|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 6 인용 특허 : 0|
A control system for use in missiles and other projectiles which provides pitch, yaw and roll control. The control system includes two opposing pairs of flaps configured in the aft end of the missile case. Each flap is attached for rotation about its leading edge. Prior to actuation, the flaps conform to the exterior surface of the missile. Upon actuation, the flaps extend into the airstream to induce aerodynamic forces. The axis of rotation of each flap is positioned at an oblique angle to the radial plane of the missile.
A control system for providing control in a projectile having an elongate case, the control system comprising: a first pair of flaps configured in opposing sides of the projectile case, each flap including a leading edge which is attached for rotation about an axis oriented at a first oblique angle to the radial plane of the projectile; a second pair of flaps configured in opposing sides of the projectile case, each flap of the second pair including a leading edge which is attached for rotation about an axis oriented at a second oblique angle to the radi...