V35 航空器及其附件综合 标准查询与下载

GJB 6360-2008 武装直升机与机载武器相容性要求

本标准规定了武装直升机与机载武器相容性要求。 本标准适用于武装直升机与机载武器相容性设计和试验。

Compatibility requirements of armed helicopter and weapon system

GJB 6355-2008 军用直升机野战加油装置通用规范

本规范规定了军用直升机野战加油装置（以下简称加油装置）的通用要求。 本规范适用于军用直升机野战加油装置。

General specification for field refueling unit for military helicopter

GJB 6351-2008 军用直升机干扰弹发射装置通用规范

本规范规定了军用直升机干扰弹发射装置（以下简称发射装置）的通用技术要求、质量保证和交货准备等要求。 本规范适用于军用直升机干扰弹发射装置。

General specification for countermeasure decoy launchers of military helicopter

HB 7878-2008 空地导弹战斗部威力指标仿真试验方法

本标准规定了空地导弹战斗部威力指标仿真试验一般要求和试验方法。 本标准适用于空地导弹破片式战斗部、侵彻式战斗部威力指标仿真的设计、试验与评定。

Simulation experiment method for air-to-ground missile warhead power index

QJ 1659A-2008 控制系统仿真试验要求

本标准规定了导弹和运载火箭控制系统仿真试验的基本要求、试验流程与基本方法。 本标准适用于导弹和运载火箭控制系统仿真试验；其他领域仿真试验可参照执行。

Requirement for experiments on control system simulation

GJB 1015A-2008 军用飞机验证要求

本标准规定了军用飞机全尺寸研制期间验证试验要求和程序，是军用飞机验证的通用要求。 本标准适用于新型军用飞机或有重大改进改型军用飞机，是制定军用飞机验证试验大纲的主要依据之一。

Military airplane demonstration requirements

HB 7880-2008 动力三角翼飞行器通用规范

本规范规定了动力三角翼飞行器的通用技术要求、质量保证规定和交货准备等。 本规范适用于动力三角翼飞行器的设计、试验和验收。

General specification for airtrike

SAE ARP5783-2008 健康和使用监控指标监测的监控器

This recommended practice applies to vibration monitoring systems for rotorcraft and fixed-wing drive trains, airframes, propulsion systems, electric power generators, and flight control systems. It addresses all aspects of metrics, including what to measure, how to measure, and how to evaluate the results. The objective of this document is to provide recommendations for evaluating the performance of vibration based diagnostic algorithms in vehicle Health and Usage Monitoring Systems.

Health and Usage Monitoring Metrics Monitoring the Monitor

SAE AIR1064D-2007 制动系统动力学

The aircraft landing gear is a complex multi-degree of freedom dynamic system, and may encounter vibration or dynamic response problems induced by braking action. The vibratory modes can be induced by brake and tire-ground frictional characteristics, antiskid operation, brake design features, landing gear design features, and tire characteristics. The impact of this vibration can range from catastrophic failure of critical system components or entire landing gears, to fatigue of small components, to passenger annoyance. It is therefore important that the vibration is assessed during the design concept phase, and verified during the development and testing phases of the system hardware. This SAE Aerospace Information Report (AIR) has been prepared by a panel of the A-5A Subcommittee to present an overview of the landing gear problems associated with aircraft braking system dynamics, and the approaches to the identification, diagnosis, and solution of these problems. All pertinent system modes of vibration are described. In addition, facilities and techniques available for test and evaluation are presented and discussed, and useful references are cited. The terminology used is intended to be consistent with SAE AIR 1489, Aerospace Landing Gear Systems Terminology, but some terminology herein is not yet included in SAE AIR 1489. The panel members include representatives from major brake, landing gear, aircraft, and brake control system manufacturers. In addition, drafts of the document were circulated for input beyond the SAE to other experts in the field.

(R) Braking System Dynamics

SAE AIR1539B-2007 环境控制系统污染

This publication will be limited to a discussion of liquid and particulate contaminants which enter the aircraft through the environmental control system (ECS). Gaseous contaminants such as ozone, fuel vapors, sulphates, etc., are not covered in this AIR. It will cover all contamination sources which interface with ECS, and the effects of this contamination on equipment. Methods of control will be limited to the equipment and interfacing ducting which normally falls within the responsibility of the ECS designer. The purpose of this Aerospace Information Report (AIR) is to categorize sources of Environmental Control System contaminants, define the effects of these contaminants on occupants and equipment, and outline design features that can be used to control contamination in aircraft systems.

