NAVY MIL-STD-2102 A-1980 AIRCREW ESCAPE PROPULSION SYSTEMS VIBRATION AND SHOCK TESTS FOR《机组人员逃生推进系统颤动及震动测试》.pdf

《NAVY MIL-STD-2102 A-1980 AIRCREW ESCAPE PROPULSION SYSTEMS VIBRATION AND SHOCK TESTS FOR《机组人员逃生推进系统颤动及震动测试》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-STD-2102 A-1980 AIRCREW ESCAPE PROPULSION SYSTEMS VIBRATION AND SHOCK TESTS FOR《机组人员逃生推进系统颤动及震动测试》.pdf（14页珍藏版）》请在麦多课文档分享上搜索。

1、MIL-STD-21 OSAINAVY) 18. AUGUJ 1980 SUPERSEDING IIL-STD2102( NAVY) 20 FEBRUARY 1880. MILITARY STANDARD AIRCREW ESCAPE PROPULSPON SYSTEMS; VIBRATION AND SHOCK TESTS FOR THIS DOCUMWENT CONTAINS .fi PAGES. FSC 1377 Licensed by Information Handling ServicesMIL-STD-2102A(NAVY) 18 August 1980 DEPARTMENT O

2、F THE NAVY WASHINGTON, DC 20362 Aircraft Escape Propulsion Systems; Vibration and Shock Tests for MIL-STD-2102A(Navy) . 1. This Military Standard is approved for use by the Naval Sea Systems Comnand, Department of the Navy, and is available for use by all Department and Agencies of the Department of

3、 Defense. 2. Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Commanding Officer, Naval Ordnance Station, StandardizationlDocumentation Divison (Sol), Indian Head, Maryland 20640 by using the sel

4、f-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by ii Licensed by Information Handling ServicesLicensed by Information Handling ServicesParagraph CONTENTS Page 1 . 1.1 2 . 2.1 3 . 4 . 4.1 4.2 4.3 4.4 4.5 4.6 5 . 5.1 5.2 5.3 5.4 5.5 5.

5、6 5.7 5.8 6 . SCOPE . Scope . REFERENCED DOCUMENTS Issues of documents DEFINITIONS GENERAL REQUIREMENTS General . Test sample Unit inspection . Equipment . Vibration . Shock . DETAILED REQUIREMENTS . .Temperature condithning . Test system desfgn crfterfa Transmissibility evaluation . Test instrument

6、ation Vibration . Shock . Sequence of testing Test documentation NOTES . 6.1 Safety precautions . 6.2 Changes rom previous issue . 1 1 1 1 1 1 1 2 2 2 2 2 2 2 3 4 5 7 8 8 9 9 9 9 APPENDIX 10 . DATA REQUIREMENTS 10 Licensed by Information Handling ServicesMIL-STD-2102A(NAVY) 18 August 1980 1. SCOPE 1

7、.1 Scope. This standard establishes vibration and shock tests of aircrew escape propulsion systems (AEPS) to determine if the systems are constructed to withstand dynamic vibration and shock stresses expected during service use, handling, and transportation. 2. REFERENCED DOCUMENTS 2.1 Issues of doc

8、uments. The following documents of the issue in effect on date of invitation for bids or request for proposal form a part of this standard to the extent specified herein. SPECIFICATIONS MILITARY MIL-P-83126 Propulsion Systems, Aircrew Escape, Design Specification for MIL-A-8509 7 Aircrew Escape Prop

9、ulsion Systems (AEPS), Procurement Specification for STANDARDS MILITARY MIL-STD-810 Environmental Test Methods MIL-STD-45662 Calibration Systems Requirements (Gopies of specifications, standards, draings, and publications required by suppliers in connection with specifjic procurement functions shoul

10、d be obtained from the Government procuring activity or as directed by the contracting officer.) 3. DEFINITIONS (Not applicable) 4. GENERAL REQUIREMENTS 4.1 General. Vibration and shock tests shall be conducted during the design verification (Phase 11) and service release (Phase I) of aircrew escape

11、 propulsion system, hereinafter referred to as AEPS, as described in MIL-P-83126. Vibration tests shall be conducted for the preproduction phase as described in MIL-A-85097, test phases 1 Licensed by Information Handling ServicesMIL-STD-2102A(NAYY) 18 August 1980 4.1.1 Vibration test. Vibration test

12、ing is conducted to ascertain whether the AEPS is sufficiently constructed to withstand dynamic vibrational stresses expected during handling, transportation, and service use. 4.1.2 Shock test. Shock testing is conducted to ascertain whether the structural integrity and performance of the AEPS are s

13、atisfactory with respect to the mechanical shock environment expected during aircraft carrier landings. 4.2 Test sample. The number of AEPS to be vibrated and shock tested shall be in accordance with MIL-P-83126 or MIL-A-85097, as applicable. 4.3 Unit inspection, Visual and radiographic inspections

