48. A rocket launch system according to claim 47 wherein said lateral conveying device is located on the ground, and comprises a locking mechanism, and said locking mechanism comprises fractional rotation twist-lock pins for locking a rocket-transporting device in said receiving structure. 49. A rocket launch system according to claim 47 wherein said lateral conveying device comprises: independently steerable wheels; anda steering mechanism for moving said lateral conveying device on said set of tracks. 50. A rocket launch system according to claim 49 and further including loading apparatus located on the ground for loading rocket-transporting devices onto said lateral conveying device, said loading apparatus comprising: a loading bed rotatable about an axis of rotation for receiving a rocket-transporting device; anda rotator operatively connected to said loading bed for moving said loading bed from a holding position for holding a rocket-transporting device on said loading bed to a release position for enabling the rocket-transporting device to be displaced to a respective one of said receiving structures of said lateral conveying devices in an upright position. 51. A rocket launch according to claim 20 wherein said elevating assembly comprises an electro-mechanical elevating assembly. 52. A rocket launch system according to claim 3 wherein each of said three power and transporting primary cables is a body of cable, said body of cable comprising: strands of wire having looped-out portions extending from said body of cable for securing items to said primary cable, each looped-out portion exiting from and returning to said body of said primary cable. 53. A rocket launch system according to claim 52 and further including: an adaptive connector having aligned wall orifices therein; anda connector for extending through a pair of said aligned wall orifices and one of said looped-out portions for connecting said adaptive connector to each of said three power and transporting primary cables. 54. A rocket launch system according to claim 52 and further including: a carriage for transporting a rocket along said three power and transporting primary cables, said carriage including: traction wheels for engaging said respective primary cables and rotating on said respective primary cables without contacting said looped-out portions to propel said carriage along said primary cables. 55. A rocket launch system according to claim 3 and further comprising a main rocket for being controllably launched by said rocket launch system and a core rocket being carried with and releasable from said main rocket, and a windshield operatively connected to said core rocket for protection against high velocity air. 56. A rocket launch system according to claim 3 and further including: at least one spacer assembly for maintaining a spaced separation between said three power and transporting primary cables, said primary cables having an adaptive connector comprising a pair of spaced, parallel flanges extending generally radially from said primary cables at the same level for each of said three primary cables, said spacer assembly comprising: three generally straight arms forming a generally equilateral triangle, said three generally straight arms being generally coplanar and forming an intersection on opposite ends of said respective generally straight arms;an orthogonal flange disposed at said respective intersections and being generally perpendicular to the plane of said three generally straight arms and disposed between said respective pairs of spaced, parallel flanges extending from said respective primary cables; andattaching structure for connecting said respective orthogonal flanges and said respective pairs of spaced, parallel flanges extending from said primary cables. 57. A rocket launch system according to claim 2 and further comprising a docking station connected to said three power and transporting primary cables at a terminal positioned along the length of said three power and transporting primary cables, said docking station being structured to receive a telescope conveying carriage, and a telescope-holding system operatively connected to said docking station. 58. A rocket launch system according to claim 57 wherein said telescope-holding system includes a rotatable turntable. 59. A rocket launch system according to claim 58 wherein said telescope-holding system including a mount constructed to hold a telescope. 60. A rocket launch system according to claim 59 wherein said telescope-holding system further comprises a telescope-holding structure for holding a telescope on said rotatable turntable. 61. A rocket launch system according to claim 60 and further including a telescope tilting structure. 62. A rocket launch system according to claim 61 and further including an elevator tube for providing a transport path for a telescope conveying-carriage for conveying a telescope to said mount, said mount being constructed to hold said telescope conveying carriage for placing the telescope in operative position(s). 63. A rocket launch system according to claim 62 wherein said elevator tube further includes: electricity-carrying cables or wheels for powering the telescope conveying carriage in said elevator tube. 64. A rocket launch system according to claim 63 wherein said docking station has a lower part and an upper part rotatable with respect to said lower part, and a rotational drive system for offsetting the relative rotation of said lower part and said upper part. 65. A rocket launch system according to claim 64 and further including: a ring bearing located between said lower part and said upper part for reducing the friction between said lower part and said upper part; andwherein said rotational drive system comprises reaction thrusters for providing said offsetting. 66. A rocket launch system according to claim 65 and further comprising: electrical power secondary cables extending upwardly from said docking station when said docking station has been elevated under the influence of said lighter-than-air balloons; anda lift ring drivable upwardly and downwardly on said secondary cables, said lift ring including:traction drivers and carriage-holding structures for holding a telescope-conveying carriage, said carriage-holding structure being pivotal and rotatable with respect to said secondary cables to orient a telescope-conveying carriage held in said carriage-holding structure for entry into said elevator tube. 67. A rocket launch system according to claim 66 and further comprising: an upper docking station connected to said secondary cables, said upper docking station comprising: an upper part,a lower part, wherein said upper part and said lower part are rotatable in opposite directions about an imaginary vertical axis,a ring bearing for reducing the friction between said upper part and said lower part, anda rotational drive system for rotating said upper part and said lower part. 68. A rocket launch system according to claim 2 wherein said cables have a steel exterior. 69. A rocket launch system according to claim 2 wherein said cables comprise: a steel exterior; andan interior composed of copper-coated steel strands. 70. A rocket launch system according to claim 1 and further comprising at least one rocket-transporting device for transporting a rocket along said at least one rocket-transporting device line, each of said at least one rocket-transporting device including: traction drives for driving said respective rocket-transporting devices along said at least one rocket-transporting device line; anda motor-generator for deriving electrical power from said at least one electric power line when said traction drives require energy to cause said at least one rocket-transporting device to travel upwards on said at least one rocket-transporting device line, and for supplying electrical power to said at least one electric power line when said traction drives generate electric power when said traction drives retard the downward motion of said at least one rocket-transporting device as said at least one rocket-transporting device travels downwards on said at least one rocket-transporting device line under the influence of gravity. 