AIR FORCE MIL-I-38263-1964 INDICATOR ATTITUDE ARU-17 A REMOTE《ARU-17 A型遥控飞行姿态指示器》.pdf

1、MIEI-38263 (USAF) 28 February i964 MILITARY SPECIFICATION INDICATOR, ATTITUDE ARU-l7/A, REMOTE 1. SCOPE 1.1 This specification covelsa the requirements for one type of remote attitude indicator, designated AFU-l?/A. 2. APPLICABLE Docms 2.1 The folluwing documents, of the issue in effect on date of i

2、nvitation for bids or request for proposal, form a part of this specification to the extent specified hereino SPECIFICATIONS Federal -P-416 Military NILE-!3106 m2s237 m3345 bB3358 M33586 Colors Identifbation Marking of U. S. Military Property Specifications and Stardards Order of Precedence for the

3、Selection a Electric Puwer, Aircraft, Characteristics and Utilization of Environmental Test Methods for Aero space and Ground Equipment Connector, mug, Electric, Straight Lamp, I.ncandescent,Singie -Contact ,Midget Flange Base, (T-1-3/4 Bulb) Case - Instrument, 5 x S-1/4, Standard Dimnsions for Nume

4、rals and Letters, Aircraft instrument Dial, Standard Form of Metals, Definition of DisBimiar (Copies of documents required by contractors in connection wi%h specific procurement functions should be obtaimd from the procuring activity or ais directed by ihe contracung officer.) 3. m-!rs 3.3. QUALIRCA

5、TI0N.- The inicator furnished under this specification shaU be a product which has been tested ani passed the qualification teslis herein, and has been listed on or approved for listing on the applicable qualified products list, 3.2 COMPONENTS,- The indicator shall consist of servo mechanisms for ac

6、tuating the pitch and roll gimbals, a dial display consisting basiically of a fixed miniature airplane, a bank angle dial, 8. bank index, a mecharxisir, mask, and a moving two-colored spheroid background with a horizontal liila dividing the two colors, a pitch trim knob, a roll trim knob, external z

7、eroing adjus-hents for pitch said roU, arrl a power-faure indicating device Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-I-382b3 bb m 997990b 013

8、8155 O m MIL-1-38263 ( USAF) 30501 RELIABILITY PROGRAMo- “he contractor shall establish a reliability assurance program and submit reports thereon in accordance With MIL4b27s42 o 3.s0X,l REIXABILITSo- During its service lifes the indicator shal have a minimum mean-time-between-failures (3fCI3F) of 3

9、26 hours at a 90 per- cent confidence levelo 3052 IONGEVITYO- The indicator shall have 8 minimum operating life of los0O hours before wearout failures occur or the equipment consistently fails to meet the specified MTi3F requirementse 3*5,3 1NTANABILJ.TY o- Maintainability shall be in accordance wit

10、h MILM-2692 e J0sa3 01 MAINTAINABILITY VmIFICATIONo- Maintainability verification shall be in accordance with the appendix of KCL-N-U. The confideaae level shall be 90 percent and the accuracy level shall be 65 percento requirement for determination of an shall be such that when it I8 Illwm%aa%erd w

11、ith externel QP Internal light OUWQ the light will be sufficiently diffused to civoid highlight and mrktnga will be olear and shwp when viewed under these conditione. 3.8.1 MINIATURE AIRPUNE,- The miniature airglane ehall be in aocorance with figure 2. The mar edge shall be within 1/16 inch of the s

12、pheroid surface, The wings shall. follow the oumature of the spheroid with the top edge of the wings and center dot tilted back approximately 49 to facilitate night lighting. The miniature airplane shall be fixed directly to the cover glass at the bottom two pointa of the W. attaching areas shall no

13、t exceed 1/8 inch diameter each and shall be color No. 37038, The W on the miniature airplane need not have a black border as shown on figure 2; however, the white portion of the W, wings, and dot shall be separated by an area of color Nor 37038 of sufficient width to show contrast, subject to the a

14、pproval of the procuring activity, white areas of the miniature airplane shall be color Nol 37875, The The 3.862 BANK ANGLE DIAL*- The bank angle dial shall be in accordance with figure 2. edge (larger !iameter) of the saale surface against the cover glass. %cgle markingSi of the dial shsLL be color

15、 No, 37875, It shall be attached to the instrument case with the front The f 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-1-38263 (USAF) . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-

16、1-38263 bb M 9779706 OL3L5 b Y O Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-1-38263 (USAF) 3,8,3 BANK INDEX,- The bank index shall be in accordance with figure 2, but shall not move with pitch deviations, index shaU. be .in a plam which is p

