초록 ▼

A low cost, on demand, dedicated launch system is provided for placing micro satellites or space-based instruments at orbital and sub-orbital altitudes and velocities. The invention describes a space launch vehicle (SLV) that incorporates a single, integrated guidance, navigation, and control unit (

A low cost, on demand, dedicated launch system is provided for placing micro satellites or space-based instruments at orbital and sub-orbital altitudes and velocities. The invention describes a space launch vehicle (SLV) that incorporates a single, integrated guidance, navigation, and control unit (GNCU) that performs all guidance and control for the SLV from main stage ignition to orbital insertion. The GNCU can remain with the payload after orbital insertion to provide satellite station keeping and orbital maneuvering capability. The use of a single integrated avionics unit for all guidance, navigation, and control simplifies the SLV, reducing weight and significantly reducing cost. In addition, this architecture allows for a combined launch and satellite bus system as the GNCU can also be used as a satellite bus. This further reduces cost and increases the payload capacity to orbit by optimizing the use of launch vehicle and satellite bus subsystems and reducing non-instrument mass delivered to orbit. All support functions are provided by the IDMV. This approach represents a significant improvement over conventional systems, especially with respect to the orbital launch of payloads less than about 100 kg.

대표청구항 ▼

1. A launch system for placing a payload in orbit, the launch system comprising: an air-launched space vehicle, wherein the space vehicle is integrated with a payload and including a means for head-end steering, wherein the space vehicle is deployed from a reusable winged vehicle.2. The launch syste

1. A launch system for placing a payload in orbit, the launch system comprising: an air-launched space vehicle, wherein the space vehicle is integrated with a payload and including a means for head-end steering, wherein the space vehicle is deployed from a reusable winged vehicle.2. The launch system of claim 1, wherein the reusable winged vehicle is a turbo-jet powered aircraft.3. The launch system of claim 1, wherein the payload has a weight of less than about 100 kg.4. The launch system of claim 1, wherein the space vehicle further comprises an expendable, multi-stage, wingless, rocket powered vehicle.5. The launch system of claim 1, wherein the space vehicle further comprises a means of accelerating the space vehicle to orbital velocity and a means for guiding the space vehicle from the point of deployment to a destination in Earth orbit.6. The launch system of claim 1, wherein the space vehicle further comprises a means for guiding the space vehicle from the point of deployment to a destination in Earth orbit.7. The launch system of claim 6, wherein the point of deployment is at an altitude less than about 12 km.8. The launch system of claim 6, wherein the point of deployment is at an altitude less than about 25 km.9. A system for placing a payload at orbital or sub-orbital trajectories, the system comprising a launch system and satellite bus system including a guidance, navigation and control unit (GNCU), wherein the launch system and satellite bus system are integrated, and wherein said launch system and satellite bus system are controlled by a single mission computer system and maneuvered by a head-end steering means disposed on the GNCU.10. The system of claim 9, wherein the launch system and satellite bus are operated using a single telemetry system.11. The system of claim 9, wherein the launch system and satellite bus are operated using a single guidance, navigation and propulsion system.12. The system of claim 9, wherein the payload has a weight of less than about 100 kg.13. The system of claim 9, wherein the payload comprises an instrument.14. A launch system for placing a payload into a desired trajectory about the Earth, the launch system comprising: a payload configured to o perate in a trajectory about the Earth; a launch vehicle configured to deliver the payload into the trajectory about the Earth; a guidance, navigation and control unit including a means for head-end steering for maneuvering the launch vehicle; and a guidance unit, wherein the guidance unit is configured to control the delivery of the payload by the launch vehicle and is further configured to monitor and control the operation of the payload on orbit.15. The launch system of claim 14 wherein the payload comprises a satellite.16. The launch system of claim 14 wherein the payload comprises an instrument.17. The launch system of claim 14 wherein the guidance unit comprises a mission computer system.18. A space launch vehicle (SLV) or placing payloads in earth orbit, comprising:rocket means for providing propulsion to said SLV; payload means coupled to said rocket means, said payload means having a mass of less then approximately 100 kilograms, said payload means being adapted to perform functions after being placed in orbit; a single guidance, navigation and control unit (GNCU) means for controlling the operation of said rocket means and said payload means comprising: an attitude control means for maneuvering said SLV while said SLV is operating in a launch phase. 19. The device of claim 18 wherein said payload means comprises a satellite.20. The device of claim 18 wherein said GNCU means is integrated with said payload and is adapted to perform guidance and control of the SLV through a launch phase and a maneuvering phase into a desired trajectory.21. The device of claim 18 wherein said rocket means includes a nozzle, said nozzle being fixed in a single position.22. The device of claim 18 wherein said rocket means comprises a plurality of stages, each stage having a nozzle in a fixed position.23. The device of claim 18 wherein said GNCU includes attitude control means for pitch, roll and yaw control.24. The device of claim 18 wherein said GNCU includes reaction control thrusters for spinning said SLV about a central axis.25. The device of claim 18 wherein said rocket means includes a propellant tank, and plumbing is coupled between said propellant tank and said GNCU such that said GNCU may draw propellant from said propellant tank for use in maneuvering said SLV.26. A method for launching a space launch vehicle (SLV), comprising the steps of:attaching said SLV to a winged reusable vehicle, said SLV including a payload; flying said winged reusable vehicle at a predetermined altitude; causing said winged reusable vehicle to perform a pull-up maneuver until a desired attitude is reached; releasing said SLV after said desired attitude is reached; maneuvering said SLV while in flight using a means or head end steering. 27. The method of claim 26, further comprising, after said releasing step, the step of rotating said space launch vehicle about a central axis.28. The method of claim 26, wherein said desired attitude constitutes said reusable winged vehicle being in a climb with a deck angle of a approximately 45° to 55°.29. A method for launching a space launch vehicle (SLV), comprising the steps of:attaching said SLV to a winged reusable vehicle, said SLV including at least a rocket means having at least one stage and a means for head end steering, where said at least one stage further includes a nozzle in a fixed position; flying said winged reusable vehicle at a predetermined altitude; causing said winged reusable vehicle to perform a pull-up maneuver until it is climbing at a deck angle of approximately 45°-55°; releasing said SLV after said desired attitude is reached; spinning said SLV about a central axis; and maneuvering said SLV while in flight using said means for head end steering. 30. The method of claim 29 wherein said SLV further includes a payload, and wherein a single guidance, navigation and control unit control the operation of said SLV and said payload.31. The method of claim 30, wherein said payload comprises a satellite.32. The method of claim 30 where said payload comprises an instrument.33. An instrument delivery and maintenance vehicle (IDMV), comprising:a guidance, navigation and propulsion (GNP) means for providing propulsion to said IDMV and controlling the operation of said IDMV and provides for head end steering for maneuvering said IDMV in a launch phase; an instrument coupled to said GNP, said instrument intended to be placed in a desired trajectory; wherein said GNP further controls the operation of said instrument. 34. The device of claim 33 wherein said GNP comprise a guidance navigation and control unit and a rocket means having at least one stage.35. An instrument delivery and maintenance vehicle (IDMV), comprising:an instrument intended to be placed in a desired trajectory; a guidance, navigation and propulsion (GNP) means coupled to said instrument, said GNP including: rocket means having at least one stage for providing propulsion to said IDMV; a guidance navigation and control unit for controlling the operation of said IDMV; and wherein said IDMV further comprises a means for head end steering for maneuvering said IDMV in a launch phase.