71. A rocket launch system according to claim 70 wherein said at least one electric power line and said at least one rocket-transporting device line are integrally combined into at least one power and transporting primary cable, said at least one rocket-transporting device being driven along said at least one primary cable by said traction drives upon energization by said motor generator. 72. A rocket launch system according to claim 71 wherein each of said at least one rocket-transporting device comprises: a carriage having an interior compartment configured to contain a rocket, the rocket being ejectable from said interior compartment during launch. 73. A rocket launch system according to claim 72 wherein said at least one power and transporting primary cable comprises three power and transporting primary cables to carry three-phase power, wherein each of said three power and transporting primary cables carry one of the phases, and said motor generator is powered by three-phase electrical power. 74. A rocket launch system according to claim 73 wherein said respective traction drives comprise: a set of traction drive wheels associated with each said carriage for engaging said three power and transporting primary cables for transporting each said carriage along said three power and transporting primary cables. 75. A rocket launch system according to claim 74 and further comprising: a docking station operatively connected to said three power and transporting primary cables at a terminal position along the length of said three power and transporting primary cables, said docking station being structured to receive each said carriage as part of a preparation for a launch of a rocket being transported in each said carriage. 76. A rocket launch system according to claim 75 and further comprising: power and guiding secondary cables operatively attached to said docking station and extendable to a higher altitude than the altitude of said docking station; andtensioning lighter-than-air balloons operatively connected to said power and guiding secondary cables for holding said power and guiding secondary cables aloft above said three power and transporting primary cables. 77. A rocket launch system according to claim 76 and further comprising: a lift ring assembly in operative engagement with said power and guiding secondary cables for deriving electrical power and being guided by said power and guiding secondary cables, said lift ring assembly being positioned above said docking station and being operatively engageable with each said carriage disposed in said docking station for lifting each said carriage out of said docking station, said lift ring assembly comprising: a tubular lift ring; anda carriage pivoting assembly for tilting said tubular lift ring to a desirable rocket launch angle. 78. A rocket launch system according to claim 77 wherein said tubular lift ring is a hollow apparatus configured to surround and operatively engage each said carriage, and being tiltable to orient each said carriage and the rocket in each said carriage in a desired launch direction. 79. A rocket launch system according to claim 78 and further comprising a lower hoist carrier from which are extendable a set of tertiary cables for being operationally connectable to and supporting said lift ring assembly; and a carriage end gripper disposable between said lower hoist carrier and said lift ring assembly and being operatively attached to said lower hoist carrier, said carriage end gripper being releasably lockably engageable with one said carriage in said lift ring assembly, said lower hoist carrier lifting said carriage end gripper for lifting each said carriage into proper engagement with each said carriage pivoting assembly prior to the launching of a rocket from said carriage disposed in said lift ring assembly. 80. A rocket launch assembly according to claim 79 wherein said carriage pivoting assembly is operatively connected to said secondary cables, said carriage pivoting assembly traveling downward along said secondary cables in a freefall condition, said secondary cables being of sufficient length to enable a rocket in each said carriage to be boosted free and clear of each said carriage by a short duration booster rocket during the freefall condition. 81. A rocket launch system according to claim 79 wherein said carriage pivoting assembly is operatively connected to said tertiary cables, said lower hoist assembly releasing said carriage end gripper upon initiation of the launch of a rocket, and a rocket being launched from each said carriage in said carriage pivoting assembly, rendering said tubular lift ring and said carriage pivoting assembly in a freefall condition, said secondary cables being of sufficient length to safely allow a time period of sufficient length at the local acceleration due to gravity of said lower hoist assembly with a rocket-transporting device having a rocket disposed therein to be decelerated to rest in the event of a misfire while said lower hoist assembly is in the freefall condition. 82. A rocket launch system according to claim 78 wherein each said carriage has opposite ends, and wherein each said carriage further comprises: thrusters at each of said ends for reducing oscillation of each said carriage in said lift ring assembly. 83. A rocket launch system according to claim 82 wherein said thrusters are reversible variable pitch thrusters. 84. A rocket launch system according to claim 83 wherein said reversible variable pitch thrusters each comprise: a hub motor; anda set of blades extending from said hub motor for being rotated in selectively opposite directions by said hub motor. 85. A rocket launch system according to claim 84 and further comprising: pivotable thruster mountings rotatably mounted on the respective ends of each said carriage, said thruster mountings holding said hub motor and said blades and being rotatable from a rest position within each said carriage to an active position parallel to the longitudinal axis of each said carriage. 86. A rocket launch system according to claim 85 wherein said thruster mountings are rotatable about opposite ends of each said carriage between said rest position, said active position, and an obtuse position away from the openings of said respective ends to avoid the impingement of exhaust gases of rockets being launched from each said carriage and to enable loading a rocket into each said carriage. 87. A rocket launch system according to claim 77 and further including a tensioning balloons attachment frame operatively connected to said secondary cables, said primary tensioning lighter-than-air balloons being attached to said tensioning balloons attachment frame for imparting sufficient tension to support cumulatively each said carriage, secondary cables and any other structure carried by said three power and transporting primary cables which are utilized in the launch of a rocket. 88. A rocket launch system according to claim 87 wherein said rocket launch system further comprises: a lower hoist assembly operatively attached to said tensioning balloons attachment frame located above said lift ring assembly when said rocket launch system is in operation;a set of tertiary cables extending from said lower hoist assembly for being operatively connectable to and supporting said lift ring assembly; anda carriage end gripper disposed between said lower hoist assembly and said lift ring assembly and being operatively connected to said lower hoist assembly, said carriage end gripper being releasably and lockably engageable with one said carriage in said lift ring assembly, said lower hoist lifting said carriage end gripper for lifting each said carriage into engagement with said carriage pivoting assembly prior to the launching of a rocket from each said carriage disposed in said lift ring assembly; andan upper hoist assembly attached to said tensioning balloon attachment frame and being operatively connected to said lower hoist assembly and to said power and guiding secondary cables, said upper hoist assembly drawing power from said power and guiding secondary cables for selectively raising and lowering said lower hoist carrier assembly to lift or assist in lifting each said carriage into and out of engagement with said lift ring assembly. 