17、arallel to the cover glass, plane shall be ;in the same plane as the front surface of the small diameter of the bank dial within tn pitch so that during a dive maneuver, the horizon line will go above the miniature amlane and during a climb maneuver, the horizon line will go below the miniature airp

18、lane, accordance with figure 3, 0,035 (nominal) inch for each degree of pitch change. markings shall be in accordance with figure 3 and the following require- ments, The spheroid shall be internally iilwninated. The roll axis shall be perpendicular to the face of the indicator The spheroid shall be

19、in The surface of the spheroid shall move The colors and 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-1-58263 (USAF) 4-1 I- I _- a. I - 3,566 IY/d O .I . Provided by IHSNot for ResaleNo reproduction or networking permitted without license fr

20、om IHS-,-,-MIL-1-38263 66 W 9997906 0338363 b W MIL-1-38263 (USAI?) 3,8,5,1 COLORS AND MARKINGS.- Above the horizon line, the spheroid shall be light gray, color No, 36373, and all markings shall be color No, 37038, alternating spaces as shown on figure 3, Below .the horizon line, the spheroid shall

21、 be color No, 37038 and all markings sha21 be color No. 36440, The lengths of the major pitch lines shall be as follows: The horizon Line shall be colors No. 37038 and No, 37875 in O (Horizon line) - 0 - - - = - - - - Width of sphere 10 I - 0 - - - - - - I 2-1/2 inches zoo - I 2-3/8 inches 30“ -? .

22、.I . I a - -. I 2-1/4 inchei 40“ -. I I - - - I - I - 21/8 inches SO0 - I - - - - - I 2 inches I I o . . I I - I I 600-.-. 1-7/8 inches 70Q-Lrr-r-irrri- 1=3/4 inches 800 - II o I ., I - - - - - ) Circle 85“ u .s - - - 0 - - - - - - Soliddot The center of the solid dots shall be the go pitch position

23、 and from center to center shall represent 180. of pitch indication. indication shall be linear over the full range and shall be spaced over L80a of the spheroid surface. hand side of the indicator and marked b accordance with figure 1, shall be incorporated for adjusting the position of the spheroi

24、d, shd-1 be color No. 36231. The reference mark on the knob shall be color No, 37038 and shall extend across the end of the knob and continue along .the side to a point on the knob that h adjacent to the circular mark on the case at the zero pitch trjm position. No, 37875. The knob shall have approx

25、imately 1/2 turn of freedom in the clockwise (ow) direction ard l/4 turn of freedom-in the counterclockwise (ccw) direction from the pitch trim position, direction shall be limited by a position stop, When the knobis rotated to the stop in the cow direction, the spheroid shall rotate ia deflect the

26、horizon line upward to indicate an 8 minimum dive. When the knob is rotated to the stop in the cw direction, the spheroid shall rotate to deflect the horizon line downward to Zxdicate a 16 minimum climb. The servo system shall operate properly for any pitch trim adjUBtInentb The knob shall have suff

27、icient friction to remain fixed when set krt shall move smoothly without evldence of binding or erratic motion when being adJusted. The pitch trim circuit shall be so designed that if three ARU-l7/A indicators are comcted to a single transmitter (pitch and roll), varying the pitch trim on any one of

28、 the indicators will not affect the other indicators by more than 1/4 in the pitch and mll axes. The pitch 3.9 PITCH TRIM KNOB.- A pitch trim knob, mounted on the lower right- The knob This mark shall be color The freedom in each - -. - - LO -_ _ -_ Provided by IHSNot for ResaleNo reproduction or ne

29、tworking permitted without license from IHS-,-,-MIL-1-38263 66 W 7777706 0138162 8 MIL-1-38263 (USAF) 3*10 ROLL TRIM KNOB.-. The position of the spheroid shall be adjustable by mans of a roll trim knob mounted on the upper right-hand side of the indicator face ami marked in accordance with figure 1.

30、 The reference mark on the knob shall be color No. 37038 and shall extend across the end of the hob ad continue along the side to a point on the knob that is adjacent to the fulcrum mark on the case at the zero roll trim position, color No. 36231. bank when rotated to its extreme cw postion and 8“ t

31、o 20 right bank when rotated to its extrem ccw position. This mark shall be color No. 37875, ani the knob shall be The knob shall position the bank index 8 to 20 left 3.U ZEROING ADJUSTMENTS.- Means shall be incorporated to externally adjust the position of the spheroid, 23 minimum, in pitch and rol

32、l. The initial setting of the pitch and roll indication at the time of delivery of the indicator shall indicate zero pitch and roll within 51/2O when thr indicator is connected to a test transmit-lr67, However, the 3.lS.l PNS.- Pins K and L of connector Ji. shall be utilized for lighting purposes, t

