U.S. patents available from 1976 to present.
U.S. patent applications available from 2005 to present.

Launch vehicle with reconfigurable interstage propellant manifolding and solid rocket boosters

Patent 5143328 Issued on September 1, 1992. Estimated Expiration Date: Icon_subject January 30, 2010. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.

Patent References

2755046

3369771

3782400

Liquid fuel multistage rocket
Patent #: 3934512
Issued on: 01/27/1976
Inventor: Adachi

Orientation system for a spin stabilized spacecraft
Patent #: 3977633
Issued on: 08/31/1976
Inventor: Keigler ,   et al.

Supplemental oil system for engines
Patent #: 4012012
Issued on: 03/15/1977
Inventor: Ligler

Pressure resistant member
Patent #: 4104878
Issued on: 08/08/1978
Inventor: Chase

Three stage rocket vehicle with parallel staging
Patent #: 4451017
Issued on: 05/29/1984
Inventor: Marshall

Heat management system for aircraft
Patent #: 4505124
Issued on: 03/19/1985
Inventor: Mayer

Automatic/manual fuel tank supply balance system
Patent #: 4591115
Issued on: 05/27/1986
Inventor: DeCarlo

More ...

Inventor

Application

No. 472096 filed on 01/30/1990

Examiners

Primary: Basinger, Sherman D.
Assistant: Bidwell, Anne E.

Attorney, Agent or Firm

Foreign Patent References

  • 2623774 FR. 06/13/1989

International Classes

B64G 001/00
B64G 001/40

Abstract

A launch vehicle having one or more high thrust solid propellant boosters and two or more liquid propellant stages all configured to burn in parallel and having an interstage propellant manifolding system between the parallel liquid burning stages. Preferably, existing U.S. launch vehicle stages may be employed as the parallel burning stages. An additional liquid stage burning in series with the lower stages may also be employed. The interstage propellant manifolding between the liquid burning stages allows the central vehicle core to be stabilized against high altitude wind loads and further provides increased performance to the launch vehicle. Additionally, the interstage propellant transfer manifold is equipped with a plurality of electromechanical valves to allow reconfiguration of the propellant flow in real time in the event of a stage failure, thereby providing significantly increased vehicle reliability.

Other References

  • Flight Performance Handbook for Powered flight Operations (Revised 1963) Ed. J. Frederick White, pp. 5-80 through 5-85
  • "Predicting Launch Vehicle Failure" Aerospace America, Sep. 1989, pp. 36-46
  • Titan Background Literature
  • Delta Background Literature
  • Atlas Background Literatur
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