89. A rocket launch system according to claim 88: wherein said docking station has connected thereto an upper ring part having an axis of rotation, a lower ring part coaxial with said upper ring part, said upper ring part and said lower ring part being connected together by a lower ring bearing, said upper ring part and said lower ring part being rotatable relative to each other, and a lower rotational drive system for driving said upper ring part and said lower ring part in counter rotation about said lower ring bearing; andwherein said tensioning balloons attachment frame has connected thereto an upper ring having an axis of rotation, a lower ring coaxial with said upper ring, said upper ring and said lower ring being connected together by an upper rotary ring bearing, and an upper rotational drive system for driving said upper ring and said lower ring in counter rotation about said upper rotary ring bearing; said upper rotational drive system and said lower drive system being operatively connected to each other to coordinate the rotation of said upper ring part and said lower ring to rotate as a unit to keep said associated cables from twisting around each other, said lower ring part and said upper ring rotating as a unit to counter wind-induced rotation and rotation resulting from the rotation of said carriage when the lower end of said one of said respective carriages is held in said upper ring part and said respective carriage is being rotated for launch. 90. A rocket launch system according to claim 89 wherein said upper rotational drive system includes: upper force thrusters for rotating or assisting in the rotation of said upper rotational drive structure; andwherein said lower rotational drive system includes lower force thrusters for rotating or assisting the rotation of said lower rotational drive system. 91. A rocket launch system according to claim 89 wherein: each said carriage has a longitudinal axis and external radial recesses extending along each said carriage, said upper ring part and said lower ring part of said docking station are coaxially aligned to define an interior space for receiving and passing therethrough each said carriage;said docking station having internal carriage guides for carrying electrical power to said traction drives and for entering said radial recesses to keep each said carriage in proper alignment and stable while supplying electrical power to each said carriage. 92. A rocket launch device according to claim 91 wherein each said carriage has a triangular cross section with corner edges with said radial corner recesses extending along said corner edges; said lift ring assembly being supported by said tertiary cables, said lift ring assembly comprising: a tubular lift ring with a triangular cross section for receiving each said carriage, said tubular ring comprising: inwardly extending internal carriage guides engageable with said radial recesses of each said carriage for maintaining the orientation of each said carriage in said tubular ring, said tubular ring having a longitudinal axis coincident with the longitudinal axis of each said carriage, the angle of said longitudinal axis relative to ground is the elevation angle of said tubular ring. 93. A rocket launch system according to claim 92 wherein said carriage pivoting assembly tilts said tubular lift ring with respect to said secondary cables. 94. A rocket launch system according to claim 93 wherein a pair of said tertiary cables is on opposite sides of said tubular lift ring, and wherein said carriage pivoting assembly comprises: a rotational drive system operatively connected to said tubular lift ring for rotating said tubular ring;lift ring guides operatively connected to said tertiary cables; andpivot pins connected to and extending from said tubular lift ring, said pivot pins being pivotally attached to each of said lift ring guides;wherein said rotational drive system rotates said tubular lift ring to pivot about said pivot pins to change the elevation angle of said tubular lift ring and each said carriage received thereby. 95. A rocket launch system according to claim 94 wherein the center of gravity of said tubular lift ring falls in the geometric center of said tubular lift ring, said center of gravity being coincident with the axis of said pivot pins. 96. A rocket launch system according to claim 95 wherein said tubular lift ring includes a clamping mechanism for releasably locating each said carriage with the center of gravity of each said carriage being disposed on the axis of said pivot pins. 97. A rocket launch system according to claim 96 wherein said tertiary cables comprise two groups of cables of fixed length, said tertiary cables being connected to said lift ring guides to attach said lower hoist assembly to said lift ring guides, said tertiary cables being 180° apart around the circumference of said lift ring where said tertiary cables are attached to said lower hoist assembly. 98. A rocket launch system according to claim 96 wherein said carriage end gripper includes a set of four orifices sized and arranged to allow said secondary cables extending between said docking station and said rotational drive system to freely pass therethrough. 99. A rocket launch system according to claim 98 wherein said carriage end gripper further include a pair of orifices for allowing said tertiary cables extending between said lift ring assembly and said lower hoist assembly to pass. 100. A rocket launch system according to claim 99 wherein said lighter-than-air balloons provide tension to said three power and transporting primary cables to enable said primary cables to function with a rocket-transporting device disposed on said respective lines. 101. A rocket launch system according to claim 100 and further comprising: at least one large harness having interconnected arms and tensioning balloon holders on said at least one large harness for attachment to said lighter-than-air balloons, said tensioning balloon holders being attached to said power and transporting primary cables to provide said tension. 102. A rocket launch system according to claim 101 and further incorporating at least one lower spacer assembly for separating said three power and transporting primary cables from each other and attaching said respective tensioning balloon holders to said respective large harnesses and to said respective balloons. 103. A rocket launch system according to claim 102 wherein said at least one large harness comprises: three arms forming an equilateral triangle; said at least one lower spacer assembly comprises: three-sided lower spacer arms forming an equilateral triangle parallel to the respective arms of said respective large harnesses;said at least one lower spacer assembly having lower spacer assembly-connecting structure at the juncture of respective lower spacer arms; andsaid rocket launch system further comprises: lower spacer harness leads connecting said respective lower spacer assembly-connecting structure with said respective tensioning balloon holders. 104. A rocket launch system according to claim 103 and further incorporating: an upper spacer assembly having three arms forming an equilateral triangle having structure at the respective intersections of said three arms for separating said power and transporting primary cables from each other. 105. A rocket launch system according to claim 104 and further including: upper spacer assembly cable ties connecting the opposite ends of said respective three arms to said three arms of said respective large harnesses; andtension ties interconnecting said respective intersections of said three arms of said upper spacer assembly to the respective intersections of said three arms of said respective large harnesses. 