Systems and methods for temperature control

Patent metadata

Field	Value
Publication number	US-10967992-B2
Application number	US-201715654569-A
Country	US
Kind code	B2
Filing date	Jul 19, 2017
Priority date	Jul 19, 2017
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

Abstract

A temperature control system may include a heat exchanger configured to cool air within a pressurized enclosed crew cabin when the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger. The system may further include a sublimator configured to cool the coolant. The system may also include a primary coolant line configured to transport the coolant from the sublimator through the heat exchanger.

First claim

What is claimed is:

1. A temperature control system comprising:
a heat exchanger that cools air within a pressurized enclosed crew cabin as the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger;
a sublimator that cools the coolant; and
a primary coolant line that transports the coolant from the sublimator through the heat exchanger;
a secondary coolant line configured to transport coolant from the sublimator through the heat exchanger; and
at least three coolant pumps, wherein two of the at least three coolant pumps are configured to circulate coolant through the primary coolant line, and wherein one of the at least three coolant pumps is configured to circulate coolant through the secondary coolant line, and wherein each of the at least three coolant pumps are powered by separate power sources.

2. The system of claim 1 , further comprising:
at least one radiator configured to cool the coolant, wherein the sublimator is configured to cool the coolant during a first stage of flight, and wherein the at least one radiator is configured to cool the coolant during a second stage of flight.

3. The system of claim 2 , wherein the sublimator is positioned along the coolant line downstream from the heat exchanger and upstream from the at least one radiator.

4. The system of claim 2 , further comprising a radiator bypass valve to alter an amount of coolant circulated through at least one radiator and thereby control a temperature of the coolant passing through the heat exchanger.

5. The system of claim 2 , wherein the heat exchanger is located in a service module, wherein the pressurized enclosed crew cabin is located in a crew module, wherein the service module is separable from the crew module, and wherein the system further comprises a first leakage prevention valve and a second leakage prevention valve coupled to the primary coolant line and configured to prevent coolant leakage when the service module is separated from the crew module.

6. The system of claim 2 , wherein the at least one radiator is an outer mold line radiator positioned along an exterior of a service module and provides the service module with micrometeoroid and orbital debris protection, aero-thermal heating protection, acoustic protection, pressure load protection, or any combination thereof.

7. The system of claim 2 , wherein the at least one radiator is thermally isolated from a service module by a vacuum during flight.

8. The system of claim 1 , further comprising:
a ground-based heat exchanger configured to cool the coolant while the enclosed crew cabin is not in flight.

9. The system of claim 8 , wherein the ground-based heat exchanger cools the coolant by receiving flow of another coolant through the ground-based heat exchanger from a ground-based connection to a ground-based coolant line.

10. The system of claim 8 , wherein the ground-based heat exchanger is located within an annulus adjacent to the pressurized enclosed crew cabin.

11. The system of claim 1 , further comprising a heat exchanger bypass valve to bypass at least a portion of the coolant from passing through the heat exchanger and thereby enable control of a temperature within the enclosed crew cabin.

12. The system of claim 1 , wherein the coolant is non-toxic.

13. The system of claim 1 , further comprising a fill port to provide access to the sublimator during flight for filling the sublimator with water.

14. The system of claim 1 , wherein the primary coolant line is insulated with a moisture absorbent foam.

15. A method for temperature control comprising:
providing a temperature control system comprising:
a heat exchanger that cools air within a pressurized enclosed crew cabin as the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger;
a sublimator that cools the coolant;
a primary coolant line that transports the coolant from the sublimator through the heat exchanger;
a secondary coolant line configured to transport coolant from the sublimator through the heat exchanger; and
at least three coolant pumps, wherein two of the at least three coolant pumps are configured to circulate coolant through the primary coolant line, and wherein one of the at least three coolant pumps is configured to circulate coolant through the secondary coolant line;

circulating coolant through the sublimator to cool the coolant;
transporting the coolant from the sublimator to the heat exchanger through the primary coolant line; and
cooling air within the pressurized enclosed crew cabin by circulating air across the heat exchanger while circulating the coolant through the heat exchanger.

16. The method of claim 15 , further comprising:
circulating the coolant through at least one radiator to cool the coolant.

17. The method of claim 15 , further comprising:
directing a portion of the coolant to bypass the heat exchanger and thereby enable control of a temperature within the enclosed crew cabin.

18. A method for temperature control comprising:
cooling air within a pressurized enclosed crew cabin by circulating the air across a heat exchanger while circulating coolant through the heat exchanger;
while the pressurized enclosed crew cabin is not in flight:
circulating the coolant through a ground-based heat exchanger, wherein the ground-based heat exchanger cools the coolant by receiving flow of another coolant from a ground-based connection to a ground-based coolant line;
during a first stage of flight:
circulating the coolant through a sublimator to cool the coolant; and
during a second stage of flight:
circulating the coolant through at least one radiator to cool the coolant.

19. The method of claim 18 , further comprising:
transporting the coolant from the sublimator to the heat exchanger through a primary coolant line using at least a first coolant pump and a second coolant pump; and
transporting the coolant from the sublimator to the heat exchanger through a secondary coolant line using at least a third coolant pump.

20. The method of claim 19 , wherein each of the first coolant pump, the second coolant pump, and the third coolant pump are powered by separate power sources.

Assignees

• Boeing Co

Inventors

• Fuller Michael James
• Leonard Daniel J
• Lauger John B
• Dunaway Brian R
• Gray John Charles

Classifications

• B64G1/46 Primary

  Arrangements or adaptations of devices for control of environment or living conditions · CPC title

• B64G1/60

  Crew or passenger accommodations · CPC title

• F25D17/00

  Arrangements for circulating cooling fluids; Arrangements for circulating gas, e.g. air, within refrigerated spaces · CPC title

• F25D3/12

  using solidified gases, e.g. carbon-dioxide snow · CPC title

• B64G1/58

  Thermal protection, e.g. heat shields · CPC title