1、MIL-I-83034B Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Oklahoma City Air logistics Center/NMEOR, Tinker AFB OK 73145-5990 by using the standardization Document Improvement Proposal (DD For
2、m 1426) appearing at the end of this document or by letter. L - SUPERSRDING MIL-I-83034A 25 April 1972 MILITARY SPECIFICATION INDICATOR, HORIZONTAL SITUATION AQU-A/A This specification Is approved for use by all Departments-and Agencies of the Department of Defense. 1. SCOPE 1.1 situation indicator,
3、 designated AQU-6A/A. Scope. This specification covers the requirements for one type of horizontal 2. APPLICABLE 2.1 Government documents. WARNING. Thle document contains technical data, whose export is restricted by Ehe Arms Export Control Act (Title 22, U.S.C., Sec. 2751 et 3.) or Executive Order
4、12470. Violations of these export laws are subject tosevere criminel penalties. DESTRUCTION NOTICE. For classified documents, follow the procedures in DoD 5200.22-M Industrial Security Manual, Section XI-19 or DoD 5200.1-R, Information Security Program Regulation, Chapter IX. For unclassified, limit
5、ed documents, destroy bv any method that will prevent disclosure of contents or reconstruction of the document. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-H IL-I -830348 SPBCIPICATIONS Federal PPP-B-60 1 PPP-B-636 Hi li tarp MIL-P-116 MIL-E-54
6、00 HIL-C-554 i HIL-S-7 762 WIL-il-77 93/6 MIL-A-8625 HIL-C-14806 MIL-L-27160 MIL-B-27497 STANDARDS Federal FED-STD-595 Military MIL-STD-100 HIL-STD-105 HXL-STD-129 MIL-STD-130 MIL-STD-4 54 MIL-sTD-46 1 MIL-STD-6 6 2 MIL-STD-4 71 MIL-STD-704 HIL-STD-781 MIL-Srn-8 1 o HXL-STD-838 HIL-STD-889 HIL-STD-9
7、 70 IS33558 Boxes, Wood , Cleated Plywood Box, Shipping, Fiberboard Preservation, Method Of Electronic Equipment, Airborne, General Specification Por Cbedcal Conversion Coating 00 Aluminum Alloys Screw Threade, Standards, Optimum Selected Series: General Specificatlon For Meter, Time Totalizing, Min
8、iature, Digital, 115 Volts, 400 Hz Anodfc Coattngs, Por Aluminum And Aluminum Alloy6 Coatings, Reflection Reducfng, Por Instrument Cover Glass And Lighting Wedges Lighting, Inetrument, Integral, White, Genetal Specification For Bearings, Jewel, Sapphire or Ruby Synthetic . Color Engineering Drawing
9、Practicer Sampling Procedures And Tables Por Inspection By Attributes Harking Por Shipment And Storage Identification Phrking Of U.S. Hiltary Property Standard General Requirements For Electronic Equipen t Electromagnetic Emfeeion And Requirements For The Control Interference Electromagnetic Interfe
10、rence hasuremeat Of Susceptibility Of Electromagnetic Charactt ria tice, I U Haintainablty Demonutration Aircraft Electric Power Chriractcrlrtic Reliability Tertr Exponential Distribution Environmental Teet Methode Lubrication Of Miitary Equipment Dfsclfdlar Metala Standard and Specification, Order
11、Of Preference Por The Selction Of DOD aterirl Procedure Por Development And Numerale the forw.ird face of bearing pointer No. 2 shall be 0.03 to 0.04 inch fonsard of plane A; the forward face of bearing pointer No. 1 shall be 0.04 to 0.05 inch foward of plane A; the lubber line shall be 0.07 inch fo
12、rward of plane A; the forward face of the courae arrow and deviation bar shall be 0.18 inch forward of plane A; and the fixed airplane reference shall be 0.25 inch forward of plane A. The first set of deviation dots shall be .O7 inch forward of plane A and the second set shall be 0.03 inch forward o
13、f plane A. The forward face of the TO-FROM pointer and deviation alarm flags shall be not more than 0.025 Inch behind plane A. dimensions given are design center values. The forward edge of the heading marker shall be 0.01 inch forward of The 3.11.1 Visibility. All marklnge, course counter, distance
14、 readout, compass card graduations, heading marker, and be8rlag pointers shall be clearly visible and 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-i-83034B readable when viewed gt a distance of 2 feet from the front of the indlcator at an 31
15、evation angle of 30 from the top of the covcrlass and 4 inchce to the right or left of the Instrument centerline. hundreds digit of the distance readout shall be vigible when vieved at a distance of 7 feet in front of the indicator at an angle of 20 to the right or left of the sides or the coverglas
