|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 12 인용 특허 : 0|
An improved flight control system for use in guided missiles having a plurality of individually actuable control surfaces is shown. In order to overcome the deleterious effects of aerodynamic cross-coupling between control surfaces at a high angle of attack, the disclosed system includes means for first determining the lift force and roll moment of each control surface, and then, in accordance with the determined values of such forces and moments, controlling separately the total pitch lift force, yaw lift force and roll moment generated by all control s...
In a flight control system for a cruciform missile having opposite pairs of control fins disposed around the body of such missile, the aerodynamic force on each one of such control fins during flight being dependent upon the angle of attack of such missile, the improvement comprising: a. means for continuously measuring the aerodynamic force on each separate one of the opposite pairs of control fins of the cruciform missile during flight and for producing a set of analogous electrical signals; b. computer means, responsive to the set of analogous electri...