(R) Environmental Control System Contamination

IEC PAS 62396-3:2007 航空电子设备的过程管理.大气辐射影响.第3部分:优化系统设计调解大气辐射的单个事件影响(SEE)

This PAS is intended to provide guidance to those involved in the design of avionic systems and equipment．It builds on the initial guidance on the system level approach to Single Event Effects in IEC/TS 62396—1．considers some avionic systems and Provldes basic methods to accommodate SEE Sothat System Hardware Assurance levels may be met．

Process management for avionics - Atmospheric radiation effets - Part 3: Optimising system design to accommodate the single event effects (SEE) of atmospheric radiation

IEC PAS 62396-2:2007 航空电子设备的过程管理.大气辐射影响.第2部分:航空电子系统单个事件影响测试用指南

the purpose of this PAS is to provide guidance related to the testing of microelectronic devices for purposes of measuring their susceptibility to single event effects(SEE)induced by the atmospheric neutrons．Since the testing can be performed in a number of different ways using different kinds of radiation sources，it also shows how the test data can be used to estimate the SEE rate of devices and boards due to the atmospheric neutrons in the atmosphere al aircraft altitudes． The type of SEE data avaliable can be viewed from many different perspectives．As indicated． the SEE testing can be performed using a variety of radiation sources，all of which can induce stagle event effects in ICs．In addition，many tests are performed on individual devices．but some tests expose an entire single board computer to radiation fields that can induce SEE effects However,a key discriminator is deciding on whether existing SEE data is available that may be used，or whether there really is no existing data and therefore．a SEE test on the device or board of interest has to be carried out

Process management for avionics - Atmospheric radiation effets - Part 2: Guidelines for single event effects testing for avionics systems

IEC PAS 62396-5:2007 航空电子设备的过程管理.大气辐射影响.第5部分:航空电子系统热中子通量和影响的评估用指南

The purpose of this PAS is to provide a more precise definition of the threal that thermal neutrons pose to avionics as a second mechanism for inducing single event upset (SEU) in microelectronics．There are two main points that will be addressed in this PAS：1 ) a detailed evaluation of the existing literature on measurements of the thermal flux inside of airliners and 2)an enhanced compilation of the thermal neutron SEU cross section in currently available SRAM devices(more than 20 different devices)．The net result of the reviews of these two different sets of data will be two ratios that we consider to be very important for leading to the ultimate objective of how large a threat is the SEU rate from thermal neutrons compared to the SEU threat from the high energy neutrons(E>1 0 MeV)．The threat from the high energy neutrons has been dealt with extensively in the literature and has been addressed by two standards([2]1 in avioniCS and【1】in microelectronics on the ground)． The two ratios that this PAS considers to be so important are：1 ) the ratio of the thermal neutron flux inside an airline rrelative to the flux of high energy(>10 MeV)neutrons inside the airliner and 2)the ratio of the SEU cross section due to thermal neutrons relative to that due to high energy neutrons．These ratios are considered to be important because with them． once we know what the SEU rates are from the high energy neutrons for an avionics box a topic which has been dealt with extensively，such as【1】，then the additional SEU rate due to thermal neutrons can be obtained with these ratios．Thus．given the SEU rate from high energy neutrons，multiplying this by the two ratios gives the SEU rate from the thermal neutrons．The total SEU rate will be the combination of the SEU rates from both the high energy and thermal neutrons．

Process management for avionics - Atmospheric radiation effets - Part 5: Guidelines for assessing thermal neutron fluxes and effects in avionics systems

IEC PAS 62396-4:2007 航空电子设备的过程管理.大气辐射影响.第4部分:带高压航空电子装置和潜在单个事件影响的设计指南

This PAS is intended to provide guidance on Atmospheric Radiation effects on high voltage, nominally above 200 V.Aivionics electronics used in aircraft operating at altitudes up to 60000 feet(18,3km).It is intended to be used in conjunction with IEC/TS 62936-1.this PAS defines the effects of that environment on high voltage electronics and provides design considerations for the accommodation of those effects within avionics systems This PAS is intended to help aerospace equipment manufacturers and designers to standardise their approach to Single Event Effects on high voltage Avionics by providing guidance，leading to a standard methodology． Details are given of the types of Single Event Effects relevant to the operation of high voltage Avionics electronics．methods of quantifying those effects，appropriate methods to assist design and to demonstrate the suitability of the electronics for the applicatlon.

