|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F42B-010/66 F42B-010/00 F42B-012/62|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 2 인용 특허 : 38|
An air vehicle, such as a missile or a steerable submunition released from a missile or another air vehicle, has a bilateral thrust system for steering. The thrust system includes a pair of diametrically-opposed divert thrusters that provide thrust having radial components in opposite radial directions. In order to control the direction of thrust, the air vehicle controls rotation of the divert thrusters and/or timing of the firing of the thrusters. The air vehicle (or some part of the air vehicle that includes the divert thrusters) may be discretely rol...
1. An air vehicle comprising: a thrust system that includes a pair of diametrically-opposed divert thrusters that provide thrust having radial components in opposite radial directions;a rotation system for rotating the divert thrusters circumferentially about a longitudinal axis of the air vehicle; anda control system operatively coupled to the thrust system and the rotation system;wherein the thrust system includes a pressurized gas source that provides continuous flow of pressurized gas, and a valve that apportions the continuous flow between the diver...