초록 ▼

A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a

A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a range of distances from one another. In a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections.

대표청구항 ▼

1. A launch system comprising: a nose section comprising a nose coupling surface;a tail section comprising a tail coupling surface facing the nose coupling surface; anda mast coupling the nose and tail sections, the mast being configured to expand and retract to displace the nose and tail sections w

1. A launch system comprising: a nose section comprising a nose coupling surface;a tail section comprising a tail coupling surface facing the nose coupling surface; anda mast coupling the nose and tail sections, the mast being configured to expand and retract to displace the nose and tail sections within a range of distances from one another during operation;wherein in a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections;further comprising aerodynamic surfaces located on either one or both of the nose and tail sections, wherein the aerodynamic surfaces are configured such that the launch system, in its retracted state, is capable of effectuating a horizontal landing, wherein the aerodynamic surfaces are configured only to support a load of the launch system for landing in its retracted state and wherein the aerodynamic surfaces are incapable of supporting loads in addition to the load of the launch system in its retracted state. 2. The launch system of claim 1, wherein the mast weight is less than 10% of the total combined weight of the nose section, the tail section and the mast. 3. The launch system of claim 1, wherein the nose and tail coupling surfaces each comprise complementary ones of a plurality of connecting pairs configured to structurally couple the nose and tail sections to one another or to structurally couple the nose and tail sections to opposing ends of a payload module, the payload module being released from the launch system after launch and before landing. 4. The launch system of claim 3, wherein the nose and tail coupling surfaces comprise first and second circumferential flanges, the first circumferential flange comprising a plurality of pins configured to actuate between a radially deployed state and a radially retracted state and the second circumferential flange comprising a plurality of apertures configured to receive the plurality of pins in the deployed state to couple the nose and tail coupling surfaces, wherein one of the first and second circumferential flanges overlaps the other one of the first and second circumferential flanges. 5. The launch system of claim 4, further comprising a payload module having third and fourth flanges disposed at the opposing ends, the third and fourth flanges having one or the other of the plurality of pins or apertures to cooperate with one or the other of the first and second flanges of the nose and tail coupling surfaces, respectively. 6. The launch system of claim 1, the payload module comprising one or a plurality of plates or push rods actuated to push against the mast after the payload is released from the launch system. 7. The launch system of claim 1, wherein the launch system is in a first expanded state and the launch system further comprises one or a combination of a releasable payload module and a releasable fuel module structurally coupled to the nose and tail sections, the payload module and/or the fuel module each being configured to be released from the launch system after launch and before landing. 8. The launch system of claim 7, further comprising one or more arms deployable from one or both of the nose and tail sections, the one or more arms comprising a plurality of pivoted sections and an end portion being configured to releasably couple and manipulate one or both of the payload module and the fuel module structurally coupled to the nose and tail sections. 9. The launch system of claim 7, wherein the payload module comprises a plurality of subunits structurally coupled together by a plurality of connecting pairs. 10. The launch module of claim 7, wherein the payload module comprises a return capsule configured to return an item from orbit, the return capsule comprising an enclosed cavity to house the item, an access door, a heat-of-reentry shield, and orbital engines. 11. The launch system of claim 1, further comprising at least one external fuel source, the at least one external fuel source being released from the launch system after launch. 12. The launch system of claim 1, further comprising one or a combination of solid-fuel rockets and/or liquid-fuel rockets releasably coupled to the launch system, the one or more solid-fuel rockets and/or liquid-fuel rockets being released from the launch system after launch. 13. The launch system of claim 12, wherein the solid-fuel rockets and the liquid-fuel rockets each comprise front and aft sections and a mast coupling the front and aft section, the mast being actuated to a first expanded state to couple a fuel section between the front and aft sections, a second expanded state to separate either one or both of the front and aft sections from the fuel section, and to a retracted state to couple the front and aft sections together after releasing the fuel section from the front and aft sections. 14. A method for assembling a payload module to a launch system, the method comprising: providing the launch system of claim 1;actuating the mast to a first elongated state in which the nose and tail sections are displaced at a distance that is greater than a length of a payload;positioning the payload between the nose and tail sections; andactuating the mast to a second elongated state in which the nose and tail coupling surfaces rigidly attach and engage the payload's forward and rearward facing surfaces, respectively. 15. The method of claim 14, wherein the remote location is in orbit and wherein the launch system comprises orbital maneuvering engines. 16. The method of claim 14, further comprising coupling one or a combination of one or more solid-fuel rockets or one or more liquid-fuel rockets to the space launch system.