IEEE 292-1969 en Specification Format for Single-Degree-of-Freedom Spring-Restrained Rate Gyros《单自由度抑跳速率陀螺的规范格式》.pdf

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1、Copyright 1998 IEEE All Rights Reserved 1IEEE Std 292-1969(R2010)IEEE Specification Format for Single-Degree-of-Freedom Spring-RestrainedRate GyrosReaffirmed June 17, 2010Reaffirmed November 8, 2005IEEE Standards BoardReaffirmed June 7, 2000Approved November 17, 1986American National Standards Insti

2、tute Copyright 1969 by The Institute of Electrical and Electronics Engineers, Inc.This publication may be reproduced, without change, in part or in its entirety, provided that notice of its copyright bythe IEEE is included.iiAcknowledgmentThe Institute wishes to acknowledge its indebtedness to those

3、 who have so freely given of their time and knowledgeand have conducted experimental work on which many of the IEEE publications are based.This Specification Format and the Test Procedure for Single-Degree-of-Freedom Spring-Restrained Rate Gyros (IEEEStandards Publication No. 293) represent a group

4、effort on a large scale. They were generated as projects of the Gyroand Accelerometer Panel from May of 1962 to November of 1967. The Gyro and Accelerometer Panel (GAP)affiliated with the IEEE in May of 1965 and is now a part of the IEEE Aerospace and Electronic Systems Group. Atotal of 238 individu

5、als attended 30 GAP meetings while these documents were in preparation. Fifty-one individualsattended six meetings or more and provided 61 percent of the total attendance of 916. These people are listed here.K. L. BachmanW. E. BachmanR. BrodersonJ. T. BullA. T. Campbell, (GAP Chair, 1965)J. R. CashP

6、. B. Clark, (GAP Chair, 1967)V. B. CoreyR. A. CrawfordH. A. DinterK. E. EggersB. H. EvansH. L. FergerW. H. FickenT. A. FuhrmanG. A. GlaubitzJ. M. GoldenR. Goodstein, (GAP Chair, 1962, 1963)K. N. GreenJ. G. HawkinsCapt. F. J. HellingsE. HitscherichJ. A. Hogg, (GAP Chair, 1963, 1964)L. K. JensenJ. V.

7、JohnstonH. KehmJ. P. KochanA. M. Leeking, (GAP Chair, 1966)R. E. LevyJ. L. LuberJ. W. MaierR. H. MarcusF. B. MikoleitM. D. MobleyC. F. MorleyG. H. NeugebauerT. M. RankinH. RogallG. SchuetzmannN. F. SinnottH. E. SolandG. T. StarksC. StrangE. L. SwainsonC. O. Swanson, (GAP Chair, 1968)C. I. ThornburgR

8、. S. VaughnJ. VolkL. F. WarnockW. M. WeilA. E. WillisiiiIntroductionThis Specification Format has been prepared as a guidefor the preparation of a single-degree-of-freedom spring-restrained rate gyro specification. Prepared by the Gyro and Accelerometer Panel of the Aerospace Electronic SystemsGroup

9、 of the Institute of Electrical and Electronics Engineers, this format provides a common meeting ground ofterminology and practice for manufacturers and users.Two other documents, Aerospace Industries Association EETC Report No. 5 (Revision A), “Standard GyroTerminology,”* and IEEE Standards Publica

10、tion No. 293, “Test Procedure for Single-Degree-of-Freedom Spring-Restrained Rate Gyros,” have been utilized in the preparation of this format. This format will be limited toconventional single-degree-of-freedom spring-restrained rate gyros. A model equation is given in paragraph 6.3 forreference, a

11、nd is to be included in a specification only to the extent necessary.Table 1, on this page, lists various rate gyro design features for which this format is applicable. The table is notintended to make any suggestion regarding the selection of particular design features that might restrict the free

12、choiceof manufacturers.Blank spaces are provided in the Specification Format for the insertion of specific values. Brackets are used todesignate possible alternates. Boxed information is intended for explanatory purposes. Figures 1, 2, and 3 are to beused as a guide for the preparation of specific f

