发明名称 |
Rocket attitude control apparatus |
摘要 |
For controlling the attitude of a rocket including a rocket fuselage and a thrust nozzle integrally attached to the rear end of the rocket fuselage and having a nozzle throat located longitudinally intermediate thereof, a rocket attitude control apparatus comprises a plurality of thrust vector control units disposed at the outer periphery of the thrust nozzle between the nozzle throat and the rear end of the thrust nozzle in circumferentially equiangularly spaced relationship to each other, and each including a fluid injecting nozzle projectable and retractable into and out of the thrust nozzle and having an injecting bore therein, wherein said fluid injecting nozzle is permitted to project into the thrust nozzle while being cooled by fluid injected from the injecting bore into the thrust nozzle. The projection of the fluid injecting nozzle causes a stream of combustion gas passing through the thrust nozzle to be partially disturbed for controlling the attitude of the rocket.
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申请公布号 |
US4384694(A) |
申请公布日期 |
1983.05.24 |
申请号 |
US19800171466 |
申请日期 |
1980.07.23 |
申请人 |
NISSAN MOTOR COMPANY, LIMITED |
发明人 |
WATANABE, YASUSHI;FUJIWARA, TERUO;SHIMANO, KUNIO |
分类号 |
B64D33/04;B64G1/00;F02K9/80;F02K9/82;F02K9/90;(IPC1-7):F42B15/18 |
主分类号 |
B64D33/04 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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