Process management for avionics - Atmospheric radiation effets - Part 4: Guidelines for designing with high voltage aircraft electronics and potential single event effects

NAVY MS33558 REV C REINST NOTICE 3-2007 航空器仪表标度盘数字和字母的标准形式

The activities listed above were interested in this document as of the date of this document. Since organizations and responsibilities can change, you should verify the currency of the information above using the ASSIST Online database at http://assist.daps.dla.mil.

NUMERAL AND LETTER, AIRCRAFT INSTRUMENT DIAL, STANDARD FORM OF

GJB 5962-2007 军用直升机分类

本标准规定了军用直升机分类准则。 本标准适用于军用直升机，民用直升机可参照使用。

Military helicopter classification

SAE AIR5683-2007 高性能1553的研究与开发

MIL-STD-1553 establishes requirements for digital command/response time division multiplexing (TDM) techniques on military vehicles, especially aircraft. The existing MIL-STD-1553 network operates at a bit rate of 1 Mbps and is limited by the protocol to a maximum data payload capacity of approximately 700 kilobits per second. The limited capacity of MIL-STD-1553 buses coupled with emerging data rich applications for avionics platforms plus the expense involved with changing or adding wires to thousands of aircraft in the fleet has driven the need for expanding the data carrying capacity of the existing MIL-STD-1553 infrastructure. This SAE Aerospace Information Report (AIR) will examine the characteristics of MIL-STD-1553 buses relative to their ability to carry data at significantly higher data rates when compared to MIL-STD-1553. Practical issues such as frequency response of 1553 bus networks and their components, signal-to-noise ratio, EMI constraints, and concurrent operation with existing MIL-STD-1553 will be discussed. Various telecommunication standards that could be appropriate for adaptation to MIL-STD-1553 buses are discussed. Early research by various companies into increasing the data carrying capability of existing MIL-STD-1553 buses is summarized as well as ongoing research. Potential applications that could benefit from increased bandwidth on MIL-STD-1553 buses are discussed.

High Performance 1553 Research and Development

DLA A-A-52304 VALID NOTICE 2-2007 刻字套及配件

The activities above were interested in this document as of the date of this document. Since organizations and responsibilities can change, you should verify the currency of the information above using the ASSIST Online database at http://assist.daps.dla.mil..

LETTERING SETS AND ACCESSORIES

ASTM F2500-07 无人驾驶飞行器系统(UAS)可视范围内飞行操作的标准实施规程

Safe operation of the unmanned aircraft is of the primary importance to the unmanned aircraft industry and for successful integration of unmanned aircraft with manned aircraft in civil airspace. Operators and pilots-in-command of unmanned aircraft systems shall comply with applicable Federal Aviation Regulations (14 CFR Part 43, 14 CFR Part 71, 14 CFR Part 73, 14 CFR Part 91, 14 CFR Part 93, and 14 CFR Part 99). This standard includes the minimum additional methods that should be followed by unmanned aircraft system operators, including pilots-in-command, on every visual range flight to ensure the safe operation of the aircraft and safety of people and property in the air and on the ground. This visual range flight operation standard shall be used in conjunction with appropriate unmanned aircraft system airworthiness and pilot qualification standards.1.1 This practice prescribes guidelines that govern the visual flight operation of unmanned aircraft systems in civil airspace in order to provide for the safe integration of unmanned aircraft flight operations with manned aircraft flight operations.1.2 This practice applies to those operations conducted for civil purposes other than sport or recreation that remain within the visual range of the pilot in command (see Terminology F 2395 for a definition of "visual range").1.3 This practice complies with the known rules, regulations, and public law available at the time of its publication. Should any conflict with a rule, regulation, or public law arise, the user must comply with rule and should notify ASTM of the conflict.This practice only prescribes accepted methods for visual range flight operation of unmanned aircraft systems.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 Unmanned Aircraft System (UAS) Visual Range Flight Operations

ASTM F2245-07a 轻型运动飞机的设计和性能用标准规范

1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” 1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight. 1.3 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 requirements prior to use.

Standard Specification for Design and Performance of a Light Sport Airplane