Integrated launch and spacecraft propulsion system
AssigneeSpace Sciences Corporation
InventorDavid P. Snowhook
Life of this patent
Estimating the term…
Abstract
A single-stage-to-orbit integrated launch and payload system is provided that includes a support structure, a propulsion system that is supported by the support structure and provides both launch propulsion and on-orbit payload propulsion, a control system that is supported by the support structure and controls both launch functions and on-orbit functions, and an electrical power system that is supported by the support structure and provides launch electrical power and on-orbit payload electrical power.
Claims25
A single-stage-to-orbit integrated launch and spacecraft system comprising:
- a support structure;
- a spacecraft payload for performing on-orbit payload functions;
- a propulsion system that is supported by said support structure and provides both launch propulsion and on-orbit spacecraft maneuvering propulsion;
- a unitary control system that is supported by said support structure and controls launch functions, on-orbit spacecraft maneuvering functions and the on-orbit payload functions;
- and
- an electrical power system that is supported by said support structure and provides launch electrical power, on-orbit spacecraft maneuvering electrical power and on-orbit payload electrical power.
A single-stage-to-orbit integrated launch and on-orbit payload system comprising:
- a payload for performing on-orbit payload functions;
- single-stage propulsion means for providing both launch propulsion and on-orbit payload propulsion;
- power means for providing both launch electrical power and on-orbit payload electrical power;
- unitary control means for controlling both launch functions and the on-orbit payload functions;
- and
- structural means for supporting said single-stage propulsion means, said power means, and said control means.
A single-stage-to-orbit integrated launch and on-orbit payload system comprising:
- a payload for performing on-orbit payload functions;
- a launch subsystem;
- an on-orbit subsystem;
- a common support structure that supports both said launch subsystem and said on-orbit subsystem;
- a common propulsion system that provides propulsion to both said launch subsystem and said on-orbit subsystem and is supported by said common support structure;
- a common, unitary control system that controls said launch subsystem, said on-orbit subsystem and said payload to perform the on-orbit payload functions, said control system being supported by said common support structure;
- and
- a common electrical power system that powers said launch subsystem, said on-orbit subsystem, and said payload while on-orbit and that is supported by said common support structure.
A single-stage spacecraft launching and on-orbit maneuvering system comprising:
- an oxidizer tank storing liquid oxidizer for spacecraft launch and gaseous oxidizer for on-orbit spacecraft maneuvering;
- a fuel tank storing liquid fuel for spacecraft launch and gaseous fuel for on-orbit spacecraft maneuvering;
- propulsion means receiving the liquid oxidizer from said oxidizer tank and the liquid fuel from said fuel tank for propelling a spacecraft during launch and receiving the gaseous oxidizer from said oxidizer tank and the gaseous fuel from said fuel tank for propelling the spacecraft during on-orbit maneuvers;
- and
- a controller for controlling said propulsion means to utilize the liquid oxidizers and the liquid fuel during launch and to utilize the gaseous oxidizer and the gaseous fuel during on-orbit maneuvers.
A method of launching and using a single-stage-to-orbit integrated launch and spacecraft maneuvering system, said method comprising the steps of:
- providing a support structure on which is supported a spacecraft, a propulsion system, a unitary control system, and an electrical power system;
- providing a spacecraft payload for performing on-orbit payload functions;
- launching the spacecraft payload and the spacecraft supported on the support structure into earth orbit using the propulsion system, the unitary control system, and the electrical power system provided in said providing step;
- and
- servicing, while on-orbit, the spacecraft payload and the spacecraft launched in said launching step with the same support structure, propulsion system, unitary control system, and electrical power system used in said launching step to launch the spacecraft payload and the spacecraft, wherein said servicing step enables the spacecraft payload to perform the on-orbit payload functions.
A single-stage-to-orbit integrated launch and spacecraft system comprising:
- a spacecraft payload including payload equipment;
- a main support structure including a payload support structure having a gimballed payload fairing, said payload support structure supporting said payload equipment, wherein said gimballed payload fairing protects said payload and said payload equipment from pressure, heat, and vibration at least during launch;
- a propulsion system supported by said main support structure;
- a control system supported by said main support structure;
- and
- an electrical power system supported by said main support structure.
Dependencies are inferred from the claim text.