|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 8 인용 특허 : 0|
A control system for a guided missile includes means for rotating the missile about its axis, a discharge nozzle so directed that its thrust exerts a lateral force on the missile and an associated reaction motor arranged to deliver, in response to a suitable signal, a thrust of suitable timing and duration to correct the missile trajectory. A suitable reaction motor has a combustion chamber in communication with the discharge nozzle by way of a relief valve, a compressible fuel tank pressurized by gases from the combustion chamber by way of a differentia...
A control system for a guided missile comprising means for rotating the missile about its axis; a discharge nozzle so directed that the thrust therefrom has a lateral component relative to the missile; a reaction motor associated with the said nozzle and having means for actuating the said motor, in response to a suitable signal, to produce a thrust from the nozzle appropriately times in relation to the roll position of the missile and appropriate duration for correcting the missile trajectory; said reaction motor comprising a combustion chamber; a disch...