106. A rocket launch assembly according to claim 105 wherein said three arms of said upper spacer assembly are parallel with the respective arms of said respective large harnesses; and wherein said rocket launch system further comprises: an upper spacer connecting structure disposed at the intersection of the respective upper spacer arms; andupper spacer connecting ties interconnecting said respective upper spacer connecting structure and said opposite ends of said arms of said respective large harnesses. 107. A rocket launch system according to claim 106 wherein said three arms of said large harness further include: tie holders at the midpoints of said respective three arms; and said rocket launch system further includes: cable leads interconnecting said upper spacer connecting structure of said arms of said upper spacer assembly and said tie holders of said respective arms of said at least one large harness. 108. A rocket launch system according to claim 107 wherein there are two or more large harnesses installed periodically along the length of said set of primary cables with said lighter-than-air balloons attached thereto to compensate for the full weight of said primary cables. 109. A rocket launch system according to claim 107 and further including a further upper spacer assembly for separating said power and transporting primary cables from each other. 110. A rocket launch system according to claim 109 and further including further upper assembly cable ties connected to said further upper spacer assembly and said upper harness. 111. A rocket launch system according to claim 110 wherein said further upper spacer assembly is located above said respective lower spacer assembly, said upper spacer assembly both separating said power and transporting primary cables from each other and attaching said respective tensioning balloon holders to said respective large harnesses and to said respective balloons, where said further upper spacer assembly comprises: three further upper spacer arms forming an equilateral triangle with arms parallel to the respective arms of said respective large harnesses;upper spacer arms connecting structure disposed at the intersection of the respective further upper spacer arms; anda set of further upper spacer connecting ties interconnects said respective further upper spacer connecting structure and said opposite ends of said arms of said respective large harnesses. 112. A rocket launch system according to claim 111 and further including stabilizing straps attached to said respective lower spacer assembly and to said upper spacer assembly to prevent said respective primary cables from touching said respective lighter-than-air balloons. 113. A rocket launch system according to claim 112 and further including: a stabilizer connected intermittently to each of said primary cables between said primary cables and said respective lighter-than-air balloons, said respective stabilizers including respective connecting members for connecting said respective stabilizers to said respective stabilizing straps. 114. A rocket launch system according to claim 113 wherein each of said respective stabilizers is composed of three stabilizing arms which collectively intersect to form an equilateral triangle. 115. A rocket launch system according to claim 114 wherein a pair of stabilizing straps is attached to said respective connecting members, said respective pairs of stabilizing straps form various angles; and wherein said rocket launch system includes strap connectors attached to said lighter-than-air balloons for enabling said stabilizing straps to contact said respective lighter-than-air balloons longitudinally. 116. A rocket launch system according to claim 101 and further including large harness reaction thrusters operatively connected to said at least one large harness for orienting said docking station, said lift ring assembly and said carriage end gripper to be oriented with respect to vertical to compensate for wind forces and for the deflation of any of said lighter-than-air balloons. 117. A rocket launch system according to claim 116 and further including position sensors for controlling the direction and force of said large harness reaction thruster. 118. A rocket launch system according to claim 117 wherein one of said reaction thrusters is disposed at the intersection of each of the respective arms of said at least one large harness. 119. A rocket launch system according to claim 118 wherein each of said reaction thrusters comprises: a fan mounted within a fan housing. 120. A rocket launch system according to claim 119 and wherein said rocket launch system further includes: a pair of arms disposed at the intersection of said respective arms of said at least one large harness; andcoaxial pins having a coaxial axis extending into said respective fan housings for enabling said respective fan housings to pivot about each of said respective coaxial axes in clockwise and counterclockwise directions. 121. A rocket launch system according to claim 120 wherein said rocket launch system further includes: respective rotatable support joints mounted at said respective tensioning balloon holders; and said respective reaction thrusters are pivotably and rotatably gimbaled electric thrusters for orienting said docking station, said lift ring assembly and said carriage end gripper with respect to vertical to compensate for wind forces and for deflation of any of said lighter-than-air balloons. 122. A rocket launch system according to claim 99 and further comprising: support cables other than said primary cables for attaching and supporting other items to said primary cables; andsupport structure for attaching said support cables to said respective primary cables, said support structure comprising: at least one primary cable flange extending from said respective primary cables in a plane including the longitudinal axis of each of said respective primary cables;a cable support member having cable connecting structure for connecting an end of said respective cables to said cable support member; andat least one cable support member flange attached to said cable support member for being attached to said at least one primary cable flange. 123. A rocket launch system according to claim 122 wherein at least one of said at least one primary cable flange and said at least one cable support member flange is a pair of spaced apart parallel flanges for receiving the other of said at least one primary cable flange and said at least one cable support member flange, and wherein said rocket launch system further comprises connecting structure for attaching said at least one primary cable flange and said at least one cable support member flange together. 124. A rocket launch system according to claim 123 wherein at least one end of said support cables comprises: a coupling yoke with a pair of spaced apart receiving members having aligned lug-receiving holes; wherein said support member comprises: a support plate having individual lug-receiving holes, said support plate slipping between said spaced apart lug-receiving members with said individual lug-receiving hole in alignment with said aligned lug-receiving holes; anda lug fastening said yoke and the cable attached thereto, to said support member. 125. A rocket launch system according to claim 77 and further comprising: a lower hoist assembly located above said lift ring assembly when said rocket launch system is in operation;a set of tertiary cables extending from said lower hoist assembly for being operationally connectable to and supporting said lift ring assembly; anda carriage end gripper disposed between said lower hoist assembly and said lift ring assembly and being operatively attached to said lower hoist assembly, said carriage end gripper being releasably and lockably engageable with a carriage in said lift ring assembly, said lower hoist assembly lifting said end gripper for lifting a carriage into engagement with said carriage pivoting assembly prior to the launching of a rocket from a carriage disposed in said lift ring assembly. 