|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/003.28; 244/003.29; 244/003.27|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 5 인용 특허 : 7|
A missile has a flight termination system that includes deployable lift surfaces that deploy forward of a center of gravity of the missile. When deployed, the lift surfaces cause the missile to rotate about its longitudinal axis. 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 pl...
1. A missile comprising: a fuselage; anddeployable roll-producing lift surfaces that deploy during flight from the fuselage, forward of a center of gravity of the missile;wherein the lift surfaces provide a roll moment to the missile, as part of a flight termination system to terminate flight of the missile; and further comprising canards forward of the center of gravity. 2. The missile of claim 1, wherein the lift surfaces also cause the missile to pitch up when the lift surfaces are deployed. 3. The missile of claim 1, wherein the lift surfaces are cur...