Receptacle, payload assembly and related methods for an aircraft
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/14
B64F-005/10
B64C-007/00
출원번호
US-0499574
(2017-04-27)
등록번호
US-10183734
(2019-01-22)
발명자
/ 주소
Scimone, Michael J.
Vollmar, Richard
Simansky, Joel
Henke, Jason
출원인 / 주소
Georgian Aerospace LLC
대리인 / 주소
Armstrong Teasdale LLP
인용정보
피인용 횟수 :
0인용 특허 :
23
초록▼
An aircraft includes a support structure, an outer skin coupled to the support structure, and a port that defines a break in the support structure and extends through the outer skin. The aircraft also includes a receptacle coupled to portions of the support structure proximate the port, such that th
An aircraft includes a support structure, an outer skin coupled to the support structure, and a port that defines a break in the support structure and extends through the outer skin. The aircraft also includes a receptacle coupled to portions of the support structure proximate the port, such that the receptacle routes at least a portion of the load borne by the support structure around the break defined by the port. The receptacle includes an opening defined therein. The aircraft further includes a removable payload assembly coupled within the receptacle opening, and a pressure ring configured to form a seal between an inner surface of the receptacle and an outer surface of the payload assembly.
대표청구항▼
1. An aircraft comprising: a support structure;an outer skin coupled to the support structure;a port that defines a break in the support structure and extends through the outer skin;a receptacle attached to portions of the support structure proximate the port, such that the receptacle routes at leas
1. An aircraft comprising: a support structure;an outer skin coupled to the support structure;a port that defines a break in the support structure and extends through the outer skin;a receptacle attached to portions of the support structure proximate the port, such that the receptacle routes at least a portion of the load borne by the support structure around the break defined by the port, the receptacle comprising an opening defined therein;a removable payload assembly mounted within the receptacle opening, wherein the payload assembly comprises: an annular housing extending from a first end to a second end;a single-pane window positioned within the annular housing; anda retainer ring sized to be received through a window opening defined by the first end of the annular housing, wherein the retainer ring is fastened to the annular housing such that the window is secured within the annular housing; anda pressure ring forming a seal between an inner surface of the receptacle and an outer surface of the payload assembly. 2. The aircraft of claim 1, wherein the receptacle is coupled to at least one of: (i) a continuous stringer of a plurality of stringers of the support structure, and(ii) a continuous rib of a plurality of ribs of the support structure,wherein the at least one of the continuous stringer and the continuous rib extends past the port. 3. The aircraft of claim 1, further comprising: at least one interior member coupled to the receptacle, the at least one interior member aligned with, and fastened to, a corresponding at least one rail mounted exteriorly to the aircraft outer skin; anda door coupled to the at least one rail proximate the port for movement between a first position and a second position. 4. The aircraft of claim 1, wherein the receptacle comprises a housing shaped to be received in the port, the receptacle housing being integrally formed. 5. The aircraft of claim 1, wherein: the receptacle further comprises a plurality of circumferentially spaced receptacle flanges extending inwardly from an inner surface that defines the receptacle opening, andthe payload assembly further comprises a plurality of circumferentially spaced payload assembly flanges that extend outward from an outer surface of the annular housing, each payload assembly flange is receivable through a corresponding gap defined between a pair of the receptacle flanges when the payload assembly is in a first rotational orientation with respect to the receptacle, and each payload assembly flange aligns for coupling with a corresponding receptacle flange when the payload assembly is in a second rotational orientation with respect to the receptacle. 6. The aircraft of claim 5, wherein the payload assembly at least partially defines a pressure boundary between an interior of the aircraft and an external environment. 7. The aircraft of claim 1, further comprising an imaging device positioned adjacent to the single-pane window. 8. The aircraft of claim 1, wherein the single-pane window is at least partially transparent to electromagnetic radiation in at least one of an optical bandwidth and an infrared bandwidth. 9. The aircraft of claim 1, wherein: the payload assembly further comprises a plurality of circumferentially spaced payload assembly flanges that extend outward from an outer surface of the annular housing and are coupled to the receptacle, andthe window assembly is configured to position the window at an oblique angle relative to the payload assembly flanges. 