16、s and 4 inches above or below the instrument centerline. )i The unlts digit of the course counter and the - 3.12 Standard synchro test transmitter. A standard calibrated svnchro with minimum and known errors shall be orovided and shall be 8n Ecliqe-Pioneer type AY201-1, or equal, high-precision tran
17、smitting synchro. A O to 360 dial clampeg to the rotor o the synchro shall be settable, rotatable, and readable through 360 of rotation to ;i ainutes of arc. The following procedure shall be used to calibrate the test 8 ynchro: 1,lZ.l us 2 and connected to C. oUhen 26V is applied to R and C (C being
18、 ground) the dial ahall be positioned. on O and clamped to the rotor when: The rotor leads shall be designated as A and C and one stator lead desiqnated a- The voltage acroes H and Y is maximum b. The voltage across the remaining two stator leads (X and Y) is minimum c. The voltage across X and Z in
19、creases before t decreases for increasinjz heading indication of the dial. The voltage X to Z and Y to 2 shall be in phase with the excitation voltage C to H when the dial reading is zero. For increasing heading Indication of the dial, the voltage X to Y shall increase and be in phase with the excit
20、ation voltage C to H. The test transmitter will be set at an index reference of zero to a positive rotation reference XYZ. 1 ,13 Presentation. The presentation shall be in accordance with inure 2. 3-14 Aircraft heading. and shall be read under the fixed lubber line located at the top of the indicato
21、r rwe as shown on figure 2. The aircraft heading shall be displayed on the azimuth ring 3.1401 br a high impedance type EP AY500-5, or equal, vhich shall receive an input from a synchro device similar to the test transmitter described in 3.12. Any CTwlth the same general impedance of the stator wind
22、ings aa a type EP AYS00-5 may be utilized. Azimuth ring signal input. he input synchro control transformer (CT) shall 3,14.2 Azimuth ring servo system. The servo followup system, consisting of a CT, d-c torquer motor, and amplifier, shall drive the azimuth card and rotor or the Input CT to a null. b
23、etween Oo and 60 There shall be no appreciable hunting oc oscillating in the servo system while the input compass signal Is changing or stationary. Ilne to within +0.500 of the position of a calibrated synchro. The design of the azimuth card loop shall rerult in operation such as would be achieved i
24、n the svstem shown on figure 4. The functional design shall k a8 shown in the block diagram on firnte 4, except that d-c torquers and position feedback shall be used. Itorhall be capable of rcceivinu a chanRe of heading at any rate per second without hunting. The sew8 system ehall position the headi
25、ng Indication under the lubber 3,14.3 Aruth card control tranrfomer zero. wlth a positive rotation reference at an index reference of 270 OF the azimth card CT as specified on figure 4 and the excitation voltage of the i3t transmltter C to H In phare with the power input pin M to pin BB: The azimuth
26、 cart CT ohal be zeroed 1 With the XYZ leade ! 10 I I I I w Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 -5.235 COURSE 4 DEVIATION AIRPLANE sviureouwim DOT(WHltE) LETTERS: I i00 R TO BOTTOM EDGE; .230 HIGH OVERALL; .O40 LINE WIDTH. NUMERALS: 1.1
27、00 R TO BOTTOM EDGE) .I88 HIGH OVERALL; .O30 LINE WIDTH. IOo LINES: .O31 LINE WIDTH, LENGTH .i25. 2. AND 8OLINES: ,010 LINE WIDTH, LENGTH .062. 4. AND 6. LINES: .OK) LINE WIDTH, LENGTH .IOO. NUMERALS AND LETTERS SHALL CONFORM TO MS33558. DIMENSIONS IN INCHES; TOLERANCS: DECIMALS 2 .OlO, FRACTIONS) i
28、 I iI6,ANtLES f 2 WBBER LINE TOUCHING COMPASS CARD EDGE, NOT OVER. COURSE POINTER TOUCHING MINOR INDICES. NUMBER I ANO 2 ON BEARING POINTERS TO 6E 3/32 HIGH,SAME STYLE -AS ON CARD. INDICES ON BEARING POINTERS TO BE .O70 LONG AND .O31 WIDE; COLOR. BLACK. FIGURE 3. Display component dimensions II Prov
29、ided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-I-83034B a. transmitter ia is at o The azimuth ring shall position at 0 (north) when the rotor of the test b. If the dial on the rotor of the test transmitter is continuously rotated BO that its heading
