Combined pressure and thermal window system for space vehicles
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/14
B64G-001/58
B64G-001/52
B64G-001/66
B64G-001/12
B64G-001/62
출원번호
US-0692744
(2015-04-22)
등록번호
US-9567114
(2017-02-14)
발명자
/ 주소
Svartstrom, Kirk Nils
출원인 / 주소
THE BOEING COMPANY
대리인 / 주소
Yee & Associates, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
A window system for a vehicle comprising a pressure and thermal window pane, a seal system, and a retainer system. The pressure and thermal window pane may be configured to provide desired pressure protection and desired thermal protection when exposed to an environment around the vehicle during ope
A window system for a vehicle comprising a pressure and thermal window pane, a seal system, and a retainer system. The pressure and thermal window pane may be configured to provide desired pressure protection and desired thermal protection when exposed to an environment around the vehicle during operation of the vehicle. The pressure and thermal window pane may have a desired ductility. The seal system may be configured to contact the pressure and thermal window pane to seal the pressure and thermal window pane. The retainer system may be configured to hold the seal system and the pressure and thermal window pane.
대표청구항▼
1. A window system for a space vehicle, the window system comprising: a sum total of two window panes, the two window panes comprising: a primary thermal window pane, the primary thermal window pane providing desired thermal protection for the space vehicle during at least one of re-entry and launch
1. A window system for a space vehicle, the window system comprising: a sum total of two window panes, the two window panes comprising: a primary thermal window pane, the primary thermal window pane providing desired thermal protection for the space vehicle during at least one of re-entry and launch; anda pressure and thermal window pane providing desired pressure protection and desired thermal protection for the space vehicle during operation of the space vehicle, the operation including at least one of re-entry and launch, in which the pressure and thermal window pane has a desired ductility;a seal system contacting the two window panes to seal the primary thermal window pane and the pressure and thermal window pane; anda retainer system holding the seal system and the two window panes. 2. The window system of claim 1, wherein the seal system comprises at least one of a number of pressure seals and a number of thermal seals. 3. The window system of claim 1, wherein the pressure and thermal window pane is comprised of a number of materials selected such that the pressure and thermal window pane has a desired structural performance such that the pressure and thermal window pane acts as a pressure barrier and a desired optical performance such that an occupant of the space vehicle may obtain information about an environment outside of the space vehicle through the pressure and thermal window pane. 4. The window system of claim 1, wherein the pressure and thermal window pane is comprised of a number of materials including at least one of a thermal plastic polymer, a polycarbonate, polymethyl methacrylate, a transparent composite material, and acrylic. 5. The window system of claim 3, wherein the desired structural performance includes the desired ductility, a desired strength, and a desired thermal resistance, wherein the desired ductility is a ductility similar to the ductility of a metal, wherein the desired strength is a strength capable of supporting loads similar to loads that may be supported by metals or metal alloys, wherein the desired thermal resistance provides a desired level of resistance to temperatures encountered during re-entry and launch, and wherein the desired optical performance includes a desired level of visibility. 6. A method for operating a space vehicle, the method comprising: operating the space vehicle having a window system comprising a sum total of two window panes, the two window panes comprising a primary thermal window pane, the primary thermal window pane providing desired thermal protection for the space vehicle during at least one of re-entry and launch and a pressure and thermal window pane which provides desired pressure protection and desired thermal protection for the space vehicle during operation of the space vehicle, the operation including at least one of re-entry and launch, in which the pressure and thermal window pane has a desired ductility; a seal system contacting the two window panes to seal the primary thermal window pane and the pressure and thermal window pane; and a retainer system holding the seal system and the two window panes; andexposing the window system to at least one of a re-entry environment and a launch environment while the space vehicle is operating. 7. The method of claim 6, wherein the seal system comprises at least one of a number of pressure seals and a number of thermal seals. 8. The method of claim 6, wherein the window system further comprises a thermal protection system configured to cover an outer retainer of the retainer system. 