126. A rocket launch system according to claim 77 wherein each said carriage includes both retractable arms for holding a rocket and locking pin receptacles, and wherein said rocket launch system further includes: an upper hoist for lifting each said carriage, said upper hoist comprising: an upper hoist cable, wherein said upper hoist is reelable to either lower or raise said upper hoist cable with respect to said upper hoist;a tensioning balloon attachment frame for being operatively attached to said tensioning lighter-than-air balloons for both offsetting the self weight of the cables and supporting said docking station and the operational weight of a carriage in said docking station with a flight ready rocket in each said carriage, and said tensioning balloon attachment frame contributing to the tensioning of the cables, said tensioning balloon attachment frame comprising: an upper ring and a lower ring, said upper ring and said lower ring being counter rotational;a first geared rotational drive system including first reaction force thrusters;a second geared rotational drive system including second reaction force thrusters;wherein said docking station further comprises an upper ring part, a lower ring part and a ring bearing, said first rotational drive system rotating said upper ring part with respect to said lower ring part;wherein said carriage pivoting assembly comprises a rotational drive system for changing an elevation angle of said tubular lift ring;said first geared rotational drive system and said second geared rotational drive system cooperating to provide opposed rotation of said upper ring with respect to said lower ring of said tensioning balloon attachment frame, and said first geared rotational drive system and said second geared rotational drive system cooperating to effect the rotation of said upper ring part of said docking station with said lower ring of said tensioning balloon attachment frame to prevent said cables from twisting around each other;at least two upper force thrusters attached to said tensioning balloon attachment frame and at least two lower force thrusters attached to said docking station for countering wind induced rotation and/or rotation resulting from the rotation of a carriage when each said carriage is held in said upper ring part of said docking station;wherein said carriage end gripper grips the upper end of a carriage held by said lift ring assembly, and said upper hoist lifts each said carriage end gripper and the carriage out of engagement with said lower ring part of said docking station and leaving the lower end of the carriage engaged by said upper ring part of said docking station, prior to the launch of a rocket from each said carriage;said first geared rotational drive system and said second rotational geared drive system rotating said upper part of said docking station and said lower ring of said tension balloon attachment frame and parts connected thereto into a desired direction of azimuth, while said at least two upper force thrusters and said at least two lower force thrusters hold said docking station and said tension balloon attachment frame steady until a selected optimal direction in azimuth is reached, whereafter said upper hoist lifts each of said lower hoist carrier, said carriage end gripper, said tubular lift ring along with a carriage loaded with a rocket to an increasing height for the safe launch of the rocket in the carriage, and said upper hoist releasing said lock pins from said lock pin receptacles in each said carriage, and said rotational drive system rotates the said carriage in said lift ring assembly to a desired elevation angle, and said upper hoist raises said carriage end gripper and said carriage end gripper is guided by said secondary cables and said tertiary cables; andsaid upper hoist reels out said upper hoist cable with the assistance of said traction drives to effect the downward travel of carriage the loaded with a rocket at the local acceleration due to gravity, the retractable arms in the carriage being withdrawable from the rocket and the rocket is boosted clear of the carriage to prevent the rocket from damaging any components of said rocket launch system when the rocket engines are fired to launch the rocket into space; the empty carriage and other components suspended by said hoist cable being decelerated by said upper hoist and said traction drives, and the carriage being reinserted into said docking station and returned to earth. 127. A rocket launch system according to claim 73 wherein said lighter-than-air balloons are operatively attached to said three power and transporting primary cables intermittently along the length of said three power and transporting primary cables to support cumulatively said three power and transporting primary cables, and any other structure carried by said three power and transporting primary cables which is utilized in the launch of a rocket. 128. A rocket launch system according to claim 127 and further including: respective sets of spacer assemblies located intermittently along said three power and transporting primary cables, each of said sets of spacer assemblies having cable engaging structure for engaging respective ones of said three power and transporting primary cables to maintain a spaced separation between said respective three primary cables, and wherein said lighter-than-air balloons are respectively, operatively connected to at least one of said spacer assemblies. 129. A rocket launch system according to claim 73 wherein said lighter-than-air balloons are operatively attached to said three power and transporting primary cables intermittently along the length of said three power and transporting primary cables to support cumulatively said three power and transporting primary cables, and any other structure carried by said three power and transporting primary cables which are utilized in the launch of a rocket. 130. A rocket launch system according to claim 73 wherein each said carriage includes a continuous heat-and-pressure resistant tube for holding a rocket, said tube preventing dangerous exhaust gases from leaving each said carriage through any side of each said carriage. 131. A rocket launch system according to claim 72 wherein said carriage comprises: opposed end openings; andend covers at said respective end openings to protect the interior of said respective carriage and any rocket contained in said respective carriage from the weather. 132. A rocket launch system according to claim 131 wherein said end covers are retractable membranes. 133. A rocket launch system according to claim 131 wherein at least one of said end covers is movable between open and closed positions to open and close said at least one end opening. 134. A rocket launch system according to claim 72 wherein said respective carriages have receptacles for being used to lift said respective carriages into components of said rocket launch system. 135. A rocket launch system according to claim 134 wherein said receptacles are pin lock receptacles. 136. A rocket launch system according to claim 72 wherein said carriage comprises: internal retractable arms having an active condition for holding a rocket securely within said carriage, and being retracted to an inactive condition to enable launch of the rocket from said carriage. 137. A rocket launch system according to claim 136 wherein said retractable arms hold a rocket with the center of gravity of the rocket being coincident with the center of gravity of said carriage. 138. A rocket launch system according to claim 136 wherein said retractable arms comprise: head members; said retractable arms having an active position wherein said respective head members can enter slots in any rockets having slots for receiving said head members to hold the rocket securely in each said carriage, and an inactive position wherein said head members are retractable from the respective slots in such rocket having slots to enable launch of the rocket. 