论文部分内容阅读
序言固体火箭发动机(SRM)是航天飞机固体助推器的一个部件。SRM的结构包括四个发动机段和一个单独的后出口锥组件。点火系统安装在前段内,可动喷管和后段相连。航天飞机每次飞行需用两台固体助推器,所以固体发动机应配对生产,然后由铁路运到发射阵地进行垂直装配。喷管有一柔性接头,用钢和橡胶薄板交替粘结而成,可提供达8°摆角的全轴向量控制。其控制靠每个助推器后裙处的两个液压动力装置驱动两个液压作动筒。 SRM是由Morton Thiokol(莫顿—锡奥科尔)公司在犹它州的Wasatch分部按照NASA马歇尔飞行中心的合同设计、研制和生产的。STS—7及其以前的各次飞行所用
Introduction The Solid Rocket Engine (SRM) is a part of the space shuttle’s solid booster. The structure of the SRM includes four engine sections and a single rear exit cone assembly. The ignition system is installed in the front section, the movable nozzle is connected with the rear section. Shuttle requires two solid boosters for each flight, so solid engines should be mated and then transported by rail to launch positions for vertical assembly. The nozzle has a flexible joint made of steel and rubber sheet alternately bonded to provide up to 8 ° angle of the whole axis vector control. The controls drive two hydraulic jacks by means of two hydraulic power units at the rear skirt of each booster. The SRM was designed, developed and manufactured by Morton Thiokol’s Wasatch division in Utah under a NASA Marshall Flight Center contract. STS-7 and its previous flights