9. The method of claim 6, wherein the pressure and thermal window pane is comprised of a number of materials selected such that the pressure and thermal window pane has a desired structural performance that includes the desired ductility such that the pressure and thermal window pane acts as a pressure barrier and a desired optical performance such that an occupant of the space vehicle may obtain information about the environment outside of the space vehicle through the pressure and thermal window pane. 10. The method of claim 6, wherein the pressure and thermal window pane is comprised of a number of materials including at least one of a thermal plastic polymer, a polycarbonate, polymethyl methacrylate, a transparent composite material, and acrylic. 11. The window system of claim 1, wherein the pressure and thermal window pane is substantially aligned with an inner structure of the space vehicle. 12. The window system of claim 11, wherein the primary thermal window pane is substantially aligned with an outer structure forming a skin of the space vehicle. 13. The window system of claim 1, further comprising a barrier positioned between the pressure and thermal window pane and the primary thermal window pane, the forming a cavity, wherein the barrier is a thermal barrier providing protection against loss of heat between the primary thermal window pane and the pressure and thermal window pane. 14. The method of claim 6, wherein the pressure and thermal window pane is substantially aligned with an inner structure of the space vehicle. 15. The method of claim 14, wherein the primary thermal window pane is substantially aligned with an outer structure forming a skin of the space vehicle, and wherein the primary thermal window pane is an outermost pane of the window system and the thermal and pressure window pane is an innermost pane of the window system. 16. The method of claim 15, further comprising a barrier positioned between the pressure and thermal window pane and the primary thermal window pane forming a cavity, wherein the barrier is a thermal barrier that provides protection against loss of heat between the primary thermal window pane and the pressure and thermal window pane. 17. A window system for a spacecraft comprising: a sum total of two window panes, the two window panes comprising: a pressure and thermal window pane comprised of a number of materials including at least one of a thermal plastic polymer, a polycarbonate, polymethyl methacrylate, a transparent composite, and acrylic, the pressure and thermal window pane having an inner surface within a pressurized interior of the spacecraft; anda primary thermal window pane having an outer surface exposed to an environment outside of the spacecraft;a first retainer system holding the pressure and thermal window pane in place;a second retainer system holding the primary thermal window pane in place; anda barrier positioned between the first retainer system and the second retainer system, wherein the barrier is a thermal barrier that provides protection against loss of heat between the primary thermal window pane and the pressure and thermal window pane. 18. A method for operating a spacecraft, the method comprising: operating the spacecraft having a window system comprising a sum total of two window panes, the two window panes comprising a primary thermal window pane having an outer surface exposed to an environment outside of the spacecraft and a pressure and thermal window pane comprised of a number of materials including at least one of a thermal plastic polymer, a polycarbonate, polymethyl methacrylate, a transparent composite, and acrylic, the pressure and thermal window pane having an inner surface within a pressurized interior of the spacecraft; a first retainer system holding the pressure and thermal window pane in place; a second retainer system holding the primary thermal window pane in place; and a barrier positioned between the first retainer system and the second retainer system, wherein the barrier is a thermal barrier that provides protection against loss of heat between the primary thermal window pane and the pressure and thermal window pane; andexposing the window system to at least one of a re-entry environment and a launch environment while the spacecraft is operating. 19. The window system of claim 13, wherein the barrier has an increasing circumference moving from the pressure and thermal window pane to the primary thermal window pane. 20. The window system of claim 1 further comprising: a thermal protection system configured to cover an outer retainer of the retainer system. 21. The window system of claim 17, wherein the barrier has an increasing circumference moving from the pressure and thermal window pane to the primary thermal window pane. 22. The window system of claim 17 further comprising: a thermal protection system configured to cover an outer retainer of the second retainer system.
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이 특허에 인용된 특허 (7)
Svartstrom, Kirk Nils, Combined pressure and thermal window system for space vehicles.
Tockstein, Michael A.; Nokes, James P.; Osborn, Jon V.; Patel, Dhruv N.; Hopkins, Alan R.; Williams, John S.; Harper, Gary N., Radio frequency transparent thermal window.
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