139. A rocket launch system according to claim 138 wherein each said carriage comprises: a heat-and-pressure resistant tube having a cavity for holding said retractable arms; andprotecting doors movable between an open position enabling movement of said retractable arms to hold a rocket, and a closed position to protect said retractable arms. 140. A rocket launch system according to claim 139 wherein said heat-and-pressure resistant tube comprises: a cavity-covering end door;an airflow deflector for pivoting between an open position for assisting in enabling said retractable arms to hold a rocket, and a closed position for assisting in protecting said protecting doors and said cavity. 141. A rocket launch system according to claim 140 wherein said cavity includes: pivot pins for mounting said end door for pivoting between said open and closed positions. 142. A rocket launch system according to claim 140 wherein each of said retractable arms comprises: a base member mounted in said cavity for moving said retractable arm between said active and said inactive positions;a stem connecting said base member to said head member;said retractable arm being movably coupled to said cavity-covering end door;and wherein said rocket launch system further comprises: a hydraulic cylinder movably coupled to said retractable arm for moving said retractable arm between the active and inactive position of said retractable arm;said hydraulic cylinder moving said retractable arm to the inactive position in response to movement of said end door to the open position to enable launch of a rocket in each said carriage, and moving said retractable arm to the active position in response to movement of said end door to the closed position to hold the rockets securely in said respective carriage. 143. A rocket launch system according to claim 72 wherein said carriage comprises: three sides defining in cross section a triangle, each side intersecting two other sides to form three intersections; andexternal recesses at said intersections for being guided in respective components of said rocket launch system. 144. A rocket launch system according to claim 72 wherein said traction drives comprise: a set of traction wheels associated with the respective carriages for engaging said at least one power and transporting primary cable for transporting each said carriage along said at least one power and transporting primary cable, said set of traction wheels respectively comprising: opposing cylindrical wheels having annular grooves for partially enveloping said at least one primary cable on which said carriage rides; wherein said traction drives are a reversible electrically powered energizing apparatus, said traction drives derive electrical power from said set of electrical power lines when said set of traction drives lift each said carriage along said at least one primary cable, and said reversible electrically powered energizing apparatus reversibly delivers electrical power to said at least one electrical power line when said traction drives move said carriage under the influence of gravity to descend said at least one primary cable. 145. A rocket launch system according to claim 144 wherein said reversible traction drives comprise: a motor generator operatively coupled with said respective cylindrical wheels for transferring electrical power across said rotating cylindrical wheels to said at least one primary cable as each said carriage descends said at least one primary cable. 146. A rocket launch system according to claim 72 wherein each said carriage comprises: a retractable arm for entering an arm-receiving opening in a respective rocket for holding the respective rocket in said carriage prior to launch, said retractable arm being retractable from the opening in preparation for launch of the respective rocket. 147. A rocket launch system according to claim 72 wherein each said carriage comprises: an opening for receiving a retractable arm from a respective rocket for holding the respective rocket in each said carriage prior to launch, said opening enabling retraction of the retractable arm in preparation for launch of the respective rocket. 148. A rocket launch system according to claim 72 and further comprising: a one-occupant rocket to be launched from each said carriage, said one-occupant rocket having a steerable motor. 149. A rocket launch system according to claim 72, and further comprising: a main rocket being launched from each said carriage for being manned by an occupant; anda launch or re-entry space suit worn by the occupant, said space suit comprising: a rigid outer shell with an internal sleeve, said internal sleeve being made of a soft material;a helmet with a rigid outer shell;an internal face mask;said space suit being capable of holding a liquid for accommodating G-force effects;an inner suit for laving close to the occupant wearing said space suit to separate the occupant from the liquid;an electro-mechanical piston apparatus: a cylinder for operatively holding said piston apparatus;said piston being movable in and out of said cylinder, and said piston apparatus being operated by electro-mechanical apparatus for controlling the volume of said suit, for normal respiration;a set of powered joints provided at locations corresponding to at least some of the joints of the occupant wearing said suit, said powered joints being lockable in an optimally aerodynamic position for launch, the occupant being upright and loaded feet first onto the top of said rocket, while resisting the G-force effects of the rocket during launch; andelastic tendons, each tendon being attached to said suit and being tangent, to said sleeve and being attached to said sleeve. 150. A rocket launch system according to claim 149, wherein the space suit further includes: a ventilating apparatus for connecting with an air supply. 151. A rocket launch system according to claim 149 wherein there is a double seal between the face of the occupant and said face mask, and wherein said space suit further includes: a leakage tube for draining fluid from said double seal of said face mask. 152. A rocket launch system according to claim 149 wherein said soft material is selected from the group consisting of elastic webbing, soft open-pore foam and soft open-pore webbing. 153. A rocket launch system according to claim 72 and further comprising a main rocket being launched from each said carriage for being manned by an occupant, and a launch or re-entry suit to be worn by the occupant, said suit comprising porous pads on the exterior of said suit for being filled with fluid and being substantially fillable with fluid during launch and during re-entry to cool by evaporation the exterior of said suit. 154. A rocket launch system according to claim 72 and further comprising a main rocket being launched from each said carriage for being manned by an occupant, and a launch or re-entry suit to be worn by the occupant, said suit comprising an ablative exterior material with thermal insulation. 155. A rocket launch system according to claim 72 and further comprising a main rocket being launched from each said carriage for being manned by an occupant, and a launch or re-entry suit to be worn by the occupant, said suit comprising an exterior material having heat-resistant thermal insulation. 156. A rocket launch system according to claim 72 and further comprising a main rocket for being controllably launchable from each said carriage by said rocket launch system, said controlled launch of said main rocket ceasing at a period after said controlled launch, a core rocket being releasable from said main rocket after launch of said main rocket, and at least one pod for respectively holding an occupant and being detachably connected to said core rocket, said at least one pod being ejectable from said core rocket for being guided to the earth or a destination in orbit. 