IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0978916
(2010-12-27)
|
등록번호 |
US-8814081
(2014-08-26)
|
발명자
/ 주소 |
- Gagne, Steve
- Arvin, John R.
|
출원인 / 주소 |
- Rolls-Royce North American Technologies, Inc.
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
7 |
초록
▼
One embodiment of the present invention is a unique aircraft. Another embodiment is a unique external pod for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and external pods for aircraft. Further embodiments, forms, features, a
One embodiment of the present invention is a unique aircraft. Another embodiment is a unique external pod for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and external pods for aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
대표청구항
▼
1. An external pod for an aircraft, comprising: a body having a thermodynamic system component, wherein the body is shaped like a fuel pod that is configured to be attached to the aircraft and to supply extra fuel to the aircraft;an attachment feature coupled to the body and configured to be attache
1. An external pod for an aircraft, comprising: a body having a thermodynamic system component, wherein the body is shaped like a fuel pod that is configured to be attached to the aircraft and to supply extra fuel to the aircraft;an attachment feature coupled to the body and configured to be attached to the aircraft and to permit deliveries between the thermodynamic system component and the aircraft; anda nose cone configured to selectively open and close during flight, wherein when the nose cone is in the open position during flight, ram air passes through the nose cone to an interior portion of the body and wherein when the nose cone is in the closed position during flight, ram air is prevented from passing through the nose cone into the interior portion of the body. 2. The external pod of claim 1, wherein the external pod is not configured to carry auxiliary fuel for a primary propulsion engine of the aircraft. 3. The external pod of claim 1, further comprising an actuation system configured to selectively open and close the nose cone. 4. The external pod of claim 1, further comprising a diffuser configured to diffuse the ram air entering the interior portion of body when the nose cone is in the open position. 5. The external pod of claim 4, wherein when the nose cone is in the closed position during flight: at least a portion of the nose cone is retracted into the body exposing the diffuser to the ram air passing through the nose cone; or at least a portion of the nose cone is retracted over an external aerodynamic surface of the body to expose the diffuser to the ram air passing through the nose cone; or a first portion of the nose cone is retracted into the body and a second portion of the nose cone is retracted over the external aerodynamic surface of the body to expose the diffuser to the ram air passing through the retracted nose cone. 6. The external pod of claim 1, wherein the attachment feature is configured to attach to a wing of the aircraft. 7. The external pod of claim 1, wherein the thermodynamic system component is a turbine. 8. The external pod of claim 7, wherein the body further includes a generator and wherein the generator is at least partially powered by the turbine during flight. 9. The external pod of claim 7, wherein the body further includes a refrigerant compressor and wherein the refrigerant compressor is at least partially powered by the turbine during flight. 10. The external pod of claim 1, wherein the thermodynamic system component is a refrigerant condenser. 11. The external pod of claim 1, wherein the thermodynamic system component is a gas turbine engine. 12. The external pod of claim 1, wherein the nose cone is formed of a plurality of segments configured to separate from each other to form an opening configured to receive the ram air into the interior portion of the body in the open position, and configured to cooperatively engage each other to prevent the entry of the ram air into the interior portion of the body. 13. An aircraft, comprising: a fuselage;a wing coupled to the fuselage;an empennage coupled to at least one of the fuselage and the wing;a propulsion engine coupled to the aircraft; andan external pod coupled to the aircraft, wherein the external pod includes a body having a thermodynamic system component; and an attachment feature coupled to the body and configured to be attached to the aircraft and to permit deliveries between the thermodynamic system component and the aircraft; anda nose cone configured to selectively open and close during flight, wherein when the nose cone is in the open position during flight, ram air passes through the nose cone to an interior portion of the body and wherein when the nose cone is in the closed position during flight, ram air is prevented from passing through the nose cone into the interior of the body. 14. The aircraft of claim 13, wherein the external pod is not configured to carry auxiliary fuel for the propulsion engine of the aircraft. 15. The aircraft of claim 13, further comprising a an actuation system configured to selectively open and close the nose cone. 16. The aircraft of claim 15, further comprising a diffuser configured to diffuse the ram air entering the interior portion of body when the nose cone is in the open position. 17. The aircraft of claim 13, wherein the thermodynamic system component is at least one of a refrigerant condenser and a turbine. 18. The aircraft of claim 17, wherein the body further includes a generator and wherein at least one of the generator and the refrigerant compressor is at least partially powered by the turbine during flight. 19. The aircraft of claim 13, wherein the body further includes a gas turbine engine. 20. The external pod of claim 13, wherein the nose cone is formed of a plurality of segments configured to separate from each other, wherein the segments retract into the interior of the body to place the nose cone in the open position; or wherein the segments retract over an exterior surface of the body to place the nose cone in the open position; or wherein some of the segments retract into the interior of the body and some of the segments retract over the exterior surface of the body to place the nose cone in the open position. 21. An aircraft, comprising: a fuselage;a wing coupled to the fuselage;an empennage coupled to at least one of the fuselage and the wing;a propulsion engine coupled to the aircraft; andmeans for housing a thermodynamic system component and for permitting deliveries between the thermodynamic system component and the aircraft,wherein the means for housing is shaped like a fuel pod that is configured to be attached to the aircraft and to supply extra fuel to the aircraft; anda nose cone configured to selectively open and close during flight, wherein when the nose cone is in the open position during flight, ram air passes through the nose cone to an interior portion of the body and wherein when the nose cone is in the closed position during flight, ram air is prevented from passing through the nose cone into the interior portion of the body. 22. The aircraft of claim 21, wherein the means for housing is configured to house a gas turbine engine. 23. The external pod of claim 21, wherein the nose cone is formed of a plurality of segments configured to separate from each other, wherein the segments retract into the interior of the body to place the nose cone in the open position; or wherein the segments retract over an exterior surface of the body to place the nose cone in the open position; or wherein some of the segments retract into the interior of the body and some of the segments retract over the exterior surface of the body to place the nose cone in the open position.
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