[특허]Multiple stage tractor propulsion vehicle

THE BOEING COMPANY

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Multiple stage tractor propulsion vehicle

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/40 B64G-001/00
출원번호	US-0562637 (2012-07-31)
등록번호	US-9114892 (2015-08-25)
발명자 / 주소	Ball, James M. Kutzmann, Aaron J. Deamer, David A.
출원인 / 주소	THE BOEING COMPANY
대리인 / 주소	Parsons Behle & Latimer
인용정보	피인용 횟수 : 0 인용 특허 : 18

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A multiple stage orbital delivery vehicle that uses tractor propulsion to launch the vehicle into space. Only the upper stage of the vehicle includes an engine and avionics allowing the lower stages to be only liquid propellant tanks that may be dumped when empty. The liquid propellant may be either monopropellant or bi-propellant. The upper stage may include multiple nozzles that burn the propellant. Alternatively, the upper stage may include an aerospike engine instead of nozzles. The multiple stage orbital delivery vehicle may be air launched from an ...

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1. A multiple stage orbital delivery vehicle comprising: a first stage releasably connected to the orbital delivery vehicle, the first stage comprising a first fuel tank and a first fuel system; anda second stage comprising a second fuel tank and a second fuel system,the second stage further comprising one or more engines in fluid communication with the first and second fuel systems, wherein the one or more engines use fuel from the first fuel tank or the second fuel tank, wherein the first stage is positioned coaxially with the second stage and positioned below the second stage. 2. The multiple stage orbital delivery vehicle of claim 1, wherein only a single stage of the multiple stage orbital delivery vehicle includes an engine. 3. The multiple stage orbital delivery vehicle of claim 1, the second stage further comprising a payload bay that may be selectively opened. 4. The multiple stage orbital delivery vehicle of claim 3 further comprising a spacecraft positioned in the payload bay. 5. The multiple stage orbital delivery vehicle of claim 1, wherein the first fuel tank and the second fuel tank are adapted to contain a liquid propellant. 6. The multiple stage orbital delivery vehicle of claim 5, wherein the liquid propellant comprises a monopropellant. 7. The multiple stage orbital delivery vehicle of claim 5, wherein the liquid propellant comprises a bi-propellant. 8. The multiple stage orbital delivery vehicle of claim 1, the second fuel system further comprising a valve to prevent leakage of fuel upon the disconnection of the first stage. 9. The multiple stage orbital delivery vehicle of claim 1, wherein the one or more engines comprise at least three engines, each engine having a nozzle, and wherein the nozzles are laterally spaced around an exterior of the second stage. 10. The multiple stage orbital delivery vehicle of claim 1, further comprising a guidance, navigation, and control system configured to control the operation of the one or more engines. 11. The multiple stage orbital delivery vehicle of claim 1, wherein the one or more engines comprise an aerospike engine including an annular combustion chamber, throat, and nozzle, the nozzle being located laterally around an exterior of the second stage. 12. The multiple stage orbital delivery vehicle of claim 11, wherein the nozzle includes multiple septums dividing the nozzle into multiple sections. 13. The multiple stage orbital delivery vehicle of claim 1 further comprising a third stage releasably connected to the orbital delivery vehicle below the first stage, the third stage comprising a third fuel tank and a third fuel system, wherein the one or more engines use fuel from first fuel tank, the second fuel tank, or the third fuel tank, and wherein the first stage is positioned between the third stage and the second stage. 14. The multiple stage orbital delivery vehicle of claim 1 further comprising: a first oxidizer tank and a first oxidizer system in the first stage; anda second oxidizer tank and a second oxidizer system in the second stagewherein the one or more engines use a combination of fuel and oxidizer from the first fuel tank and the first oxidizer tank or from the second fuel tank and the second oxidizer tank. 15. The multiple stage orbital delivery vehicle of claim 1, wherein the first stage comprises an upper end and a lower end and wherein the upper and lower ends are located beneath the one or more engines of the second stage. 16. A multiple stage orbital delivery vehicle comprising: a first lower stage comprising a first fuel tank and a first fuel system;a second upper stage comprising a second fuel tank and a second fuel system;one or more engines connected to the second upper stage in fluid communication with the first fuel tank and second fuel tank, the one or more engines adapted to be shared by the first stage and the second stage, wherein the first lower stage is coaxial with the second upper stage. 17. The multiple stage orbital delivery vehicle of claim 16 further comprising a third stage comprising a third fuel tank and a third fuel system, wherein the third stage is adapted to share one or more engines with the first stage or the second stage, and wherein the first lower stage is positioned between the second upper stage and the third stage. 18. The multiple stage orbital delivery vehicle of claim 16, wherein the first lower stage has an upper end and a lower end and wherein the upper and lower ends are located beneath the one or more engines connected to the second upper stage.

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Multiple stage tractor propulsion vehicle

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Multiple stage tractor propulsion vehicle

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