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首页> 外国专利> METHOD FOR CONTROL OF TRACTION VECTOR OF LIQUID-PROPELLANT ROCKET ENGINE AND LIQUID-PROPELLANT ROCKET ENGINE FOR ITS REALIZATION

METHOD FOR CONTROL OF TRACTION VECTOR OF LIQUID-PROPELLANT ROCKET ENGINE AND LIQUID-PROPELLANT ROCKET ENGINE FOR ITS REALIZATION

机译：控制液体火箭发动机和液体火箭发动机牵引矢量的实现方法

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A method for control of traction vector of a liquid-propellant rocket engine and liquid-propellant rocket engine for its realization is proposed. The method is based on control of flow rate of fuel components for injection to the nozzle according to required lateral forces, gas-dynamical control of traction vector of the engine is performed jointly by non-symmetrical injection of fuel component to supersonic flow of nozzle through the units for injection, and mechanical control of traction vector with tilting the chamber or the engine as a whole, this is fixed in hinge unit with drives connected to the devices of gas-dynamical control of traction vector and the system of control of flight of the spacecraft. The liquid-propellant rocket engine with controlled traction vector includes a combustion chamber with supersonic nozzle, turbo-pump system for supply of fuel components to combustion chamber with turbine that includes an exhaust collector of generator gas connected with gas duct to the circular collector of the exhaust gas supercharge to supersonic section of the nozzle, the units for injection of fuel components to the nozzle placed in each quarter of the nozzle and connected with pipelines with control devices with high-pressure main of the engine, drives of control devices connected to command control devices. The engine is connected to the body of the stage of the rocket with a hinge unit, and with drives installed in the planes of control of traction vector for tilting the chamber of the engine or the engine as a whole and connected to the system for control of flight and the system of gas-dynamical control of traction vector.
机译：提出了一种控制液体火箭发动机牵引力的方法和实现该方法的液体火箭发动机。该方法基于根据所需的侧向力控制用于喷射到喷嘴的燃料成分的流速，通过将燃料成分非对称地喷射到喷嘴的超音速流中来联合执行发动机的牵引矢量的气动控制。注射单元，以及使腔室或发动机整体倾斜的牵引矢量的机械控制，固定在铰链单元中，驱动器连接到牵引矢量的气体动力控制装置和飞行控制系统飞船。具有受控牵引力矢量的液体推进剂火箭发动机包括带有超音速喷嘴的燃烧室，用于向带有涡轮的燃烧室供应燃料成分的涡轮泵系统，该涡轮泵系统包括与气体管道相连的发电机气体的排气收集器，该收集器的气体管道连接至涡轮的圆形收集器。排气增压到喷嘴的超音速部分，将燃料成分喷射到喷嘴的单元放置在喷嘴的每个四分之一中，并与带有高压发动机控制装置的管路相连，控制装置的驱动器与命令相连控制设备。发动机通过铰链单元连接到火箭级的主体，驱动器安装在牵引矢量的控制平面中，用于使发动机腔或整个发动机倾斜，并连接至控制系统飞行原理和牵引矢量的气动力控制系统。

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