14、in accordance with MIL-P-83126 or MIL-A-85097 shall be performed on AEPS prior and subsequent to vibration and shock testing. 4.4 Equipment, The AEPS shall be attached to an exciter table by means of a rigid fixture capable of transmitting the required input vibratory acceleration. activity and shal

15、l apply excitation to the AEPS only through the attachment fittings unless otherwise approved. approved by the Government procuring activity. The configuration shall be approved by the Government procuring Any design change of fixture shall be 4.5 Vibration. The AEPS shall not sustain damage, initia

16、te, or sub- sequently fail to operate in conformance with applicable ballistic require- ments after being subjected to testing in accordance with 5.5 herein. 4.6 Shock. The AEPS shall not sustain damage, initiate, or subsequently fail to operate in conformance with applicable ballistic requirements

17、after being subjected to testing in accordance with 5.6 herein. 5. DETAILED REQUIRMENTS 5.1 Temperature conditioning. Prior to initiating a test that requires the AEPS to be at the specified temperature, each AEPS shall be conditioned for the required time interval specified by the Government procur

18、ing activity, and maintained within the required temperature tolerance for the duration of the test. 5.1.1 Temperature makeup time. Tf the temperature falls outside of the specified temperature limits for a period of more than five minutes, all testing shall stop and the AEPS shall be reconditioned.

19、 A reconditioning time of two minutes for every minute the AEPS spent outside the specified temperature envelope is required; hwever, the AEPS does not have to be reconditioned in excess of the initial conditioning time interval. 2 Licensed by Information Handling ServicesLicensed by Information Han

20、dling ServicesMIL-STD-2102A(NAVY) 18 August 1980 opportunity during vibration, the lockwires are to be visually inspected to ensure the bolts have nat loosened. f. g. h. Bolts shall not be loaded in shear for vibration where possible. Bolts loaded in tension shall be spaced no more than three inches

21、 Bolt lengths shall be minimized (for example, by bolt hole counterboring) where possible and practical, without adversely impacting the rigidity of the material belng joined by the bolts. No shear plane shall pass through a threaded section. are to be carried by bolt shanks installed in close fitti

22、ng (.O05 inch max clearance) bores/counterborec. Shanks are to fit in both matng parts .25 inch minimum. i. These loads j. It may be preferable to use two or three separate specialized orientation fixtures for holding the AEPS to the exciter table rather than using one fixture that can be used to ar

23、ient the AEPS in three mutually k. The fixture(s) shall be designed and/or procedures shall be used to minimize stress/ctrain placed on the AEFS during testing at the conditioned test temperature by thermal expansion differences between the AEPS and test fixture. 5.3 Transmissibility evaluation. . T

24、he vibratian/shock f ixture(s) shall be evaluated or transmissibility .prior to vibration or shock testing. 5.3.1 Test setup. The fixture(s) shall be bolted to the exciter table in the same manner proposed for the actual AEPS tests, but without attaching the AEPS, Input accelerometers shall, be plac

25、ed on the exciter table near the fixture. Output accelerometers shall be .placed at each fixture-to- AEPS attachment point in a manner that will simulate maximum actual input to the AEPS at each point. and output accelerometer circuits. obtained from the Government procur.ement activity, or its repr

26、esentative, prior to initiation of actual tests. actual test conditions except that frequency shall be varied at a rate not to exceed 1.00 octave per minute. plotted automatically as amplitude versus frequency on an X-Y plotter and continually monitored on an oscilloscope. If a fixture Is to be orie

27、nted on the exciter table in more than one-way,-a transmissibility test shall be required for each different Orientation. Transmissibility evaluation shall include, for each fixture configuration, all, axes of input, and both vibration and shock inputs. fixture acceptability. In the 0-2000 Hz freque

28、ncy range, the maximum transmissibility at the test item mounting point(s) is two (2), and at any point on the fixture is three (3). The maximum transverse motion must be less than the input. Tracking filters shall be used in both Input Approval of the test setup shall be Input acceleration shall si

29、mulate Output acceleration shall be The following guidelines shall apply to 4 f-, - - Licensed by Information Handling ServicesMIL-STD-2102A(NAVY) 18 August 1980 5.4 Test instrumentation. All test measurements shall be made with instruments whose accuraEy conforms to the following: a. The specified

30、tolerance, range, or limit shall be reduced by the amount o inaccuracy of thetest instrument used; all test measurements shall be made with instruments whose accuracies have been verified, within the year preceding test initiation, in accordance with MIL-STD-45662 and to the satisfaction of the Gove

31、rnment procuring activity; calibration records of all test equipment shall be maintained for a period of at least 1 year from date of test completion and shall be made available for review to the Government procuring actvity before test initiation and, if requested, afterwards (see Appendix). b. Ins

