V72 航天器动力系统 标准查询与下载

CISPR 16-1-2-2014 无线电干扰和抗扰度测量设备和方法规范.第1-2部分:无线电干扰和抗扰度测量设备.用于传导干扰测量的耦合装置

Specification for radio disturbance and immunity measuring apparatus and methods - Part 1-2: Radio disturbance and immunity measuring apparatus - Coupling devices for conducted disturbance measurements

GOST R 56099-2014 液体火箭发动机. 强制试验方法

Engines rocket liquid. Methods of the forced test

QJ 1789.1-2011 液体火箭发动机试验测量不确定度评定

Evaluation of Measurement Uncertainty in Liquid Rocket Motor Test

QJ 1789.2-2011 液体火箭发动机试验测量不确定度评定

Evaluation of Measurement Uncertainty in Liquid Rocket Motor Test

QJ 1789.3-2011 液体火箭发动机试验测量不确定度评定

Evaluation of Measurement Uncertainty in Liquid Rocket Motor Test

BS ISO 10830:2011 空间系统.无损检验.固体火箭发动机用石墨锭的自动超声波检查方法

Space systems. Non-destructive testing. Automatic ultrasonic inspection method of graphite ingot for solid rocket motors

BS ISO 23339:2011 太空系统.无人驾驶飞船.剩余可用推进剂的质量估算

Space systems. Unmanned spacecraft. Estimating the mass of remaining usable propellant

SAE AIR1168/11A-2011 航天器推进和入口传热

The prediction of vehicle temperatures during ascent through the earth's atmosphere requires an accurate knowledge of the aerodynamic heating rates occurring at the vehicle surface. Flight parameters required in heating calculations include the local airstream velocity, pressure, and temperature at the boundary layer edge for the vehicle location in question. In addition, thermodynamic and transport air properties are required at these conditions. Both laminar and turbulent boundary layers occur during the boost trajectory. Experience has shown that laminar and turbulent heating are of equivalent importance. Laminar heating predominates in importance in the stagnation areas, but the large afterbody surfaces are most strongly affected by turbulent heating. Once the local flow conditions and corresponding air properties have been obtained, the convective heating rate may be calculated for a particular wall temperature. This assumes that the boundary layer flow regime (that is, turbulent, laminar, or transitory) has also been established, so that a heating theory corresponding to the particular flow conditions may be selected. This section presents theoretical methods for computing boost vehicle surface aerodynamic heating rates. First, procedures are given for computing the local flow distributions around the vehicle. Second, methods are given for computing the convective heating rates, using the flow parameters found previously.

Spacecraft Boost and Entry Heat Transfer

QJ 20021-2011 姿控发动机气体引射高空模拟试验方法

本标准规定了姿控发动机气体(氮气、空气)引射高空模拟试验的-般要求、试验准备、试验程序和试验结果处理要求。 本标准适用于可贮存推进剂液体火箭姿控发动机(以下简称发动机)气体引射高空模拟试验。冷气、固体和凝胶等姿控发动机亦可参照执行。

Test method for high altitude gas injection simulation of attitude control engine

QJ 20064-2011 导弹引信生产安全技术要求

本标准规定了战术导弹引信制造、试验、包装、运输、贮存与销毁的安全技术要求。 本标准适用于战术导弹引信的研制与生产。

Technical requirements of production safety for missile fuze

QJ 20048-2011 航天液体火箭发动机涡轮盘超声波检测方法

本标准规定了液体火箭发动机涡轮盘超声波检测的-般要求、检测要求和验收要求。 本标准适用于液体火箭发动机涡轮盘及涡轮盘饼材的超声波检测。其它盘类件的超声波检测可参照使用。

Ultrasonic testing method for turbine disc of liquid rocket engine

QJ 20033-2011 液氧煤油发动机试验后处理规定

本标准规定了液氧煤油发动机试验后处理的-般要求、交接和连接及处理程序。 本标准适用于液氧煤油发动机（以下简称发动机）试验后在试验台上的处理和返回制造厂后在清洗厂房的处理。

Post-treatment rules for LOX/Kerosene rocket engine test

HB 7774.5-2011 基于UG航空发动机建模要求.第5部分：管路

本部分规定了应用UG软件进行航空发动机管路敷设及二维制图的要求。 本部分适用于航空发动机管路敷设，非航空产品管路敷设设计可参照使用。

Requirements for aeroengine modeling in Unigraphics.Part 5: Piping

ANSI/NFPA 1125-2011 模拟火箭和高能火箭电动机的生产标准

1.1 Scope. 1.1.1* This code shall apply to the manufacture of model and high power rocket motors designed, sold, and used for the purpose of propelling recoverable aero models. 1.1.2 This code shall apply to the design, construction, and reliability of model and high power rocket motors and model rocket and high power motor-reloading kits and their components, and to the limitation of propellant mass and power. 1.1.3 This code shall not apply to the sale and use of the following: (1) Model rocket motors (covered by NFPA 1122, Code for Model Rocketry) (2) High power rocket motors (covered by NFPA 1127, Code for High Power Rocketry) 1.1.4* This code shall not apply to the manufacture, transportation, and storage of fireworks. 1.1.5 This code shall not apply to the manufacture, transportation, and storage of rocket motors by the United States military or other agencies or political subdivisions of the United States. 1.1.6 This code shall not apply to the assembly of reloadable model or high power rocket motors by the user. 1.1.7 This code shall not apply to the fabrication of model rocket motors or high power rocket motors by individuals for their personal use.

Code for the Manufacture of Model Rocket and High Power Rocket Motors

QJ 3307-2008 固体火箭发动机离心静止试验方法

Centrifugal static test method for solid rocket motors

QJ 3308-2008 固体火箭发动机纤维缠绕壳体容积增量测量方法

Measurement method of volume increment of solid rocket motor filament wound casing

QJ 3312-2008 固体火箭发动机静止试验推力矢量测量方法

Thrust Vector Measurement Method for Static Test of Solid Rocket Motor

QJ 2295A-2008 液体火箭发动机燃气发生器通用规范

General specification for gas generators for liquid rocket engines

GJB 6474-2008 导弹用复合材料高压环形气瓶规范

本规范规定了导弹用复合材料高压环形气瓶的要求、质量保证规定和交货准备等。 本规范适用于设计压力不大于60MPa、容积不小于0.4L的橡胶内衬和钛合金内衬导弹用复合材料高压环形气瓶。导弹用PBO纤维复合材料高压环形气瓶可参照执行。

Specification for high-pressure toroidal composite vessels for missile

DIN EN 14607-6:2006 航天工程. 机械. 第6部分: 烟火制造; 英文版本EN 14607-6: 2004

This part 6 of space engineering - Mechanical defines the requirements for the discipline of pyrotechnics engineering.

Space engineering - Mechanical - Part 6: Pyrotechnics; English version EN 14607-6:2004