BAE Systems Information and Electronic Systems Integration Inc.
대리인 / 주소
Maine Cernota & Rardin
인용정보
피인용 횟수 :
1인용 특허 :
12
초록▼
A compact, purely mechanical wing deployment assisting mechanism uses torsion springs and lever arms to apply a deploying force to a guidance wing during its initial deployment through a wing slot in a rocket or missile, thereby assisting the wing to burst through a cover seal protecting the wing sl
A compact, purely mechanical wing deployment assisting mechanism uses torsion springs and lever arms to apply a deploying force to a guidance wing during its initial deployment through a wing slot in a rocket or missile, thereby assisting the wing to burst through a cover seal protecting the wing slot. The wings are then fully deployed by centrifugal force. Various embodiments include two “extreme duty” springs and two lever arms per wing, working in parallel. Embodiments provide a total of at least 24 pounds of force per wing at the end of a spring travel of 0.30 inches. In some embodiments, the entire mechanism weighs less than 0.5 pounds and/or occupies less than 2.5 cubic inches per wing. In embodiments, an assembled group, including two springs and two lever arms, is located between each pair of wings, whereby each assembled group applies one lever arm to each adjoining wing.
대표청구항▼
1. A wing deployment assisting mechanism for increasing an initial deployment force applied to a guidance wing of a rocket or missile so as to propel the guidance wing outward from a stowed configuration at least through an initial phase of movement toward a deployed configuration of the guidance wi
1. A wing deployment assisting mechanism for increasing an initial deployment force applied to a guidance wing of a rocket or missile so as to propel the guidance wing outward from a stowed configuration at least through an initial phase of movement toward a deployed configuration of the guidance wing, the wing deployment assisting mechanism comprising: at least one lever arm pivotally fixed to the rocket or missile, the lever arm being distinct and separate from the guidance wing, but cooperative with the guidance wing so as to propel the guidance wing outward from the stowed configuration when the lever arm is pivoted outward, the lever arm being separated from the guidance wing and providing no support to the guidance wing when the guidance wing is in the deployed configuration; andat least one torsion spring cooperative with the lever arm and configured to apply a deploying force tending to pivot the lever arm outward. 2. The wing deployment assisting mechanism of claim 1, wherein the torsion spring is an extreme duty torsion spring. 3. The wing deployment assisting mechanism of claim 1, wherein the rocket or missile includes N guidance wings, 2N lever arms and 2N torsion springs, where N is an integer greater than 1, each of the guidance wings being propelled by two corresponding lever arms and two corresponding torsion springs. 4. The wing deployment assisting mechanism of claim 3, wherein the 2N lever arms and 2N torsion springs are included in N compact assemblies, each compact assembly including two of the lever arms and two of the torsion springs, one of the lever arms in each compact assembly being a first lever arm and the other of the lever arms being a second lever arm, one of the torsion springs in each compact assembly being a first torsion spring and the other of the torsion springs being a second torsion spring. 5. The wing deployment assisting mechanism of claim 4, wherein one of the compact assemblies is located between each pair of adjacent guidance wings. 6. The wing deployment assisting mechanism of claim 5, wherein for each of the compact assemblies, the first torsion spring and the first lever arm apply a deploying force to the guidance wing on a first side of the compact assembly, and the second torsion spring and the second lever arm apply a deploying force to the guidance wing on a second side of the compact assembly. 7. The wing deployment assisting mechanism of claim 6, wherein for each of the compact assemblies the first and second lever arms pivot about axes which differ in angle by 360°/N. 8. The wing deployment assisting mechanism of claim 1, wherein the deploying force is sufficient to enable the guidance wing to break through a frangible seal covering a wing slot in a fuselage of the rocket or missile. 9. The wing deployment assisting mechanism of claim 1, wherein the mechanism applies at least 24 pounds of deploying force to the wing at the end of a spring travel of 0.30 inches. 10. The wing deployment assisting mechanism of claim 1, wherein the rocket or missile includes N guidance wings, N being an integer greater than 1, and the entire wing deployment assisting mechanism for all of the N guidance wings weighs less than 0.5 pounds. 11. The wing deployment assisting mechanism of claim 1, wherein the rocket or missile includes N guidance wings, N being an integer greater than 1, and the wing deployment assisting mechanism occupies less than 2.5 cubic inches per guidance wing. 12. The wing deployment assisting mechanism of claim 1, wherein the lever arm remains internal to a main assembly of the rocket or missile during deployment of the guidance wing to the deployed configuration.
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이 특허에 인용된 특허 (12)
Nicholas Paul H. (Burbank CA) Lipera Larry (Lancaster CA) Justice Stephen G. (Santa Clarita CA) Wurts Joseph M. (Valencia CA), Airborne vehicle with wing extension and roll control.
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