System for the recovery, storage and utilisation of atmospheric gas for use as a vehicle propellant

Patent metadata

Field	Value
Publication number	US-10087887-B2
Application number	US-201113876547-A
Country	US
Kind code	B2
Filing date	Jul 27, 2011
Priority date	Sep 30, 2010
Publication date	Oct 2, 2018
Grant date	Oct 2, 2018

Abstract

A system for the recovery and management of atmospheric gas is disclosed, such as for use as a vehicle propellant in a vehicle propulsion system. The system can include a compressor configured to compress atmospheric gas and first and second storage tanks configured to store liquefied atmospheric gas from the compressor. The second storage tank can have a heater operable to heat liquefied atmospheric gas therein to convert it to a high pressure gas. The second storage tank includes an outlet duct fluidly coupled to the first storage tank for supplying high pressure gas to the first storage tank.

First claim

The invention claimed is:

1. A system for the recovery and management of atmospheric gas, comprising:
a compressor configured to draw in and compress atmospheric gas at least when the system is stationary; and
first and second storage tanks configured to store liquefied atmospheric gas from the compressor, each storage tank having an inlet duct for receiving a supply of liquefied atmospheric gas thereto, the inlet duct of the first storage tank being fluidly connected to the compressor, the second storage tank having a heater operable to heat and convert liquefied atmospheric gas therein to a high pressure gas, wherein the second storage tank includes an outlet duct fluidly coupled to the first storage tank for supplying high pressure gas to the first storage tank and, a control valve in said outlet duct, wherein the first storage tank includes an outlet duct for a flow of liquid out of the first storage tank under pressure provided by gas from the second storage tank.

2. A system according to claim 1 comprising:
a liquefaction heat exchanger disposed downstream of the at least one compressor to liquefy compressed atmospheric gas from the at least one compressor.

3. A system according to claim 1 , wherein the control valve in the outlet duct of the second storage tank comprises:
a Joule-Thomson control valve.

4. A system according to claim 1 , comprising:
a heat exchanger in the outlet duct of the second storage tank, downstream of the control valve.

5. A system according to claim 1 , wherein the heater of the second storage tank is an electrical heater.

6. A system according to claim 1 , wherein the heater of the second storage tank comprises:
a Radioisotope Heating Unit.

7. A system according to claim 1 , wherein the at least one compressor includes a plurality of compressors in series configured to draw in and compress atmospheric gas.

8. A system according to claim 7 , comprising:
three compressors.

9. A system according to claim 7 wherein at least one of the compressors is a rotary compressor, and at least one of the compressors is a piston compressor.

10. A system according to claim 1 , wherein the inlet ducts of the first and second storage tanks are independently controllable by respective supply valves.

11. A system according to claim 1 , wherein the exit duct of the first tank comprises:
a valve to control the flow of fluid out of the first tank.

12. A system according to claim 1 , comprising:
a third storage tank for storing liquefied atmospheric gas supplied from the at least one compressor, said third storage tank having an inlet duct for a supply of liquefied atmospheric gas thereto.

13. A system according to claim 12 , wherein the third storage tank comprises:
a heater operable to heat and convert liquefied atmospheric gas therein to a high pressure gas.

14. A system according to claim 13 , wherein the inlet duct of the third storage tank is independently controllable by a supply valve.

15. A system according to claim 12 , wherein the inlet duct of the second and/or third storage tank is fluidly connected to the at least one compressor.

16. A system according to claim 1 , wherein the inlet duct of the second and/or a third storage tank is fluidly coupled to an outlet duct from the first storage tank via a valve for controllably filling the second and/or third storage tank from the first storage tank.

17. A system according to claim 1 , wherein at least one of the storage tanks comprises:
an overpressure valve configured to open when pressure within the tank exceeds a predetermined value.

18. A propulsion system for a flying planetary surface exploration vehicle comprising:
a main thruster unit and a plurality of reaction control thrusters; and
a system for recovery and management of atmospheric gas according to claim 1 , wherein the outlet duct of the first storage tank is fluidly connected to the main thruster unit via a control valve to supply liquefied atmospheric gas from the first storage tank to the main thruster unit as a propellant fuel.

19. A propulsion system according to claim 18 , wherein the main thruster unit comprises:
an exhaust nozzle; and
a superheating unit configured to convert liquefied atmospheric gas supplied thereto to a superheated gas for discharge through the exhaust nozzle as a vehicle propellant to produce lifting thrust.

20. A propulsion system according to claim 19 , wherein the superheating unit comprises:
a thermal capacitor for transfer of heat to liquefied atmospheric gas supplied thereto; and
a heating means for heating the thermal capacitor.

21. A propulsion system according to claim 19 , wherein the reaction control thrusters are fluidly connected to the main thruster unit for supplying high pressure gas to the reaction control thrusters as a propellant.

22. A propulsion system according to claim 18 , wherein the reaction control thrusters are fluidly connected to the second storage tank or to a third storage tank for supplying high pressure gas to the reaction control thrusters as a propellant.

23. A propulsion system according to claim 18 , wherein an outlet duct of the first storage tank is fluidly coupled to a secondary superheating unit configured to convert liquefied atmospheric gas supplied thereto from the first storage tank, to a superheated gas, the secondary superheating unit being fluidly connected to the reaction control thrusters to supply high pressure gas to the reaction control thrusters as a propellant.

24. A propulsion system according to claim 18 , wherein at least one of the storage tanks comprises:
a liquid level sensor; and
a controller connected to said sensor, wherein the controller is configured to close the inlet supply valve of each storage tank when the liquid level sensor detects that the tank is filled to a pre-determined level with liquefied atmospheric gas.

25. A propulsion system according to claim 24 , wherein the controller is configured to control the compressor to stop when a level sensor detects that the liquid level in a storage tank has reached the pre-determined level.

26. A propulsion system according to claim 22 , wherein the second and/or the third storage tank comprises:
a temperature sensor and/or a pressure sensor, and the system comprises:
a controller connected to said sensor, wherein the controller is configured to control a heater of a respective storage tank in dependence on a sensed temperature and/or pressure detected by the sensor(s).

27. A propulsion system according to claim 18 , comprising:
one or more vehicle attitude sensors; and
a controller, connected to each attitude sensor and to the reaction control thrusters, configured to activate one or more or the reaction control thrusters in dependence on signals provided by each attitude sensor.

28. A propulsion system according to claim 27 wherein the controller is coupled to a control valve associated with each reaction control thruster and is configured to open a respective valve to allow high pressure gas to be discharged though the respective reaction control thruster in dependence on signals provided by each attitude sensor.

29. A flight-capable vehicle for planetary surface exploration including a propulsion system according to claim 18 .

30. A system according to claim 1 , wherein the inlet duct of the second

Assignees

• Reed Jaime Simon
• Airbus Defence & Space Ltd

Inventors

• Reed Jaime Simon

Classifications

• B64G1/401

  Liquid propellant rocket engines (Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415) · CPC title

• B64G1/40

  Arrangements or adaptations of propulsion systems · CPC title

• B64G1/10 Primary

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title

• B64G1/16

  Extraterrestrial cars · CPC title

• B64G2001/1071

  Operations & Transport · mapped topic