IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0305573
(2011-11-28)
|
등록번호 |
US-9016629
(2015-04-28)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
4 |
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 wherein the retainer system comprises: an inner retainer configured to receive a first seal of the seal system and the pressure and thermal window pane, the first seal contacting the inner retainer and a first surface of the pressure and thermal window pane, the inner retainer and the first surface of the pressure and thermal window pane within a pressurized interior of the space vehicle; andan outer retainer connected to the inner retainer such that the pressure and thermal window pane and the seal system are held in place by the outer retainer and the inner retainer such that the pressure and thermal window pane remains sealed, and wherein the seal system comprises: the first seal; anda second seal contacting the outer retainer and a second surface of the pressure and thermal window pane. 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. The window system of claim 1, wherein the outer retainer is a first outer retainer, the inner retainer is a first inner retainer: wherein the seal system contacts the primary thermal window pane to seal the primary thermal window pane; and further comprising:a second outer retainer configured to receive a third seal of the seal system and the primary thermal window pane, the third seal contacting the second outer retainer and a first surface of the primary thermal window pane, the first surface of the primary thermal window pane exposed to an environment outside of the space vehicle;a second inner retainer connected with the second outer retainer such that the primary thermal window pane and the seal system are held in place by the second outer retainer and the second inner retainer such that the primary thermal window pane remains sealed;the third seal; anda fourth seal contacting the second inner retainer and a second surface of the primary thermal window pane. 7. The window system of claim 6, wherein the pressure and thermal window pane is substantially aligned with an inner structure of the space vehicle. 8. The window system of claim 7, wherein the primary thermal window pane is substantially aligned with an outer structure forming a skin of the space vehicle. 9. The window system of claim 8, further comprising a barrier positioned between the first outer retainer and the second inner retainer; the barrier, the pressure and thermal window pane, the primary thermal window pane, the first outer retainer, and the second inner retainer forming a cavity, wherein the barrier has an increasing circumference moving from the first outer retainer to the second inner retainer. 10. 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, wherein the retainer system comprises an inner retainer configured to receive a first seal of the seal system and the pressure and thermal window pane, the first seal contacting the inner retainer and a first surface of the pressure and thermal window pane, the inner retainer and the first surface of the pressure and thermal window pane within a pressurized interior of the space vehicle; and an outer retainer connected to the inner retainer such that the pressure and thermal window pane and the seal system are held in place by the outer retainer and the inner retainer such that the pressure and thermal window pane remains sealed, and wherein the seal system comprises: the first seal; anda second seal contacting the outer retainer and a second surface of 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 space vehicle is operating. 11. The method of claim 10, wherein the seal system comprises at least one of a number of pressure seals and a number of thermal seals. 12. The method of claim 10, wherein the seal system is configured to reduce leaks when a pressure is present. 13. The method of claim 10, wherein the window system further comprises a thermal protection system configured to cover the outer retainer. 14. The method of claim 10, wherein the outer retainer is a first outer retainer and the inner retainer is a first inner retainer and wherein the seal system contacts the primary thermal window pane to seal the primary thermal window pane; and wherein the window system further comprises: a second outer retainer configured to receive a third seal of the seal system and the primary thermal window pane, the third seal contacting the second outer retainer and a first surface of the primary thermal window pane, the third surface of the primary thermal window pane exposed to an environment outside of the space vehicle;a second inner retainer connected with the second outer retainer such that the thermal window pane and the seal system are held in place by the second outer retainer and the second inner retainer such that the primary thermal window pane remains sealed;the third seal; anda fourth seal contacting the second inner retainer and a second surface of the primary thermal window pane. 15. The method of claim 14, wherein the pressure and thermal window pane is substantially aligned with an inner structure of the space vehicle. 16. The method of claim 15, 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. 17. The method of claim 16, further comprising a barrier positioned between the first outer retainer and the second inner retainer; the barrier, the pressure and thermal window pane, the primary thermal window pane, the first outer retainer, and the second inner retainer forming a cavity, and 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. The method of claim 10, 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. 19. The method of claim 10, 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. 20. 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, the first retainer system comprising: a first inner retainer sealed to the inner surface of the pressure and thermal window pane by a first seal; anda first outer retainer sealed to an outer surface of the pressure and thermal window pane by a second seal pane, the first outer retainer connected to the first inner retainer such that the pressure and thermal window pane, the first seal, and the second seal are held in place by the first outer retainer and the first inner retainer such that pressure and thermal window pane remains sealed; anda second retainer system holding the primary thermal window pane in place, the retainer system comprising: a second outer retainer sealed to the outer surface of the primary thermal window pane by a third seal; anda second inner retainer sealed to an inner surface of the primary thermal window pane by a fourth seal, the second inner retainer connected to the second outer retainer such that the primary thermal window pane, the third seal, and the fourth seal are held in place by the second outer retainer and the second inner retainer such that the primary thermal window pane remains sealed. 21. 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, the first retainer system comprising: a first inner retainer sealed to the inner surface of the pressure and thermal window pane by a first seal, and a first outer retainer sealed to an outer surface of the pressure and thermal window pane by a second seal pane, the first outer retainer connected to the first inner retainer such that the pressure and thermal window pane, the first seal, and the second seal are held in place by the first outer retainer and the first inner retainer such that pressure and thermal window pane remains sealed; and a second retainer system holding the primary thermal window pane in place, the retainer system comprising: a second outer retainer sealed to the outer surface of the primary thermal window pane by a third seal, and a second inner retainer sealed to an inner surface of the primary thermal window pane by a fourth seal, the second inner retainer connected to the second outer retainer such that the primary thermal window pane, the third seal, and the fourth seal are held in place by the second outer retainer and the second inner retainer such that the primary thermal window pane remains sealed; andexposing the window system to at least one of a re-entry environment and a launch environment while the spacecraft is operating.
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