Collapsible wing and unmanned aircraft system including collapsible wing
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-003/56
B64C-003/54
출원번호
US-0463516
(2012-05-03)
등록번호
US-9010693
(2015-04-21)
발명자
/ 주소
Barbieri, James Emmett Dee
출원인 / 주소
Barbieri, James Emmett Dee
대리인 / 주소
Polsinelli PC
인용정보
피인용 횟수 :
2인용 특허 :
2
초록
A collapsible wing, methods of producing the collapsible wing, and an unmanned aircraft system that includes the collapsible wing are provided.
대표청구항▼
1. A collapsible wing for an unmanned aircraft system, comprising at least two strutless monocoque composite wing span sections, each comprising a first inner wing span section and an outer wing span section, wherein the first inner wing span section nests within the outer wing span section in a col
1. A collapsible wing for an unmanned aircraft system, comprising at least two strutless monocoque composite wing span sections, each comprising a first inner wing span section and an outer wing span section, wherein the first inner wing span section nests within the outer wing span section in a collapsed configuration. 2. The collapsible wing of claim 1, wherein the collapsible wing further comprises at least one locking mechanism, and wherein the collapsible wing is deployed into an extended configuration by removing the first inner wing span section from a nested position within the outer wing span section until the at least one locking mechanism reversibly engages to secure the wing span section in a fixed relationship. 3. The collapsible wing of claim 2, wherein the fixed relationship comprises a first protruding end of the first inner wing span section protruding from an open end of the outer wing span section in a spanwise direction. 4. The collapsible wing of claim 3, wherein the at least two wing span sections further incorporate one or more mechanical limits to prevent the separation of the at least two wing span sections during deployment to the extended configuration. 5. The collapsible wing of claim 4, wherein the at least one locking mechanism additionally functions as the one or more mechanical limits. 6. The collapsible wing of claim 5, wherein the one or more mechanical limits comprise a first flange situated at a first non-protruding end opposite to the first protruding end of the first inner wing span section and a second flange situated at the open end of the outer wing span section, and wherein the first flange and the second flange interlock when the first inner wing span section is deployed to a maximum extended position consistent with the extended configuration. 7. The collapsible wing of claim 6, wherein the least one locking mechanism comprises a first locking element situated at the first non-protruding end of the first inner wing span section and a second locking element situated at the open end of the outer wing span, wherein the first locking element and the second locking element are selected from: frictional linings, magnets, tabs and receptacles, spring-loaded ball bearings and slot receptacles, and any combination thereof. 8. The collapsible wing of claim 3, wherein the at least two wing span sections further comprise a second inner wing span section, wherein the first inner wing span section and the second inner wing span section nest within the outer wing span section in the collapsed configuration. 9. The collapsible wing of claim 8, wherein the collapsible wing is deployed into the extended configuration by moving the first inner wing span section from its nested position within the outer wing span section and by moving the second inner wing span section from its nested position within the outer wing span section in opposite spanwise directions until the at least one locking mechanism reversibly engages to secure the at least two wing span sections in a second fixed relationship. 10. The collapsible wing of claim 9, wherein the second fixed relationship comprises the first protruding end of the first inner wing span section protruding from the open end of the outer wing span section in a spanwise direction and the second protruding end of the second inner wing span section protruding from a second open end of the outer wing span section opposite to the first open end. 11. The collapsible wing of claim 3, wherein the at least two wing span sections further comprise at least one additional wing span section, wherein the at least one additional wing span section nests within the first inner wing span section in the collapsed configuration. 12. The collapsible wing of claim 11, wherein the first protruding end further comprises a first open end, and wherein the fixed relationship of the extended configuration further comprises an intermediate protruding end protruding from the first open end in the spanwise direction. 13. A collapsible wing for an unmanned aircraft system, comprising at least two nested strutless monocoque composite wing span sections comprising a wing tip section, wherein: each wing span section protrudes in an outboard direction from a spanwise lumen within a corresponding adjacent wing span section situated inboard of the wing span section, ending at the wing tip section situated at a most outboard position in an extended configuration of the wing;each wing span section nests within the spanwise lumen within the corresponding adjacent wing span section situated inboard of the wing span section in a collapsed position;the wing is changed from the collapsed configuration to the extended configuration by deploying the wing tip section in an outboard direction, causing each wing span section to translate outboard relative to each adjacent wing span section; andthe wing is changed from the extended position to the collapsed position by moving the wing tip section in an inboard direction, causing each wing span section to translate inboard into the lumen of each corresponding adjacent wing span section. 