远地点发动机

据有关方面初步调查，卫星的远地点发动机因燃料阀发生故障不能正常运转是造成失败的原因。

According to preliminary investigations by concerned parties , the cause of the failure was that the satellite 's apogee engine was unable to normally operate because of a breakdown in the fuel valve .

黏合剂活性基团对HTPB推进剂力学性能的影响机制双组元液体推进剂远地点发动机

Mechanism of influence of active groups in binder on mechanical properties of HTPB propellants bipropellant liquid apogee motor

STW试验通信卫星远地点发动机飞行实验

Space-flight tests of the apogee boost motor for STW experimental communications satellite

STW试验通讯卫星远地点发动机真空总冲测试技术

The measuring technology on vacuum total impulse of the apogee booster for STW experimental communication satellite

文中还以FG-15远地点发动机为例介绍了我国固体推进技术的水平。

To show the progresses made by China in this field , the FG-15 apogee motor used on Chinese DFH-2 geostationary communications satellite is introduced at the end of the article .

液体远地点发动机工作期间卫星的姿态控制问题

The attitude control problems of satellite as Liquid Apogee moter is working

双组元液体推进剂远地点发动机

Bipropellant liquid apogee motor

文章给出在发射静止卫星过程中，固体远地点发动机点火时间和点火姿态的最佳值确定方法。

This paper provides a method for determining the optimum time and attitude in process of geostationary satellite launch at which the solid-apogee motor to be fired .

在采用小推力远地点发动机的情况下，地球静止卫星在远地点变轨的策略宜按整星功能实现和优化的原则确定。

Under the Condition of utilization low-thrust apogee motor , the apogee maneuver scheme for the geostationary satellite is defined by the Principle of realization and optimization of entire satellite function .

本文将全系数自适应控制方法用于带有液体晃动和挠性太阳帆板的三轴稳定地球同步轨道卫星在远地点发动机工作期间的姿态自适应控制。

In this paper , the all-coefficient adaptive control method is adapted to the adaptive attitude control of three-axis stabilized satellite with liquid propellant and flexible solar arrays during the liquid apogee motor operating .

高比冲双组元液体远地点火箭发动机研究

Research on the High Specific Impulse Bipropellant Liquid Apogee Engine

本文应用一维多流管耦合模型分析了液体远地点火箭发动机中的燃烧、流动过程及各因素对燃烧效率的影响。

The one-dimensional coupled stream tube model is presented and used for analysis of combustion and flow processes in liquid rocket engine at apogee . The effects of various factors on combustion efficiency are also analyzed .