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OwnerJacob B. Lopata, Michel R. Kamelinventors
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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.
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, wherein the space vehicle is deployed from a reusable winged vehicle.
An air-launched space vehicle, the space vehicle comprising a first stage motor, a first interstage, a second stage motor, a second interstage, a third stage motor, a single guidance, navigation, and control unit, a heat shield, and a payload, wherein said space vehicle is deployed to a destination in Earth orbit by means of a reusable winged vehicle.
A system for placing a payload at orbital or sub-orbital altitudes, the system comprising a launch system and satellite bus system, 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.
A launch system for placing a payload into a desired trajectory about the Earth, the launch system comprising:
Dependencies are inferred from the claim text.