Rolling vehicle having collar with passively controlled ailerons
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F42B-015/01
F42B-010/64
출원번호
US-0215497
(2011-08-23)
등록번호
US-8993948
(2015-03-31)
발명자
/ 주소
Geswender, Chris E.
Vesty, Paul
Frost, Geoffrey W.
Morgan, Bruce E.
Strassman, Doron
출원인 / 주소
Raytheon Company
대리인 / 주소
Renner, Otto, Boisselle & Sklar, LLP
인용정보
피인용 횟수 :
1인용 특허 :
9
초록▼
A spinning, rolling, or roll-stabilized vehicle, such as a projectile, includes a fuselage that rotates about its longitudinal axis (spins) during flight. A collar is positionable relative to the fuselage to steer the projectile, with the collar having ailerons to provide a roll force to position th
A spinning, rolling, or roll-stabilized vehicle, such as a projectile, includes a fuselage that rotates about its longitudinal axis (spins) during flight. A collar is positionable relative to the fuselage to steer the projectile, with the collar having ailerons to provide a roll force to position the collar. The collar also has elevators to provide lateral force to steer the projectile. The positioning of the collar may be accomplished by moderating the roll force of the ailerons to hold the position of the collar substantially constant with regard to a longitudinal axis of the projectile. The ailerons passively change angle of attack with changes in the dynamic pressure of the projectile. At low speeds the ailerons have a relatively large angle of attack, and at high speeds, the ailerons resiliently reduce their angles of attack, avoiding large rolling forces on the collar.
대표청구항▼
1. An air vehicle comprising: a fuselage that rolls about a longitudinal axis of the fuselage; anda collar that is positionable relative to the fuselage;wherein the collar includes ailerons that passively change angle of attack without a directed input force or commanded action, relative to a collar
1. An air vehicle comprising: a fuselage that rolls about a longitudinal axis of the fuselage; anda collar that is positionable relative to the fuselage;wherein the collar includes ailerons that passively change angle of attack without a directed input force or commanded action, relative to a collar housing of the collar, as a function of dynamic pressure of the projectile, with the change in angle of attack involving aerodynamic forces on the ailerons being balanced against resilient forces on the ailerons; andwherein the resilient forces are provided by resilient devices that are operatively coupled to the ailerons, in opposition to a pressure force on the ailerons that tends to reduce the angle of attack of the ailerons by pivoting the ailerons as the dynamic pressure increases. 2. The air vehicle of claim 1, wherein the ailerons provide a circumferential force on the collar during flight of the projectile to counter-roll the collar in an opposite direction from the fuselage. 3. The air vehicle of claim 1, wherein the resilient devices include torsion bars that are operatively coupled to the ailerons to position the ailerons. 4. The air vehicle of claim 1, further comprising blisters external to a collar housing of the collar, wherein at least part of the resilient devices for changing angle of attack of the ailerons is located in the blisters. 5. The air vehicle of claim 1, wherein the collar also includes elevators;wherein the ailerons are used for positioning the collar relative to the fuselage; andwherein the elevators are used to provide a steering force on the projectile. 6. The air vehicle of claim 5, wherein the elevators each have a fixed angle of attack. 7. The air vehicle of claim 5, wherein the elevators are used for bank-to-turn steering. 8. The air vehicle of claim 1, further comprising mechanical stops that limit angle of attack changes of the ailerons. 9. The air vehicle of claim 1, wherein the ailerons passively change angle of attack independently of one another. 10. The air vehicle of claim 1, further comprising a brake to brake counter-rolling of the collar relative to the fuselage. 11. The air vehicle of claim 1, wherein collar is part of a fuzewell guidance kit. 12. An air vehicle comprising: a fuselage that rolls about a longitudinal axis of the fuselage; anda collar that is positionable relative to the fuselage;wherein the collar includes ailerons that passively change angle of attack without a directed input force or commanded action as a function of dynamic pressure of the projectile; andwherein the ailerons resiliently change angle of attack as a function of the dynamic pressure of the projectile; andfurther comprising respective springs operatively coupled to the ailerons that provide a spring force, in opposition to a pressure force on the ailerons that tends to reduce the angle of attack of the ailerons by pivoting the ailerons as the dynamic pressure increases. 13. The air vehicle of claim 12, wherein the spring force is provided by leaf springs. 14. The air vehicle of claim 12, wherein the spring force is provided by torsion springs. 15. The air vehicle of claim 12, wherein the spring force is provided by elastic bands. 16. An air vehicle comprising: a fuselage that rolls about a longitudinal axis of the fuselage; anda collar that is positionable relative to the fuselage;wherein the collar includes ailerons that provide a circumferential force on the collar during flight of the projectile; andwherein the ailerons resiliently change angle of attack without a directed input force or commanded action, relative to a collar housing of the collar, as a function of dynamic pressure of the projectile, with the change in angle of attack involving aerodynamic forces on the ailerons being balanced against resilient forces on the ailerons; andwherein the resilient forces are provided by resilient devices that are operatively coupled to the ailerons, in opposition to a pressure force on the ailerons that tends to reduce the angle of attack of the ailerons by pivoting the ailerons as the dynamic pressure increases. 17. A fuzewell guidance kit comprising: a guidance kit fuselage;a collar that is rotatable relative to the fuselage;wherein the collar includes ailerons that passively change angle of attack without a directed input force or commanded action, relative to a collar housing of the collar, as a function of dynamic pressure, with the change in angle of attack involving aerodynamic forces on the ailerons being balanced against resilient forces on the ailerons; andwherein the resilient forces are provided by resilient devices that are operatively coupled to the ailerons, in opposition to a pressure force on the ailerons that tends to reduce the angle of attack of the ailerons by pivoting the ailerons as the dynamic pressure increases. 18. The guidance kit of claim 17, wherein the collar also includes a pair of fixed-angle-of-attack elevators.
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이 특허에 인용된 특허 (9)
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Speicher John M. (Geyserville CA) Voigt Allan A. (Geyserville CA) Voigt Che-Ram S. (Geyserville CA), Differential yoke-aerofin thrust vector control system.
Seidel Wolfgang,DEX ; Guischard Frank,DEX, Method for autonomous guidance of a spin-stabilized artillery projectile and autonomously guided artillery projectile for realizing this method.
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