|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64C-003/56 F42B-010/14 F42B-015/01|
|미국특허분류(USC)||244/049 ; 244/032.7 ; 244/032.8 ; 244/032.9|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 11 인용 특허 : 4|
The wing deployment device is a simple mechanical device that resides in hollow of the wing and combines a primary and a secondary rotational motions to translate the wing from its stored position to its deployed position. The primary rotational motion occurs when the initial restraint holding the wing to the missile body is severed and the wing, under the influence of the spring component of the device, rotates to a position normal to the missile body axis. After the lapse of a pre-determined duration of time, the secondary rotational motion is started ...
[ I claim:] [1.] A device for deploying a hollowed wing of a flying object upon the severance of the initial restraint of the wing, said device residing in the hollow of the wing and the flying object having a rib protruding from the exterior surface thereof, said device comprising:a swivel having a first cylindrical hole therethrough; a base positioned between said rib and said swivel, said base having a second cylindrical hole therethrough and being rigidly coupled to the interior surface of the wing; a cylindrical shaft inserted through said cylindric...