32、trumentation (all of which shall be provided by the contractor) shall be capable of measuring acceleration within +5.0% of measured accele- ration, frequency within k1.0% of measured frequency or except the temperature requirement. During this cycling, maximum displacement of the AEPS components sha

33、ll be determined. Based upon this information,.the location of three accelerometers shall be determined. Triaxial accelerometers shall then be mounted 3 hours in each of 3 axes. The input vibratory . acceleration shall be in accordance with MIL-STD-810, Figure 514.2-28, Curve A, with a Wo factor of

34、0.1G2/Hz. search and vibrated as specified hereafter. testing temperature. with MIL-STD-810, using Curve H of Figure 514.2-2, or Curve M of Figure 514.2-3 for AEPS used in helicopters, as determined by the Government procuring activity. All resonances shall be as noted. During the resonance survey,

35、a permanent continuous record of input vibratory acceleration shall be kept. but preference is for FM tape. During the resonance search, frequency shall be varied at a rate not to exceed 0.50 octave per minute. reasonance search shall be conducted with all axes of. the output accelerometers being mo

36、nitored. Based upon these nine outputs (minimum), the four resonant points (inaximum) shall be selected. Input vibratory acceleration shall be in accordance c This record may be made on an oscillograph, The output acceleration in any of the three AEPS axes to the input accele- ration as measured at

37、the excitation attachment Doints) exceeds a value quency band wherein the amplitude ratio exceeds 1.5 to 1 (as c.ontrasted to a clearly defined peak), this entire band width shall be considered one resonant point. considered a resonant band shall be 0.33 octave. If, also within this band width, ther

38、e are clearly defined amplitude peaks, the most: severe of these shall be considered an additional resonant point. The minimum frequency band width which shall be - I Licensed by Information Handling Services MIL-STD-2302A 33 H 7777733 0076745 b W MLL-STD-2102A(NAYY) 18 August 1980 5.5.2.4 Endurance

39、 vibration. Each AEPS shall be sinusoidally vibrated for 15 hours; 5 hours in each of three axes specified herein. One half hour of endurance vibration shall be performed at each resonant frequency for the maximum of four most severe resonant frequencies. The remaining vibration time shall be used f

40、or cycling. Input vibratory acceleration for each resonant frequency shall be in accordance with the acceleration and displacement of Curve H, Figure 514.2-2 of MIL-STD-810, or Curve My Figure 514.2-3 of MIL-STD-810 for AEPS used in helicopters, as determined by the Government procuring activity. de

41、tected in an axis, the AEPS shall be vibrated in accordance with the aforementioned provisions of MIL-STD-810. AEPS shall be 15 hours which shall Include resonant and nonresonant fre- quencies, as applicable. Endurance vibration of frequency bands which are classified as resonances in 5.5.2.1 shall

42、be conducted as continuous repetitive sweeps across that entire band up in frequency and return, at a rate not to exceed 0.50 octave per minute. vibrated at one time during resonance dwell. possible or necessary (or desirable from a scheduling standpoint) several AEPS may be frequency cycled simulta

43、neously, as long as the fixture and accelerometer i-nstrumentation on each AEPS meets the requirements specified herein and is approved by the Government procuring activity. gs shall be monitored every fifteen minutes on every accelerometer channel. If a significant divergence has occurred, stop the

44、 test and inspect the test set-up for an abnormality/failure. If no resonant frequencies are Total vibration time for the Only one AEPS shall be However, should it be The output 5.6 Shock. .Shock shall be transmitted to the AEPS through the attachment fittings to simulate service conditions. Each AE

45、PS shall receive a total of 1500 shocks. The duration of each shock shall be 10 +_ 2 milliseconds. a. Fifteen gs with shock applied in both directions, along the longitudinal axis of the AEPS (500 shocks each direction). b. Fifteen gs with shock applied in a direction perpendicular to the longitudin

46、al axis of the AEPS (500 shocks). 5.6.1 Photographic record. A photographic record of the shock wave form shall be kept, set of AEPS shocked in each axis; one photograph of one of the first shocks in each axis; one after approximately 250 shocks in each axis, and one near the 500th shock in each axi

47、s. Three photographs o the wave orm shall be taken for each 5.6.2 Shock wave form. The shock shall be of essentially a square wave (rounded corners) shape. 2.00 milliseconds as measured between the 10 percent and 90 percent levels of the peak acceleration. This rise and decay time will be a maximum of 5.7 Sequence of testing. Shock testing will be conducted immediately after vibration testing in each axis. 8 Licensed by Information Handling ServicesPreparing Activity: NAVY - OS Project Number: 13 7 7-N7 04 Licensed by Information Handling ServicesLicensed by Information Handling Services