13、igures or drawings.The user is cautioned not to overspecify.Only those parameters that are required to guarantee proper instrumentperformance in the intended usage should be controlled.* Available from: National Standards Association, Inc.1321 Fourteenth Street N.W.Washington. D.C. 20005Table 1Rate

14、Gyro Design FeaturesPickoff Spin MotorDampingRegulation Self-Test TorquerRotor RotationDetector1. Variable reluctance (microsyn)1. Ac synchronous hysteresis (3-phase, 2-phase)1. Self-compensating1. Variable reluctance 1. Pulse2. Potentiometer 2. Ac induction (squirrel cage rotor) (3-phase, 2-phase)2

15、. Controlled temperature (heater controlled)2. Dc permanent magnet 2. Near sinusoidal3. Switch 3. Dc (with governor) 3. Uncompensated4. Other (optical, capacitance)NOTE The intent of this table is to indicate configurations of a spring-restrained rate gyro for which this specification format is appl

16、icable. The features may be employed in any combination.ivSPECIFICATION COVER SHEETRATE GYRO, _ DEGREES PER SECONDSpecification No. _DateProcuring Firm or Organization DatavCLAUSE PAGE1. Scope.12. Applicable Documents12.1 Specifications . 12.2 Standards 12.3 Drawings 22.4 Bulletins . 22.5 Other Publ

17、ications 23. Requirements 23.1 Description . 23.2 General Requirements 23.3 Performance . 33.4 Mechanical . 73.5 Electrical 83.6 Environmental 103.7 Reliability. 134. Quality Assurance Provisions .134.1 Classification of Tests 134.2 Acceptance Tests 134.3 Qualification Tests . 154.4 Reliability Test

18、s . 164.5 Test Conditions and Equipment. 174.6 Test Methods 174.7 Test Data Submittal 195. Preparation For Delivery.196. Notes .196.1 Intended Use 196.2 Ordering Data. 206.3 Model Equation 20Copyright 1998 IEEE All Rights Reserved1IEEE Specification Format for Single-Degree-of-Freedom Spring-Restrai

19、ned Rate Gyros1. ScopeThis specification defines the requirements for a single-degree-of-freedom spring-restrained rate gyro for aircraft,missile, spacecraft,_ applications. The rate gyro shall be capable of providing (dc, ac) voltage outputsproportional to angular rate inputs up to_ degrees per sec

20、ond, a switch closure(s) at angular rates (exceeding,less than)_ (+, -, )_ degrees per second.2. Applicable DocumentsThe following documents of the issue in effect on date of invitation for bid or request for proposal form a part of thespecification to the extent specified herein. In the event of an

21、y conflict between the requirements of this document andthe listed documents, the requirements of this document shall govern.2.1 Specifications2.1.1 Government2.1.2 Industry/Technical2.1.3 Company2.2 Standards2.2.1 Government2.2.2 Industry/Technical2.2.2.1 Aerospace Industries Association, EETC Repo

22、rt No. 5 (Revision A), “Standard Gyro Terminology,” June 1965.2Copyright 1998 IEEE All Rights ReservedIEEE Std 292-1969 IEEE SPECIFICATION FORMAT FOR SINGLE-DEGREE-OF-FREEDOM2.2.2.2 IEEE Standards Publication No. 293, “Test Procedure for Single-Degree-of-Freedom Spring-Restrained Rate Gyros.”2.2.3 C

23、ompany2.3 Drawings2.3.1 Government2.3.2 Industry/Technical2.3.3 Company2.4 Bulletins2.4.1 Government2.4.2 Industry/Technical2.4.3 Company2.5 Other Publications3. Requirements3.1 DescriptionThe major components of the rate gyro herein specified are a variable reluctance (microsyn), potentiometer,swit

24、ch,_ pickoff, a rotor, a hysteresis synchronous, induction, direct current,_ spin motor, and self-compensated, controlled temperature, uncompensated damping. The elastic restraint is accomplished by a mechanicalspring. A variable reluctance (microsyn), direct-current permanent magnet,_ torquer and a