157. A rocket launch system according to claim 156 and further comprising a windshield connected to said at least one pod for protecting the occupant held in said at least one pod against high velocity air. 158. A rocket launch system according to claim 72 and further including: a main rocket for being launched from each said carriage;at least one pod for being ejectable from said main rocket; anda sled-like re-entry frame included in said at least one pod, said re-entry frame comprising steering fins and an aerodynamic spike with a disc serving as a forward shockwave initiator. 159. A rocket launch system according to claim 72 and further including: a rocket for launching from each said carriage; andan aerospace plane attached to the body of said rocket, said aerospace plane having folded lift and directional control structures attached to the body of said aerospace plane, and said aerospace plane having wings movable between folded and unfolded positions under the control of said folded lift and directional control structures. 160. A rocket launch system according to claim 72 and further including a rocket for launching from each said carriage; and a lifting-type re-entry vehicle, said lifting-type re-entry vehicle having folded lift and directional control structures having folded and unfolded configurations. 161. A rocket launch system according to claim 72 and further including: a rocket for launching from each said carriage, said rocket having a payload protected by aerodynamic shells, said aerodynamic shells being detachable after said rocket has left the earth's atmosphere following the launch of said rocket and said payload has entered space. 162. A rocket launch system according to claim 72 wherein in the event each said carriage transports a rocket having at least one fin, each said carriage comprises: an internal support for holding the rocket, said internal support including:slots for receiving the rocket having at least one fin and holding the rocket having at least one fin stable in each said carriage. 163. A rocket launch system according to claim 70 wherein said traction drives are reversible traction drives for deriving electrical power from said at least one electrical power line when said traction drives lift said rocket-transporting device along said at least one rocket-transporting device line, and said reversible traction drives reversibly deliver electrical power to said at least one electrical power line when said traction drives move said rocket-transporting device under the influence of gravity to descend said at least one rocket-transporting device line. 164. A rocket launch system according to claim 163 wherein said traction drives comprise: a set of traction drive wheels associated with said respective carriages for engaging said at least one electrical power line, and said set of traction drive wheels being operatively connected to said reversible traction drives; said traction drives serving as regenerative brakes when said respective carriages move along said at least one rocket-transporting device line under the influence of gravity to effect the delivery of electrical power to said at least one electrical power line during the braking of said respective carriages. 165. A rocket launch system according to claim 1 wherein said lighter-than-air balloons are operatively attached to said at least one electric power line and to at least one said rocket-transporting device line intermittently along the length of said at least one power line and said at least one rocket-transporting device line to support cumulatively said respective lines, and any other structure carried by said at least one transporting device line which is utilized in the launch of a rocket. 166. A rocket launch system according to claim 1 wherein the electric power is continuously withdrawable along said at least one electric power line. 167. A rocket launch system according to claim 166 wherein said at least one electric power line and said at least one rocket-transporting device line are integrally combined into at least one power and transporting primary cable. 168. A rocket launch system according to claim 167 and further comprising at least one rocket-transporting device for transporting a rocket along said at least one power and transporting primary cable, said at least one rocket-transporting device including: traction drives for driving said respective rocket-transporting devices along said at least one power and transporting primary cable; and a motor-generator for deriving electrical power from said at least one electric power line of said at least one power and transporting primary cable when said traction drives require energy to cause said at least one rocket-transporting device to travel upwards on said at least one power and transporting primary cable, and for supplying electrical power to said at least one electric power line when said traction drives generate electric power when said traction drives retard the downward motion of said at least one rocket-transporting device as said at least one rocket-transporting device travels downwards on said at least one power and transporting primary cable under the influence of gravity. 169. A rocket launch system according to claim 168 wherein said respective traction drives comprise: a set of traction drive wheels associated with each of said respective rocket-transporting devices for engaging said at least one power and transporting primary cables for transporting said respective rocket-transporting devices along said at least one power and transporting primary cable. 170. A rocket launch system according to claim 168 wherein said traction drives are reversible traction drives for deriving electrical power from said at least one electrical power line of said at least one power and transporting primary cable when said traction drives lift said rocket-transporting device along said at least one rocket-transporting primary cable, and said reversible traction drives reversibly delivers electrical power to said at least one electrical power line of said at least one power and transporting primary cable when said traction drives move said rocket-transporting device under the influence of gravity to descend said at least one power and transporting cable. 171. A rocket launch system according to claim 170 wherein said traction drives comprise: a set of traction drive wheels associated with said respective rocket-transporting devices for engaging said at least one power and transporting primary cable for both transporting said rocket-transporting device along said at least one power and transporting primary cable, and said set of traction drive wheels being operatively connected to said reversible electrically powered energizing apparatus; said traction drives serving as regenerative brakes when said respective carriages move along said at least one primary cable under the influence of gravity to effect the delivery of electrical power to said at least one electric power line of said at least one power and transporting primary cable during the braking of said respective carriages. 172. A rocket launch system according to claim 168 wherein said at least one power and transporting primary cable comprises three power and transporting primary cables for carrying three-phase power, wherein each of said three power and transporting primary cables carry one of the phases. 