SAE AIR 1810C-2003 Design Development and Test Criteria-Solid State Proximity Switches Systems for Landing Gear Applications《(R)设计 开发和试验标准 起落架应用的固体接近开关 系统》.pdf
《SAE AIR 1810C-2003 Design Development and Test Criteria-Solid State Proximity Switches Systems for Landing Gear Applications《(R)设计 开发和试验标准 起落架应用的固体接近开关 系统》.pdf》由会员分享,可在线阅读,更多相关《SAE AIR 1810C-2003 Design Development and Test Criteria-Solid State Proximity Switches Systems for Landing Gear Applications《(R)设计 开发和试验标准 起落架应用的固体接近开关 系统》.pdf(17页珍藏版)》请在麦多课文档分享上搜索。
1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there
2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2013 SAE International All rights reserved. No part of this p
3、ublication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497
4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.orgSAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/AIR1810CAEROSPACEINFORMATION REPORT AIR1810 REV. CIssued 1983-09 Revised 2003-01 R
5、eaffirmed 2013-10 Superseding AIR1810B (R) Design, Development and Test Criteria - Solid State Proximity Switches/Systems for Landing Gear Applications RATIONALE AIR1810C has been reaffirmed to comply with the SAE five-year review policy. 1. SCOPE:This document examines the most important considerat
6、ions relative to the use of proximity sensing systems for applications on aircraft landing gear. In general, the recommendations included are applicable to other demanding aircraft sensor installations where the environment is equally severe.1.1 Purpose:The purpose of this SAE Aerospace Information
7、Report (AIR) is to suggest specification, application, performance, and validation criteria for solid-state proximity sensing systems used for environmentally severe applications on aircraft landing gear.2. APPLICABLE DOCUMENTS:The following publications form a part of this document to the extent sp
8、ecified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this document takes precede
9、nce. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2.1 Military Publicati
10、ons:Available from DODSSP, Subscription Services Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094.MIL-C-85049 Connector Accessories, Electrical, Backshell, Environmental, Cable Sealing, StraightMIL-I-16923 Insulating Compound, Electrical, Embedding, EpoxyMIL-PRF-23586 Sealing Compo
11、und (With Accelerator), Silicone Rubber, ElectricalMIL-W-22759 Wire, Electric, Fluoropolymer-Insulated, FEP-PVF2, Lightweight, Silver-Coated, High Strength Copper Alloy Conductor, 600-VoltMIL-STD-461 Requirements for the Control of Electromagnetic Interference Characteristics of Subsystems and Equip
12、mentMIL-STD-704 Aircraft Electric Power CharacteristicsMIL-STD-810F Environmental Engineering Considerations and Laboratory Tests2.2 RTCA, Inc. Publications:Available from RTCA, Inc., 1140 Connecticut Avenue, NW, Suite 1020, Washington, DC 20036-4001.RTCA DO-160D Environmental Conditions and Test Pr
13、ocedures for Airborne Equipment3. DISCUSSION:3.1 Integral Electronics Proximity Switch Characteristics and Performance:Non-contacting proximity switches have been used on some aircraft as landing gear control and indication limit switches since 1965. There are two kinds of proximity sensing systems
14、in common use: proximity switches that have the switching electronics built into the sensing head and operate on the principle of eddy current losses, and proximity sensors that use variable reluctance and are connected to remote switching electronics contained in a separate electronics module. Prox
15、imity sensors produce an output that is a function of the distance between the sensor and its target, and this characteristic can be used to provide the maintenance technician with help during rigging. Proximity switches, on the other hand, only provide a bistable output target near or target far. I
16、ntegral Electronics Proximity Switch Characteristics and Performance:The following briefly describes the features and characteristics of the “one-piece” proximity switch.a. Installation: No separate electronics module is required.b. Reliability: Experience has demonstrated a Mean Time Between Failur
17、es (MTBF) of 5,000 to 50,000 hours for each switch, depending on exposure and application.c. Maintainability: Integral proximity switches are generally not repairable.SAE INTERNATIONAL AIR1810C Page 2 of 17_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduct
18、ion or networking permitted without license from IHS-,-,-3.1 (Continued):d. Sensing Range: From 0.050 to 0.5 inch as a function of effective sensor area or sensor diameter.e. Target: Any conductive material: however, the actuation point varies with different materials. Ferromagnetic steel generally
19、provides the maximum actuation range and should be utilized whenever possible.f. Temperature Range: From -55 to 71 C is normal. The upper limits can be extended to 125 C if the thermal interface is specified and controlled and adequately rated electrical parts are used.g. EMI Capability: No practica
20、l limitations except radiated susceptibility. Normal designs should be capable of operation in 20 volt per meter fields. Special designs that can operate in fields in excess of 300 volts per meter from 5 KHz to 4 GHz are presently in service. Aircraft HF, VHF and UHF transmitter bands should be test
21、ed.h. Shock: Current devices are capable of survival at up to 50 g shock levels. This limitation is dictated by electronic die attachment capability.i. Vibration: It is of the greatest importance that the mounting provisions account for the relative motion between the switch and target during exposu
22、re to vibration. The mounting hardware must be stiff enough to limit the change in the sensing gap to not more than 15% of the nominal gap when it is reacting the forces imposed by the switch during acceleration. The target must also be robustly mounted. Each installation should be designed to limit
23、 motion in both the head-on and slide-by directions during deflection of the structure to prevent false indications. Depending upon mechanical mounting features and possible resonances of individual installations, normal designs are capable of withstanding 25 to 75 g RMS equivalent vibration. Specia
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