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

24、l designs are limited only by the capability of the microcircuits and other components used in the design.j. Moisture/SWAMP Environment: The SWAMP is defined as a “severe wind and moisture problem” area. Experience has shown that moisture ingestion is the principal cause of premature failure of inte

25、gral electronics proximity switches. Sealing integrity is severely tested by the rapid temperature and pressure changes associated with the SWAMP landing gear environment. It is strongly suggested that development and qualification test programs include the test parameters outlined in Section 5. Pro

26、duction testing requirements should also consider the inclusion of a cycled high stress burn-in period (“Shake and Bake”) to improve reliability by weeding out “infant mortality” failures.SAE INTERNATIONAL AIR1810C Page 3 of 17_ Copyright SAE International Provided by IHS under license with SAENot f

27、or ResaleNo reproduction or networking permitted without license from IHS-,-,-3.2 Separate Electronics Proximity System Characteristics and Performance:Included here are the characteristics of the typical “two-piece” proximity switch system.a. Installation: Electronics modules, usually packaged toge

28、ther in a standardized Air Transport Radio (ATR) proximity electronics enclosure, are required to be located in an environmentally controlled aircraft area. Any required logic, output drivers, and Built-In-Test (BIT) circuitry are usually included in the same enclosure. Point to point wiring, within

29、 the enclosure, is preferred for ease of maintenance and modification if space constraints allow.b. Reliability: This type of system has demonstrated a field MTBF of 180,000 to 300,000 hours for each switch channel (one sensor together with its electronics module). The reason for the large improveme

30、nt in reliability, over the one-piece switch, is that the electronics module is housed in a controlled aircraft environment and the sensor is a low impedance device that is inherently less sensitive to moisture ingestion.c. Maintainability: Electronics modules are repairable and replaceable without

31、disturbing the sensor installation/rigging. Sensors are non-repairable, but can be replaced without adjustment of the electronic module.d. Temperature Range:1. Sensor: Normal -55 to 85 C or -65 to +100 C. The range may, with special design effort be extended to -200 to +450 C.2. Electronic Module: -

32、40 to +71 C.e. Sensing Range: Similar to integral electronics unit.f. Target: Must be a ferromagnetic material such as 4130, 4340 or 17-4PH steel. For increased switching range and sensitivity, specialty high permeability alloys may be used. This system has the inherent capability of “seeing through

33、” non-magnetic metals such as 300 series stainless steel and titanium.g. EMI Capability: The same as integral electronic switches except that care must be taken to ensure that radiated emissions requirements are met on the wires connecting the sensor to the electronics module. Sensor wiring is usual

34、ly a twisted pair or triple for improved EMI rejection.SAE INTERNATIONAL AIR1810C Page 4 of 17_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.2 (Continued):h. Shock and Vibration:1. Sensor/Target

35、: As with proximity switches, it is of great importance that the mounting provisions account for the relative motion between the sensor and target during exposure 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 w

36、hen its reacting the forces imposed by the switch during acceleration. The target must also be robustly mounted. Each installation should be designed to limit motion in both the head-on and slide-by directions during deflection of the structure so that false indications are prevented. No practical l

37、imitations exist except with mounting features that are unique to individual designs. Switching repeatability is enhanced by rigid, well-designed installations.2. Electronics Module: The normal electronics bay environment should not be exceeded without special care.i. Moisture/SWAMP Environment: The

38、 sensor in the separate electronics system is a low impedance device that is not inherently sensitive to moisture ingestion. However, moisture penetration can cause long-term deleterious effects resulting from corrosion and freeze-break failure.4. SUGGESTED PRACTICES FOR DESIGN, DEVELOPMENT AND APPL

39、ICATION:4.1 Materials:a. All exposed parts must be of corrosion resistant or protected to resist corrosion and structurally capable of surviving in the wheel well environment. Non-metallic materials should be resistant to the effects of ozone and ultra-violet radiation.b. Abutting dissimilar metals

40、should not be used when exposed to wheel well conditions without special precautions.c. All potting and encapsulation compounds that are exposed to wheel well conditions must be unaffected by moisture. Suggested criteria are those of MIL-I-16923 for epoxies, and MIL-PRF-23586 for silicones. Potting

41、voids should be eliminated since they tend to collect contaminants and moisture. Hermetic techniques that eliminate exposed potting and encapsulation materials are preferred.d. In order to maximize reliability, the order of preference in the construction of solid state electronic circuitry is as fol

42、lows (the most preferred construction listed first and the least preferred last).1. Monolithic microelectronic integrated circuits;2. Thin film, thick film, or hybrid microcircuit devices3. Discrete parts.e. External components and surfaces should not be susceptible to, or damaged by aircraft fuel,

43、hydraulic fluids, disinfectants, de-icers or cleaning agents.SAE INTERNATIONAL AIR1810C Page 5 of 17_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4.2 Construction:a. Mounting: The sensor mounting

44、 means should prevent all relative motion between the switch and the structure to which it is attached. Proximity switches or sensors are not sensitive to mounting attitude. If units are to be installed within one inch of each other, care should be taken to ensure that the effects of one on the othe

45、r are understood and acceptable. In addition, the effects of surrounding metal structure must be considered.b. Electrical Termination: Most switches or sensors include twisted “pigtail” leads or shielded cables. The aircraft manufacturer usually specifies the type and length of wire or cable. Howeve

46、r, experience has shown that sensor wiring that meets the following guidelines, when located in the wheel well environment, will provide satisfactory service:1. Size:(a) 20 gauge minimum for twisted 2 or 3-wire cable.(b) 22 gauge minimum for twisted, shielded and jacketed multi-wire cable.2. Wire: H

47、igh-strength copper alloy with silver plating is generally preferred. Wire insulation systems that use flexible, homogenous modified Teflon of medium weight, are also generally preferred over lightweight multi-wall, stiff, springy constructions. MIL-W-22759 is a reasonable, basic wire specification. For installations where the sensor harness has to be very flexible (e.g., routing the sensor wire in conduits that fold with a side brace mechanism or that are routed over the torque link apex), a wound (w