Inflatable airfoil system having reduced radar and infrared observability
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/00
B64C-003/00
B64C-005/00
출원번호
US-0633272
(2009-12-08)
등록번호
US-8727280
(2014-05-20)
발명자
/ 주소
Lutke, Kevin Reed
Kutzmann, Aaron Jonathan
출원인 / 주소
The Boeing Company
대리인 / 주소
Yee & Associates, P.C.
인용정보
피인용 횟수 :
4인용 특허 :
38
초록▼
A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a n
A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.
대표청구항▼
1. An apparatus comprising: a fuselage;an inflatable airfoil connected to the fuselage and having an inner end and an outer end, the inflatable airfoil comprising a number of materials substantially transparent to electromagnetic waves through the inflatable airfoil, the inflatable airfoil further c
1. An apparatus comprising: a fuselage;an inflatable airfoil connected to the fuselage and having an inner end and an outer end, the inflatable airfoil comprising a number of materials substantially transparent to electromagnetic waves through the inflatable airfoil, the inflatable airfoil further comprising a plurality of channels interconnected to form a serpentine flow path for a gas; anda section of the inflatable airfoil associated with the fuselage and having a number of openings including a first number of openings and a second number of openings, the first number of openings and the second number of openings in communication with at least some of the plurality of channels, the first number of openings configured to pass a heated gas into the plurality of channels and the second number of openings configured to allow the gas when cooled to exit out of the plurality of channels. 2. The apparatus of claim 1, wherein the section of the inflatable airfoil is configured to form an electrically continuous surface with the fuselage. 3. The apparatus of claim 1, further comprising an interface between the fuselage and the section of the inflatable airfoil configured to be electrically continuous with the fuselage and the section. 4. The apparatus of claim 3, wherein the inner end of the inflatable airfoil is associated with the interface. 5. The apparatus of claim 4, wherein a serpentine seal associates the inner end of the inflatable airfoil with the interface. 6. The apparatus of claim 1, wherein the section of the inflatable airfoil is configured to allow an electrical current to flow between the section and the fuselage. 7. The apparatus of claim 1, wherein the second number of openings is located at the inner end of the inflatable airfoil. 8. The apparatus of claim 1, wherein the second number of openings is in a location selected from at least one of a surface of the inflatable airfoil, the outer end of the inflatable airfoil, a leading edge of the inflatable airfoil, and a trailing edge of the inflatable airfoil. 9. The apparatus of claim 1, wherein the number of materials is selected from one of polyurethane, a bi-directional polyester film, plastic, a para-aramid synthetic fiber with an airtight liner, and nylon with the airtight liner. 10. The apparatus of claim 1, wherein the electromagnetic waves have a frequency from about 30 MHz to about 300 GHz. 11. The apparatus of claim 1, wherein the inflatable airfoil is selected from one of a wing, a canard, a stabilizer, a horizontal stabilizer, a vertical stabilizer, and a V-shaped stabilizer. 12. A system for an unmanned aerial vehicle, the system comprising: a fuselage;an inflatable airfoil having an inner end and an outer end, the inflatable airfoil comprising a number of materials substantially transparent to electromagnetic waves, the inflatable airfoil further comprising a plurality of channels interconnected to form a serpentine flow path for a gas;wherein a section of the inflatable airfoil is associated with the fuselage at an interface, the section of the inflatable airfoil having a number of openings in communication with at least some of the plurality of channels, the section of the inflatable airfoil configured to form an electrically continuous surface with the fuselage by allowing an electrical current to flow between the section of the inflatable airfoil and the fuselage, the section of the inflatable airfoil further configured to reduce an entry of the electromagnetic waves into an interior of the fuselage;an airfoil skin forming a surface of the inflatable airfoil, a portion of the airfoil skin at the inner end of the inflatable airfoil associated with the fuselage at the interface by a serpentine seal;a heat exchange system in fluid communication with the plurality of channels, a first number of openings in the number of openings in the section of the inflatable airfoil in communication with the plurality of channels, and a second number of openings in communication with the plurality of channels, the first number of openings configured to pass a heated gas into the plurality of channels and the second number of openings configured to allow the gas when cooled to exit out of the plurality of channels, the second number of openings further configured to send a cooled gas to a location selected from at least one of the inner end of the inflatable airfoil, the surface of the inflatable airfoil, the outer end of the inflatable airfoil, a leading edge of the inflatable airfoil, and a trailing edge of the inflatable airfoil; andan inflation system connected to the inflatable airfoil, the inflatable airfoil selected from one of a stabilizer, a horizontal stabilizer, a vertical stabilizer, and a V-shaped stabilizer. 13. An apparatus comprising: an airfoil having an inner end and an outer end, the airfoil further having a plurality of channels interconnected to form a serpentine flow path for gas within the airfoil;a first number of openings in communication with the plurality of channels; anda second number of openings in communication with the plurality of channels, the first number of openings and the second number of openings associated with at least some of the plurality of channels, the first number of openings configured to pass a heated gas into the plurality of channels and the second number of openings configured to allow the gas when cooled to exit out of the plurality of channels. 14. The apparatus of claim 13, wherein the airfoil is an inflatable airfoil comprised of a number of materials substantially transparent to electromagnetic waves through the inflatable airfoil. 15. The apparatus of claim 14, wherein the first number of openings and the second number of openings are connected to a fuselage of an aircraft. 16. The apparatus of claim 15, further including a heat exchange system comprising a plurality of gas lines within the aircraft, wherein a third and fourth number of openings are in communication with said gas lines and the plurality of channels. 17. The apparatus of claim 14, wherein the second number of openings is located at the inner end of the inflatable airfoil. 18. The apparatus of claim 17, wherein the second number of openings is in a location selected from at least one of a surface of the airfoil, the outer end of the inflatable airfoil, a leading edge of the airfoil, and a trailing edge of the airfoil.
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