Reusable rocket-propelled high altitude airplane and method and apparatus for mid-air oxidizer transfer to said airplane

• US 6,119,985 A
• Filed: 03/07/1997
• Issued: 09/19/2000
• Est. Priority Date: 03/07/1997
• Status: Expired due to Fees

• Current Assignee: Rocketplane Limited Incorporated
• Original Assignee: Pioneer Rocketplane Corporation
• Inventors: Zubrin, Robert M., Clapp, Mitchell B.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US08/813,476
• Time in Patent Office: 1,292 Days
• Field of Search: 244/2, 244/160, 244/162, 244/172, 244/135 A, 244/135 R, 244/58, 244/59, 244/63, 244/73 R, 244/74, 244/53 B, 244/53 R, 244/62, 60/257, 60/259
• US Class Current: 244/171.4
• CPC Class Codes: B64C 39/02 characterised by special use
• CPC Class Codes: B64D 27/023 of rocket type, e.g. for assisting taking-off or braking
• CPC Class Codes: B64D 39/00 Refuelling during flight filling or emptying fuel tanks B64D37/14
• CPC Class Codes: B64G 1/005 Air launch
• CPC Class Codes: B64G 1/14 Space shuttles reusable launch rockets B64G1/006
• CPC Class Codes: B64G 1/401 Liquid propellant rocket engines Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: B64G 1/58 Thermal protection, e.g. heat shields
• CPC Class Codes: B64G 1/62 Systems for re-entry into the earth's atmosphere; Retarding or landing devices
• CPC Class Codes: F05B 2220/50 for auxiliary power units (APU's)
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A reusable rocket airplane which may be utilized to launch satellites and other payloads into space. The airplane may also be used for rapid surface to surface flight. The reusable rocket airplane may be safely supplied with oxidizer in mid-air, achieve an altitude outside the Earth'"'"'s atmosphere, and return safely to be used again. The rocket airplane utilizes unique concepts to secure its gas turbine engines for high speed flight, minimize fluid spillage during mid-air oxidizer transfer, as well as employs design features advantageous to the economical building and reuse of the rocket airplane.

Claims

1. A rocket propelled airplane, comprising:

a low pressure propellant tank in the wine or fuselage of said airplane, said propellant tank adapted to contain propellant therein;

a rocket engine including a reservoir of cold high pressure gas and a heat exchanger to warm the gas in order to pressurize the propellant tank, wherein said rocket engine is an airbreathing engine having one or more air inlets;

a pump to raise the propellant in the propellant tank from a low pressure to a higher pressure adapted for the use in the rocket engine; and

a turbine to apply energy from the warm high pressure gas to operate said pump, said turbine having an exhaust port which is vented to the propellant tank so that pressure in the propellant tank may be maintained as the propellant is withdrawn from the propellant tank.

2. The rocket propelled airplane of claim 1, wherein said gas is helium.

3. A rocket propelled airplane, comprising:

a low pressure propellant tank in the wing or fuselage of said airplane, said propellant tank adapted to contain propellant therein;

a rocket engine including a reservoir of cold high pressure gas and a heat exchanger to warm the gas in order to pressurize the propellant tank, said rocket engine being an airbreathing engine adapted to receive incoming air and having one or more air inlets;

a pump to raise the propellant in the propellant tank from a low pressure to a higher pressure adapted for the use in the rocket engine; and

a turbine to apply energy from the warm high pressure gas to operate said pump, said turbine having an exhaust port which is vented to the propellant tank so that pressure in the propellant tank may be maintained as the propellant is withdrawn from the propellant tank;

an inlet closure device coupled to said one or more air inlets, said inlet closure device having an open state and a closed state, said open state and said closed state both being independently smooth with respect to the incoming air.

4. The rocket propelled airplane of claim 3, wherein said gas is helium.

5. A rocket propelled airplane, comprising:

a low pressure propellant tank in the wing or fuselage of said airplane, said propellant tank adapted to contain propellant therein;

a rocket engine including a reservoir of cold high pressure gas and a heat exchanger to warm the gas in order to pressurize the propellant tank, wherein said gas is helium;

a pump to raise the propellant in the propellant tank from a low pressure to a higher pressure adapted for the use in the rocket engine; and

a turbine to apply energy of the warm high pressure gas to operate said pump, said turbine having an exhaust port which is vented to the propellant tank so that pressure in the propellant tank may be maintained as the propellant is withdrawn from the propellant tank.