25、 rotor rotationdetector are included as self-test features. See Figure 1.3.2 General Requirements3.2.1 PrecedenceIn the event of conflict among the purchase agreement, this specification, and other documents referred to herein, theorder of precedence shall be as follows:a) purchase agreement,b) this

26、 specification and its applicable drawings (see paragraphs 3.4.2, 3.4.6, and 3.5.1),c) other applicable documents (see Section 2.).Other applicable documents should be listed under the appropriate paragraph.Self-test features may or may not be required.Copyright 1998 IEEE All Rights Reserved3SPRING-

27、RESTRAINED RATE GYROS IEEE Std 292-19693.2.2 DefinitionsThe following documents define terminology used in this specification, and the test techniques that will be utilized todetermine unit compliance.3.2.2.1 : Standard Gyro Terminology, Aerospace Industries Association EETC Report No. 5 (Revision A

28、).3.2.2.2 : Test Procedure for Single-Degree-of-Freedom Spring-Restrained Rate Gyros, IEEE Standards PublicationNo. 293.3.3 PerformanceThe tolerances include a summation of manufacturing and test errors, and environmental effects. Any exceptions dueto environmental effects are listed under paragraph

29、 3.6.3.1.3.3.1 Input Limits_ /s.3.3.1.1 Limit StopsThe output angle shall be mechanically limited to an input limit value of _ /s.3.3.1.2 Mechanical OverloadThe rate gyro shall perform within specification after an angular rate of _ /s has been applied about the _axis, axes for _ seconds a total of

30、_ times. The rate gyro shall perform within specification after anangular acceleration of _ /S2has been applied about the _ axis, axes for _ seconds, a total of_ times.3.3.2 Gyro Scale Factor_ _ V/(/s).3.3.3 Natural Frequency_ _ hertz, not less than _ hertz.3.3.4 Damping Ratio_ _.The positive and ne

31、gative input limits need not be equal.A tolerance may be specified if necessary. The positive and negative limit stops need not be equal.Acceptable limits are sometimes specified graphically.4Copyright 1998 IEEE All Rights ReservedIEEE Std 292-1969 IEEE SPECIFICATION FORMAT FOR SINGLE-DEGREE-OF-FREE

32、DOM3.3.5 Run-Up Time_ seconds max to _ percent of full speed.3.3.6 Warm-Up Time_ seconds max.3.3.7 Self-Test TorquerScale Factor: _ _ (/s)/mA.Continuous Torquing Rate at _ C Ambient: _ /s max.Composite Error: _ percent max of the max continuous torquing rate.3.3.8 Rotor Rotation DetectorPeak Output:

33、 _ _ volts (at rated speed).Repetition Rate: _ times rotor speed.Pulse Width: _ seconds at _ volts (at rated speed).Total Output: _ volts root mean square minimum (at rated speed).Fundamental Signal: (Sinusoidal) _ percent of total output.Fundamental Frequency: _ times rotor speed.3.3.9 Rate SwitchS

34、witch Operation, increasing rate: normally open, closed contacts shall close, open at _ _/s within _ seconds.Switch Operation, decreasing rate: switch shall return to normal at _ _ /s within _seconds.3.3.10 Composite Error0 to _ /s: _ percent max of the output range.Sometimes minimum run-down time i

35、s also specified.For a variable reluctance torquer, the scale factor shall be _ _ (/s)/mA2.Sometimes nonlinear torquers are specified, in which case a table defining output versus input should be supplied.For the pulse output type.For near sinusoidal output type.Other types of Rotor Rotation Detecto

36、rs should be specified in accordance with their characteristics.This requirement is based on use as an erection cutout. Other uses may require a different form of specification.The rate switch may be the sole gyro output or an additional output. Sometimes contact bounce requirements arespecified.Cop

