| 摘要 |
A missile (10) has a flight termination system (30) that includes deployable lift surfaces (34) that deploy forward of a center of gravity (22) of the missile. When deployed, the lift surfaces (34) cause the missile (10) to rotate about its longitudinal axis (40). This rotation eventually increases in rate until the missile nears a natural roll frequency of the missile. As the missile nears or reaches its natural roll frequency, the missile's nose pitches up, angle of attack diverges and the missile tumbles, resulting in rapid termination of flight by loss of aerodynamic lift, vertical plunging and crashing. The lift surfaces may be curved surfaces that conform to the shape of a fuselage of the missile, prior to the deployment of the lift surfaces. The lift surfaces may be canted slightly relative to a missile longitudinal axis when the lift surfaces are deployed. |