10. A method of retrofitting an aircraft to accommodate a removable payload assembly, the aircraft including a support structure and an outer skin coupled thereto, the method comprising: removing a portion of the support structure adjacent a port such that a break in the support structure is defined, wherein the port extends through the outer skin;coupling a receptacle to portions of the support structure proximate the port, such that the receptacle routes at least a portion of the load borne by the support structure around the break defined by the port, the receptacle including an opening defined therein; andcoupling a removable payload assembly within the receptacle opening, wherein the payload assembly includes a window assembly. 11. The method of claim 10, further comprising coupling the receptacle to at least one of: (i) a continuous stringer of a plurality of stringers of the support structure, and(ii) a continuous rib of a plurality of ribs of the support structure,wherein the at least one of the continuous stringer and the continuous rib extends past the port. 12. The method of claim 10, further comprising: coupling at least one interior member to the receptacle, the at least one interior member aligned with, and fastened to, a corresponding at least one rail mounted exteriorly to the aircraft outer skin; andcoupling a door to the at least one rail proximate the port for movement between a first position and a second position. 13. The method of claim 10, wherein coupling the receptacle to the portions of the support structure comprises coupling an integrally formed housing of the receptacle to the portions of the support structure, the housing shaped to be received in the port. 14. The method of claim 10, wherein coupling the removable payload assembly within the receptacle opening comprises: positioning the payload assembly in a first rotational orientation with respect to the receptacle opening, such that each of a plurality of flanges of the payload assembly aligns with a corresponding gap defined between a pair of a plurality of flanges of the receptacle, wherein the receptacle flanges extend inwardly from an inner surface that defines the receptacle opening and the payload assembly flanges extend outward from an outer surface of the payload assembly;moving the payload assembly at least partially into the receptacle opening, such that the payload assembly flanges pass through the corresponding gaps;rotating the payload assembly to a second rotational orientation, such that each receptacle flange is aligned with a corresponding payload assembly flange; andcoupling each receptacle flange to the corresponding payload assembly flange to secure the payload assembly within the receptacle. 15. The method of claim 14, wherein coupling the removable payload assembly within the receptacle opening further comprises coupling the payload assembly such that the payload assembly at least partially defines a pressure boundary between an interior of the aircraft and an external environment. 16. The method of claim 10, further comprising positioning an imaging device adjacent to a window of the window assembly. 17. The method of claim 10, further comprising coupling the removable payload assembly that includes the window assembly comprising a single-pane window that is at least partially transparent to electromagnetic radiation in at least one of an optical bandwidth and an infrared bandwidth. 18. The method of claim 10, wherein the payload assembly further includes a plurality of circumferentially spaced payload assembly flanges that extend outward from an outer surface of the payload assembly, and wherein coupling the removable payload assembly within the receptacle opening comprises coupling the payload assembly flanges to the receptacle such that a window of the window assembly is positioned at an oblique angle relative to the payload assembly flanges. 19. A method of replacing a first removable payload assembly in a receptacle of an aircraft with a second removable payload assembly, the aircraft including a support structure, an outer skin coupled to the support structure, and a port extending through the outer skin, wherein the receptacle is coupled to portions of the support structure proximate the port, the method comprising: rotating the first payload assembly within the receptacle to a first rotational orientation with respect to the receptacle, such that each of a plurality of flanges of the first payload assembly aligns with a corresponding gap defined between a pair of a plurality of flanges of the receptacle, wherein the receptacle flanges extend inwardly from an inner surface that defines a receptacle opening and the first payload assembly flanges extend outward from an outer surface of the first payload assembly;removing the first payload assembly from the receptacle, such that the payload assembly flanges pass through the corresponding gaps;inserting the second payload assembly into the receptacle in the first rotational orientation; andcoupling each receptacle flange to a corresponding one of a plurality of payload assembly flanges of the second payload assembly to secure the second payload assembly within the receptacle. 20. The method of claim 19, further comprising coupling a pressure ring between the inner surface of the receptacle and the outer surface of the second payload assembly, the pressure ring configured to form a seal therebetween. 21. The method of claim 19, wherein the first payload assembly includes a window and the second payload assembly comprises a plate that plugs the receptacle opening.
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이 특허에 인용된 특허 (23)
Goto, Shingo; Sugimura, Toshiaki, Aircraft and method for mounting device to be installed outside aircraft onto airframe.
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