37、yright 1998 IEEE All Rights Reserved5SPRING-RESTRAINED RATE GYROS IEEE Std 292-1969_ /s to input limits: _ percent max of the output range.3.3.11 Threshold_ /s max.3.3.12 Resolution_ /s max.3.3.13 Hysteresis Error_ /s max.3.3.14 Zero Offset_ max.3.3.15 Acceleration-Sensitive Drift Rate_ (/s)/gmax._

38、(/s)/g2, max.3.3.16 Output Noise_ /s peak-to-peak max at frequencies _ hertz to _ hertz.3.3.17 Rate Sensitivity About the Spin Reference AxisAt zero rate input to the Input Reference Axis (IRA): _ (/s)/(/s) max.At _ /s input to theIRA: _ ( /s)/(/s) max.3.3.18 Rate Sensitivity About the Output Axis_

39、(/s)/(/s) max.Sometimes referred to as “signal modulation.” Usually specified at zero input rates. Other input may be specified.A function of the misalignment of the actual Spin Axis (SA) with respect to the Spin Reference Axis (SRA).A function of the misalignment of the actual SA with respect to th

40、e SRA and of gimbal output angle.Due to the actual SA not being perpendicular to the Output Axis (OA) as defined by the axis alignment provisions.Not usually specified, but added for consideration.6Copyright 1998 IEEE All Rights ReservedIEEE Std 292-1969 IEEE SPECIFICATION FORMAT FOR SINGLE-DEGREE-O

41、F-FREEDOM3.3.19 Angular Acceleration Sensitivity About the Output Axis_ (/s)/(rad/2) max.3.3.20 Reference ConstantsThese constants are for reference only. They are not specified independently because they may vary within theframework of the specification and also because they are difficult or imposs

42、ible to measure independently in acomplete gyro. Nominal values are listed.Rotor Angular Momentum: _ g cm2/S.Rotor Speed: _ r/min.Gimbal Output Angles at Input Limits: _ degree.Gimbal Moment of Inertia: _ g cm2.Elastic Restraint Coefficient: _ dyn cm/rad.Damping Coefficient: _ dyn cm s/rad.3.3.21 Po

43、larityShall conform to Drawing No. _, Figure 1, Outline Drawing No. _, Figure 2, Schematic Drawing No._, Figure 3.3.3.21.1 PickoffThe voltage from the pickoff secondary line-to-return shall be in-, out-of- phase, within the pickoff phase shift, withthe voltage from the pickoff primary line-to-return

44、 for positive input rates.3.3.21.2 RotorThe rotor shall rotate in the direction indicated by the SRA for ac excitation phase sequence, phase _ leadsphase _ leads phase _; dc positive voltage, spin motor line-to-return.3.3.21.3 Self-Test TorquerA positive rate indication shall result when the voltage

45、 from the control line-to-return is positive, negative.A function of gimbal moment of inertia and of rotor angular momentum. Numerically equal to gimbal moment ofinertia divided by rotor angular momentum.The positive and negative output angles need not be equal.For direct-current pickoffs this shall

46、 read: The voltage (or resistance) from the pickoff signal line to the pickoffexcitation line shall decrease for positive input rates.For a variable reluctance torquer this shall read: A positive rate indication shall result when the voltage from thecontrol line-to-return has the same, opposite pola

47、rity, phase as the voltage from the pattern line-to-return.Copyright 1998 IEEE All Rights Reserved7SPRING-RESTRAINED RATE GYROS IEEE Std 292-19693.3.22 Life3.3.22.1 Storage_ months.3.3.22.2 Operating_ hours.3.4 Mechanical3.4.1 Exterior SurfacesAll exterior surfaces must withstand the environment her

48、ein specified and the handling expected in the normal courseof operation, testing, and maintenance without deterioration that causes nonconformance to this specification.3.4.2 Outline and Mounting DimensionsShall conform to Drawing No. _, Figure 2.3.4.3 Gyro AxesThe IRA and the SRA are determined from the axis alignment provisions on the gyro case.3.4.4 Weight_ ounce, pound, gram,