发明名称 |
PROPULSION SYSTEM FOR AN AIRCRAFT, IN PARTICULAR FOR A MISSILE |
摘要 |
<p>A propulsion system including: a booster; a turbojet engine; the booster including a chamber which is fixed to a rear casing of the turbojet engine by being arranged along the longitudinal axis thereof, which chamber includes at a rear a jet pipe and includes at least one charge and a mechanism initiating the charge; and gas bleed tubes connected to the booster and which are configured either for igniting the combustion chamber of the turbojet engine on for starting the turbine of the turbojet.</p> |
申请公布号 |
EP2614242(A1) |
申请公布日期 |
2013.07.17 |
申请号 |
EP20110773056 |
申请日期 |
2011.09.08 |
申请人 |
MICROTURBO;MBDA FRANCE;ROXEL FRANCE |
发明人 |
GUYADER, GILLES, AIME, YANN;RIDEAU, JEAN-FRANCOIS;PFIFFER, ANDRE;DOUALLE, JEAN-FRANCOIS |
分类号 |
F02C7/27;F02K9/00;F02K9/30;F02K9/78;F41A33/02;F42B15/10 |
主分类号 |
F02C7/27 |
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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