航天器控制导引系统标准-分析测试百科网

NAVY MIL-C-81925-1973 C-9154/APM型检测控制设备

The equipment covered by this specification shall be forermediate shop use and shall facilitate the interface and test of the R-I623/APN Radar Receiver, the RT- 1028/APN-202 Receiver Transmitter, the MD-817D Modulator, and the RT-763D/APN-I54(V) Receiver Transmitter.

CONTROL, TEST HARNESS, C-9154/APM

ICS: 49.140
CCS: V73
发布: 1973-03-13
实施

ASTM E491-73(2010) 航天飞机热平衡试验用太阳模拟的标准实施规程

1.1 Purpose: 1.1.1 The primary purpose of this practice is to provide guidance for making adequate thermal balance tests of spacecraft and components where solar simulation has been determined to be the applicable method. Careful adherence to this practice should ensure the adequate simulation of the radiation environment of space for thermal tests of space vehicles. 1.1.2 A corollary purpose is to provide the proper test environment for systems-integration tests of space vehicles. An accurate space-simulation test for thermal balance generally will provide a good environment for operating all electrical and mechanical systems in their various mission modes to determine interferences within the complete system. Although adherence to this practice will provide the correct thermal environment for this type of test, there is no discussion of the extensive electronic equipment and procedures required to support systems-integration testing. 1.2 Nonapplicability8212;This practice does not apply to or provide incomplete coverage of the following types of tests: 1.2.1 Launch phase or atmospheric reentry of space vehicles, 1.2.2 Landers on planet surfaces, 1.2.3 Degradation of thermal coatings, 1.2.4 Increased friction in space of mechanical devices, sometimes called “cold welding,” 1.2.5 Sun sensors, 1.2.6 Man in space, 1.2.7 Energy conversion devices, and 1.2.8 Tests of components for leaks, outgassing, radiation damage, or bulk thermal properties. 1.3 Range of Application: 1.3.1 The extreme diversification of space-craft, design philosophies, and analytical effort makes the preparation of a brief, concise document impossible. Because of this, various spacecraft parameters are classified and related to the important characteristic of space simulators in a chart in 7.6. 1.3.2 The ultimate result of the thermal balance test is to prove the thermal design to the satisfaction of the thermal designers. Flexibility must be provided to them to trade off additional analytical effort for simulator shortcomings. The combination of a comprehensive thermal-analytical model, modern computers, and a competent team of analysts greatly reduces the requirements for accuracy of space simulation. 1.4 Utility8212;This practice will be useful during space vehicle test phases from the development through flight acceptance test. It should provide guidance for space simulation testing early in the design phase of thermal control models of subsystems and spacecraft. Flight spacecraft frequently are tested before launch. Occasionally, tests are made in a space chamber after a sister spacecraft is launched as an aid in analyzing anomalies that occur in space. 1.5 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practice for Solar Simulation for Thermal Balance Testing of Spacecraft

ICS: 49.140
CCS: V73
发布: 1973
实施

NAVY MIL-T-81527 B-1971 AWG-10方凳导弹控制系统测试集

The equipment listed herein shall be an integrated assembly of Contractok-Furnished and Government -Furnished Equipment to facilitate detailed maintenance of AN/AWG-10 Missile Control System (MCS) at the Intermediate Level where a sidebench is available.

TEST SET, MISSILE CONTROL SYSTEM, AWG-10 SIDE BENCH

ICS: 49.140
CCS: V73
发布: 1971-01-29
实施

ASTM E296-70(2010) 用于空间模拟器的电离压力计的标准实施规程

1.1 This practice provides application criteria, definitions, and supplemental information to assist the user in obtaining meaningful vacuum ionization gage measurements below 10−1 N/m2 (10−3 torr) in space-simulation facilities. Since a variety of influences can alter observed vacuum measurements, means of identifying and assessing potential problem areas receive considerable attention. This practice must be considered informational, for it is impossible to specify a means of applying the vacuum-measuring equipment to guarantee accuracy of the observed vacuum measurement. Therefore, the user''s judgment is essential so that if a problem area is identified, suitable steps can be taken to either minimize the effect, correct the observed readings as appropriate, or note the possible error in the observation. 1.2 While much of the discussion is concerned with the application of hot-cathode ionization gages, no exclusion is made of cold-cathode designs. Since a great deal more experience with hot-cathode gages is available and hot-cathode devices are used in the majority of applications, the present emphasis is fully warranted. 1.3 The values stated in inch-pound units are to be regarded as the standard. The metric equivalents of inch-pound units may be approximate.

Standard Practice for Ionization Gage Application to Space Simulators

ICS: 49.140
CCS: V73
发布: 1970
实施

NAVY MIL-W-3947 B-1969 导弹和航天器运载火箭的重量和平衡控制系统

This specification requires the establishment of a weight and balance control system to provide for the management of mass characteristics programs and to facilitate the preparation and submission of data as specified herein. The term 'Weight and BalanceIl as used herein is intended to include terms relating to mass and mass properties.

WEIGHT AND BALANCE CONTROL SYSTEM FOR GUIDED MISSILES AND SPACE LAUNCH VEHICLES

ICS: 49.140
CCS: V73
发布: 1969
实施

NAVY MIL-F-21572 VALID NOTICE 1-1964 引信功能控制装置AN/AWW-1(*)

This notice forms a part of Specification MIL-F-215?2(Wep) dated 15 J1Ay 1960 and shall constitute the covering page of the Specification

FUZE FUNCTION CONTROL SET AN/AWW-1(*)

ICS: 49.140
CCS: V73
发布: 1964-06-09
实施

NAVY MIL-T-23643 (2)-1964 AN/SRM系列目标控制系统测试设置

TEST SET, TARGET CONTROL SYSTEM, AN/SRM SERIES (AN/SRM-2, AN/SRM-3, AN/SRM-4, AN/SRM-5 AND AN/SRM-6)

ICS: 49.140
CCS: V73
发布: 1964
实施

NAVY MIL-T-23643-1963 AN/SRM系列目标控制系统测试设置

maintenance tests for Target Control Systems of the AN/SRW-4 Series. l 1.1 Scope. The equipment covered by this specification shall be capable of per- ~ The equipment covered by this specification shall be capable of per-

TEST SET, TARGET CONTROL SYSTEM, AN/SRM SERIES (AN/SRM-2, AN/SRM-3, AN/SRM-4, AN/SRM-5 AND AN/SRM-6)

ICS: 49.140
CCS: V73
发布: 1963-02-05
实施

NAVY MIL-F-21572-1960 引信功能控制装置AN/AWW-1(*)

The equipment covered by this specification shall be used in fighter- bomber type aircraft as a d-c and r-f fuze charging power-supply.

FUZE FUNCTION CONTROL SET AN/AWW-1(*)

ICS: 49.140
CCS: V73
发布: 1960-07-15
实施

NAVY MIL-F-18372-1955 设计,安装与测试飞行控制系统的一般规格

This specification covers the general requirements for the design, installation, and test of flight control systems for all types of piloted aircraft contracted for by the U. S. Navy. (Power plant controls are excluded).

FLIGHT CONTROL SYSTEMS: DESIGN, INSTALLATION AND TEST OF, AIRCRAFT (GENERAL SPECIFICATION FOR)