14. A collapsible wing for an unmanned aircraft system, comprising: a strutless monocoque composite wing root section comprising a first thin membrane forming an airfoil-shaped external wing root surface and defining a spanwise internal root lumen opening at a root inboard end and a root outboard end, anda strutless monocoque composite wing tip section comprising a second thin membrane forming an airfoil-shaped external tip surface and defining a spanwise internal tip lumen opening at a tip inboard end and a closed tip outboard end, whereinthe wing tip section nests within the root lumen in a collapsed position, andwherein the tip outboard end protrudes from the root lumen at the root outboard end in an extended position. 15. The collapsible wing of claim 14, further comprising a locking mechanism comprising a first locking element attached to the root section and a second locking element attached to the tip section, wherein the first locking element is reversibly engaged with the second locking element, and wherein the tip section is secured in a fixed position relative to the root section when the collapsible wing is in the extended position. 16. The collapsible wing of claim 15 further comprising at least one additional strutless monocoque composite wing intermediate section comprising a third thin membrane forming an airfoil-shaped external intermediate surface and defining an internal spanwise intermediate lumen opening at an intermediate inboard end and at an intermediate outboard end, wherein: the wing tip section nests within the intermediate lumen and the intermediate section nests within the root lumen in the collapsed position, andwherein the tip outboard end protrudes from the intermediate lumen at the intermediate outboard end and the intermediate outboard end protrudes from the root lumen at the root outboard end in the extended position. 17. A unmanned air system comprising a first collapsible wing, a second collapsible wing, and a fuselage, wherein: the first collapsible wing and the second collapsible wing each comprise at least two nested strutless monocoque composite wing span sections comprising a wing root section and a wing tip section;the system further comprises an integrated attachment fitting situated at an inboard edge of the wing root section, wherein the attachment fitting reversibly engages a corresponding integrated receptacle situated on the fuselage; andeach wing is extended by deploying each wing tip section in an outboard direction, resulting in the sliding of each wing span section in an outboard direction in a telescoping movement. 18. The unmanned air system of claim 17, wherein the first collapsible wing and the second collapsible wing are identical in size and shape and are used interchangeably as a left wing and a right wing. 19. The unmanned air system of claim 18, wherein the first collapsible wing is used as the left wing and the second collapsible wing used as the right wing, and wherein the first collapsible wing and the second collapsible wing are not used interchangeably. 20. The unmanned air system of claim 17, wherein the first collapsible wing and the second collapsible wing are integrated into a single collapsible wing comprising at least three nested strutless wing span sections comprising the center section, a first wing tip section, and a second wing tip section, wherein; the integrated attachment fitting is situated at a centerline location on the center section, wherein the attachment fitting reversibly engages a corresponding integrated receptacle situated on the centerline of the fuselage; andthe single collapsible wing is extended by deploying the first wing tip section and the second wing tip section in opposite spanwise directions, resulting in the translation of the first wing tip section and the second wing tip section in opposite outboard directions in a telescoping movement. 21. A method of transporting and assembling an unmanned air system comprising a first collapsible wing comprising a first monocoque composite wing tip section nested within a first monocoque composite wing root section, a second collapsible wing comprising a second monocoque composite wing tip section nested within a second monocoque composite wing root section, and a fuselage, the method comprising: carrying the unmanned air system in a disassembled state within one or more packs carried by one or more persons, wherein the disassembled state comprises the first collapsible wing in a collapsed configuration and the second collapsible wing in the collapsed configuration;deploying the first wing tip section to extend the first collapsible wing to an extended configuration;deploying the second wing tip to extend the second collapsible wing to the extended position;attaching the extended first collapsible wing to a corresponding first wing fitting, wherein the first wing fitting is situated at a first side of the fuselage; and,attaching the extended second collapsible wing to a corresponding second wing fitting, wherein the second wing fitting is situated at a second side of the fuselage. 22. A collapsible wing for an unmanned aircraft system, comprising at least two strutless wing span sections, each comprising a first inner wing span section and an outer wing span section, wherein: the first inner wing span section nests within the outer wing span section in a collapsed configuration;the collapsible wing further comprises at least one locking mechanism;the collapsible wing is deployed into an extended configuration by removing the first inner wing span section from a nested position within the outer wing span section until the at least one locking mechanism reversibly engages to secure the wing span section in a fixed relationship; andthe at least two wing span sections further incorporate one or more mechanical limits to prevent the separation of the at least two wing span sections during deployment to the extended configuration.
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