[특허]Survivable and reusable launch vehicle

The Boeing Company

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Survivable and reusable launch vehicle

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-03702
미국특허분류(USC)	244/002
출원번호	US-0453777 (2003-06-03)
발명자 / 주소	August, Henry
출원인 / 주소	The Boeing Company
대리인 / 주소	Harness Dickey &
인용정보	피인용 횟수 : 2 인용 특허 : 7

초록
▼

A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.

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1. A reusable, mach-velocity mobile platform comprising:a generally tubular shaped body having an aft end, a forward end, and a payload section disposed about a longitudinal axis of said body; a weapons release device operable to discharge at least one weapon from the aft end of said body; an arch wing supported at said aft end of said body; and a forward steering device connectable at said forward end, said forward steering device configurable as an arched wing canard; wherein said platform is adaptable for operation phases including at least one of a propelled vertical launch phase, a powerless glide phase, a weapons release phase, and a landing phase. 2. A reusable, mach-velocity mobile platform comprising:a generally tubular shaped body having an aft end, a forward end, and a payload section disposed about a longitudinal axis of said body; an arch wing supported at said aft end of said body; a forward steering device connectable at said forward end, said forward steering device configurable as an arched wing canard; and a canard axis of rotation, said arched wing canard being rotatably connected to said forward end about said canard axis of rotation; wherein said platform is adaptable for operation phases including at least one of a propelled vertical launch phase, a powerless glide phase, a weapons release phase, and a landing phase. 3. The mobile platform of claim 2, wherein said arched wing canard comprises both a port adjustment mechanism and a starboard adjustment mechanism to roll said mobile platform about said mobile platform longitudinal axis.4. The mobile platform of claim 3, wherein each said port adjustment mechanism and said starboard adjustment mechanism are operable to rotate said arched wing canard in each of a forward and an aft direction to provide for an independent port steering force and an independent starboard steering force for said mobile platform.5. The mobile platform of claim 2, wherein said arched wing canard is rotatable to each of a forward rotated position, a neutral position and an aft rotated position.6. The mobile platform of claim 5, wherein when said arched wing canard is rotatably positioned in said forward rotated position, a download is generated by said arched wing canard to said forward end.7. The mobile platform of claim 5, wherein when said arched wing canard is rotatably positioned in said aft rotated position, an upload is generated by said arched wing canard to said forward end.8. The mobile platform of claim 5, wherein when said arched wing canard is rotatably positioned in said neutral position, one of an upload and a neutral load is generated by said arched wing canard to said forward end.9. The mobile platform of claim 2, further comprising a plurality of landing devices extendable from said body.10. The mobile platform of claim 2, further comprising a nose assembly connected at said forward end, said nose assembly having an upward fixed angle-of-attack to provide lift force at said forward end.11. A method to operate a multiple mach velocity mobile platform comprising the steps of:coating a plurality of body surfaces of a mobile platform with a radar absorbing material; compressively loading a looped steering device as a control surface at a forward end of the mobile platform; loading a weapons package into the mobile platform; launching the mobile platform; uncoiling the looped steering device to a flight control position; rotating at least a portion of said steering device to generate a steering force at said forward end of said mobile platform; and controlling a powerless flight phase of the mobile platform using the looped steering device at the forward end and a control surface located at an aft end of the mobile platform. 12. The method of claim 11, comprising rotating said steering device to control one of an upload and a download during said powerless flight phase.13. The method of claim 11, comprising launching the mobile platform to a predetermined altitude at a multiple mach velocity.14. The method of claim 11, comprising discharging the weapons package through an aft end of the mobile platform during a weapons release phase following said powerless flight phase.15. A flight control system for a reusable flight platform, comprising:a body section having an aft end, a forward end, and a payload portion positioned between the forward end and the aft end; an arch wing having an upper wing section positioned directly above a lower wing section, the arch wing connectable to the aft end of the body section; an aft flight control device connectable to the arch wing; a forward flight control device connectable at the forward end, the forward steering device configurable as an arched wing canard rotatable toward at least one of the forward end and the aft end; and a mechanism to deploy the arched wing canard between each of a contracted or stowed position and an expanded or deployed position. 16. The flight control system of claim 15, wherein the mechanism to deploy the arched wing canard is further divisible into a port mechanism and a starboard mechanism.17. The flight control system of claim 16, wherein a forward attitude of the body section is controllable by a co-rotation of both the port mechanism and the starboard mechanism.18. The flight control system of claim 16, wherein at least one of a port and a starboard steering motion of the body section is controllable by a rotation of one of the port mechanism and the starboard mechanism relative to the other.19. The flight control system of claim 15, wherein in the contracted or stowed position, the arched wing canard is conformable to a perimeter of the body section.20. The flight control system of claim 15, wherein a material of the arched wing canard is selectable to provide a spring force to retain the arched wing canard in the expanded or deployed position.21. A method to operate a multiple mach velocity mobile platform comprising the steps of:compressing a looped steering device at least partially about a circumference of the mobile platform at a forward end of the mobile platform; launching the mobile platform; expanding the looped steering device to a flight control position after launching the mobile platform; rotating at least a portion of the steering device in one of a forward and an aft direction to generate a steering force at the forward end of the mobile platform; and controlling a powerless flight phase of the mobile platform using the looped steering device at the forward end and a control surface located at an aft end of the mobile platform. 22. The method of claim 21, comprising discharging a weapons package through an aft end of the mobile platform during a weapons release phase following the powerless flight phase.23. The method of claim 22, comprising loading the weapons package into the mobile platform prior to launching the mobile platform.24. The method of claim 21, comprising:recovering the mobile platform for reuse following the weapons release phase; and loading a new weapons package into the mobile platform. 25. A flight control system for a reusable flight platform, comprising:a body section having an aft end, a forward end, and a payload portion positioned between the forward end and the aft end; an arch wing connectable to the aft end of the body section; an aft flight control device connectable to the arch wing; a forward flight control device connectable at the forward end, the forward steering device configurable as an arched wing canard; and a mechanism to deploy the arched wing canard between each of a contracted or stowed position and an expanded or deployed position, the mechanism further divisible into a port mechanism and a starboard mechanism; wherein a forward attitude of the body section is operably controllable by a co-rotation of both the port mechanism and the starboard mechanism.

이 특허에 인용된 특허 (7)

이 특허를 인용한 특허 피인용횟수: 2

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Survivable and reusable launch vehicle

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이 특허에 인용된 특허 (7)

이 특허를 인용한 특허 피인용횟수: 2

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Survivable and reusable launch vehicle

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이 특허에 인용된 특허 (7)

이 특허를 인용한 특허 피인용횟수: 2

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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