173. A method for removing debris from an orbit of the debris around the earth using a rocket launch system, the rocket launch system comprising: at least one electric power line for carrying electrical power from a source of electrical power, at least one power line having a low end portion for being positioned at a low altitude and a high end portion for extending into high altitudes;at least one rocket-transporting device line for transporting a rocket-transporting device between a low altitude and a high altitude, the at least one rocket-transporting device line having a low end portion for being positioned at a low altitude and a high end portion for extending into high altitudes;wherein the at least one power line of the at least one electric power line and the at least one rocket-transporting device line lines of the set of rocket-transporting device lines are integrally combined into at least one power and transporting primary cable;lighter-than-air balloons connected to said at least one power lines and at least one rocket-transporting device line for holding said at least one power line and the at least one rocket-transporting device line upwards to a high altitude;a docking station operatively connected to the at least one power and transporting primary cable at a terminal position along the length of said at least one power and transporting primary cable, the docking station being structured to receive a rocket-transporting device as part of a preparation for a launch of a rocket being transported in a rocket-transporting device;at least one power and guiding secondary cable operatively attached to the docking station and being extendable to a higher altitude than the altitude of the docking station, the rocket launch system further comprising lighter-than-air balloons operatively connected to the at least one power and guiding secondary cable for holding and tensioning the at least one power and guiding secondary cable aloft above the at least one power and transporting primary cable; anda lift ring assembly in operative engagement with the at least one power and guiding secondary cable for deriving electrical power from and being guided by the at least one power and guiding secondary cable, the lift ring assembly being positionable above the docking station and being operatively engageable with a rocket-transporting device disposed in the docking station for lifting the rocket-transporting device out of the docking station and having a rocket-transporting device pivoting assembly for being tilted to a desired rocket launch angle, said lift ring assembly including: a tubular ring for maintaining the orientation of a rocket-transporting device in the lift ring assembly and being pivotable by the lift ring assembly; anda rotational drive assembly for changing the elevation angle of said tubular ring and a rocket-transporting device held thereby;a lower hoist assembly located above the lift ring assembly when the rocket launch system is in operation;at least one supporting tertiary cable extending from the lower hoist assembly for being operationally connectable to and supporting the lift ring assembly; anda rocket-transporting device end gripper disposable between the lower hoist assembly and the lift ring assembly and being operatively attached to the lower hoist assembly, the rocket-transporting device end gripper being releasably and lockably engageable with a rocket-transporting device in the lift ring assembly, the lower hoist assembly lifting the rocket-transporting device end gripper for lifting a rocket-transporting device into engagement with the rocket-transporting device pivoting assembly prior to the launching of a rocket from a rocket-transporting device disposed in said the ring assembly;a rocket-transporting device for transporting a rocket along both said at least one power and transporting cable and the at least one power and guiding secondary cable, the rocket-transporting device including: traction drives for driving the rocket-transporting device along the at least one power and transporting primary cable, the traction drives including: an electrically powered energizing apparatus for deriving electrical power from the at least one power and transporting primary cable when the traction drives require energy to cause the rocket-transporting device to travel upwards on the at least one power and transporting cable;wherein said method comprises: placing a rocket in said rocket-transporting device;driving the rocket-transporting device with a rocket placed in rocket-transporting device and along the at least one power and transporting primary cable to the docking station and along the at least one power and guiding secondary cable to the lift ring assembly using the traction drives to derive electrical power from both the respective at least one power and transporting primary cable and the at least one power and guiding secondary cable;using the lower hoist assembly to lower the lift ring assembly to engage the upper part of the docking station;lowering the end gripper and attaching the end gripper to the rocket-transporting device;using the lower hoist assembly to lift the rocket-transporting device into further engagement with the lift ring assembly such that the combined centers of gravity of the lift ring assembly, the rocket-transporting device and the rocket coincide with the pivot axis of the lift ring assembly;disengaging the end gripper from the rocket-transporting device;guiding the lift ring assembly with the secondary cables and supporting the lift ring assembly with the tertiary cables, and lifting the rocket-transporting device until the rocket-transporting device is out of engagement with the docking station;rotating the tubular ring to put the rocket-transporting device at an appropriate angle for launch;actuating the rocket to launch the rocket to the orbit of the debris; andusing the rocket to remove the debris from the orbit. 174. A rocket launch system comprising: at least one electric power line for carrying electrical power from a source of electrical power from a remote electric power system on the earth, the electric power being continuously withdrawable along said at least one electric power line, said at least one electric power line having a low end portion for being positioned at a low altitude and a high end portion for extending into high altitudes;at least one rocket-transporting device line for transporting a rocket-transporting device between a low altitude and high altitudes, said at least one rocket-transporting device line having a low end portion for being positioned at a low altitude and a high end portion for extending into higher altitudes;lighter-than-air balloons connected to said at least one electric power line and said at least one rocket-transporting device line for supporting said at least one electric power line and said at least one rocket-transporting device line upwards to a high altitude;a rocket-transporting device for transporting a rocket along said at least one rocket-transporting device line, said rocket-transporting device including: traction drives for driving said rocket-transporting device along said at least one rocket-transporting device line, said traction drives comprising: a motor-generator for deriving electrical power from said at least one electric power line when said traction drives require energy to cause said rocket-transporting device to travel upwards on said at least one rocket-transporting device line, and for supplying electrical power to said at least one electric power line when said motor-generator generates electric power when said traction drives retard the downward motion of said rocket-transporting device as said rocket-transporting device travels downwards on said at least one rocket-transporting device line under the influence of gravity;said rocket-transporting device comprising: an interior compartment configured to contain a rocket, the rocket being ejectable from said interior compartment during launch;wherein said respective at least one electric power line and said at least one rocket-transporting device line are integrally combined into at least one power and transporting primary cable, said respective rocket-transporting devices being driven along said at least one power and transporting primary cable by said traction drives upon energization by said motor-generator. 175. A rocket launch system according to claim 174 wherein said traction drives comprise: a set of traction wheels associated with the respective rocket-transporting device for engaging said at least one power and transporting primary cable for transporting the respective rocket-transporting devices along said at least one power and transporting primary cable, said set of traction wheels respectively comprising: opposing cylindrical wheels having annular grooves for partially enveloping said at least one primary cable on which said respective rocket-transporting device rides.