33、he. case. The lighting leads, or lead, shall not be grounded to 3.25.2 RESISTORS.- Resistors shall not form any part of the lighting system; hwever, available space shall be allocated for ncorporating a dimming resistor, In case8 where resbtors are approved, they shall be in series with the entire l

34、ighting rJ5rcui.t. 3.15.3 PRI31E: STANDARD,- Using parts that are identical to the parts to be used in production ndicator, an indicator shall be constructed which meets all display requirements of MU-E-25467 except for parts that affect the lighting design, This indicator may be a lighted model. Th

35、e indicator model and recorded lighting data shall be submitted to the procuring activity for approval and, if approved, shall be certified as aprime standard, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.15.3.1 PRIME STANDARD LIFE.- A minimum o

36、f 12 average areas covering all representative areas of the face of the prime standard shall be meamred for bright-ness and color prior to submission and at least every 50 hours of operation thereafter. in color in any two or more of these areas, using the initiai data as reference, shall void certi

37、fication of the prim standard. A change of *20 percent in brightness or *5 percent 3.15.4 LAMp.- A lamp conforming to FE25237 shall be used as the light source. 3.16 ATTITUDE ACTUATION.- The spheroid shall be rotated about the pitch and roll gimbal axes by mans of geared servo motors until a null is

38、 attained between the control transformer synchros on the indicator axes and the trans- mitter synchros in the pitch alid roll displacement reference. The fseedom of the spheroid rotation shall be unlimited about the roll arid pitch axes. The gear design shall be such as to eliminate play and backla

39、sh, be no hunting or jumping movement in the indicator when it is properly connected to a vertical gyro control. 70 percent critically damped arid shall not lag the signal source by more than 10 at maximum rates of servo operation. There shal The indications shall be approximately 3.16.1 SYNCHRO CON

40、TROL TRANSFORMER.- The synchro control transformer on the pitch and roll axes shall be high-impedance synchros, Eclipse Pioneer type AY 500-5, or equivalent. When four indicators are connected to a single test transmitter per axis, there shall be no noticeable change in performance under the followi

41、ng conditions: a. When the nominal no-load output of a transmitter drops 0.72V b. When the phase angle between the transmitter rotor excitation vol.tage and the stator leg-bo-leg voltage changes to 3.5. 3.16.2 STANDARD TEST TRANSMITTER.- The standard test transmitter shall consist of an Eclipse Pion

42、eer type AY 200-1, or equal, high-precision synchro with minimum and known el”r0r.s. The rotor of the synchro shall be settable and rotatable through 360”. These settings shall be readable to within 6 minutes of arc arid each degree of scale marking shall represent lo of synchro rotor rotation with

43、the scale marked from Oo to 360 and so-affixed to fie synchro as to be readable as specified herein, The following method shall be used to calibrate the standard test transmitter: a. The rotor leads shall be designated as H and C ad one stator lead designated as Z and connected to C. When 26V is app

44、lied across H and C (C being grouni.), the scale shall be positioned on zero when the voltage across H and X is maximum and the voltage across the remaining two stator leads (X and Y) is minimum. decreases for increasing numbers of the scale The voltage across X and 2 increases before it Provided by

45、 IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-I-382b3 bb W 977990b CIL38167 7 W MIEZ-38263 (UAF) b, Synchro excitation - The test transmitter rotor shai.1 be excited from the same pmer supply voltage that operates the indicator. 5.1; shall be so applied t

46、hat the voltage from rotor lead C to rotor lead H is Ln phase with the voltage from pin.A to pin B of the indicator connector 51 with lead C and pin A cornon. 3.16.3 PITCH AND TruLL SENSING.- When the standard liest transmitters, set at a scale reading of 180, are connected to the Indicator as shown

47、 in table Z, the indication shall drive to gero pitch and roll. scale setting of the test transmitters shall result in right bank and climb indications, Decreasing scale setting shall result in left bank and dive indicatbns , ncreashg 3.17 indicator isha11 be such that in the process of follmp, the

48、Mications h pitch or bank will move smoothly without hunting, oscillating, or jumping greater than 1/4“ total amplitude in pitch or total amplitude in bank when connected to a standard test transmitter. There shall be no sustained electrical or mechanical oscillations in either axis greater than 1/4

49、“ total amplitude at any indication. The servo mechanism shall be 70 to 100 percent damped and shall not lag the signal source by more than 10 at maximum rate of servo operation, FouotnrP OPERATION,- The electrical and mechanical design of the 3.11,l FoLLWUP RATE.- The rate at which the motors drive the gimbal