30、 indication increases, the azimuth ring heading shall increase (counterclockwise (ccw) rotation) accordingly and the voltree C to li of the CT shall be in phase with the excitation voltage C to H. see 6.3.2) - 3.15 Command headinq. A means of selecting a desired heading both automatically and manual
31、ly shall be provided. around the azimuth ring shall be dirven by a d-c torquer servo system when excited by a remote device similar to the standard test transmitter specified in 3.12 and manually by a knob at the lower left corner of the instrument. There shall be no visible interaction between the
32、knob and the servo motor IBO that when the remote sycnhro device is driving the servo system, turning the knob will have no lastinp; effect on the heading marker position. synchronism with the azimuth ring after it is set. The heading eeection knob shall be connected with the heading marker in such
33、manner that clockwise (cw) rotation of the knob produces cw rotation of the knob produces CU rotation of the heading marker and vice versa. to I. desired heading. The heading set knob shall be (LB shown on figure 1. The maximum backlash between the command heading marker and the azimuth card shall b
34、e 0.250. A heading marker as shown on figure 2, which can rotate The heading marker shall rotate in . The turning ratio between the knob and the heeding marker shall be 7 The azimuth ecale reading indicated under the headlng marker shall be the 3.15.1 Heading marker servo system. described in 3.14.2
35、 for driving the azimuth ring shall be employed for positioning A d-c torquer servo system similar to that 1 ) the heading marker in response to a remte inpu0 signalb change of command heading at any rate between O position the heading marker around the azimuth ring to within 0.50 of the position of
36、 the test synchro, the function design of the heading marker loop shall be as shown on figure 4. The heading marker servo shall conform to the electrical connector and pin wiring shown on figure 4. The servo shall receive a and 60 per second without hunting. There shall be no appreciable hunt or osc
37、illation in the nervo syehem and it shall 4 3.15.2 Heading marker signal input. precision traneolver CDSH-10-AS-4, or electrical equivalent. The heading synchro device shall be a Clifton 3.15.3 Heading datum control transformer. The heading datum CT shall be a Clifton Precision CC-8-A-4 CT, or equal
38、, and shall operate a8 shown on figure 4. Electronic circuitry may be utilized to obtain the datum CT function when approved by the contracting actlvity. 3.15.4 command and heading datum-CTs shall be zeroed with positive rotation referenced at Heading command and heading datum control transfomer zer
39、o. Both the heading an index reference of 27OV. Both synchros shall be zeroed in the following manner: a. The standard test transmitter shall be positioned to zero indication on its dial and locked, connected to the heading command and headinp; datum CTs in accordance with the XYZ notation Indicated
40、 on figure 4, and excited with 26V, 400 Hz. bm the voltage C to H of the heading command CT rotor and heading datum CT rotor shown on figure 4 shall be null. The heading marker shall be positioned to 0 (north) on the azimuth card and i- ) 12 Provided by IHSNot for ResaleNo reproduction or networking
41、 permitted without license from IHS-,-,-MIL- 1- 830348 FIGURE 4. Functional schernot e dlagtom. 13 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-1-830 34B J c. When the heading marker is rotated cw around the azimuth ring, voltage C to H of the
42、 heading command CT rotor and heading cT rotor shall he In the ogpostte phase sense as the valtage C to H of the standard test transmitter from O H of the standard test transmttters from 180 (south) to O (north). d. When the heading marker is set on O (north) on the azimuth dial and the rotor of the
43、 standard test transmitters rotated to indicate an increasing heading (dial ccw), the voltage S to H of the heading command CT and the heading datum CTo shail be null at ,O to 180 , null at 180 , and opposite to the phase sense of C to H from 180 to O (north) to 180, null at 180 (south) and shall be
44、 it the eame phage sense as voltage C to - O in the same phase as the excitation voltaRe C to H from e. When the transmitter winding of the heading command CT is excited with 26V ac ao that the voltage C to H is in phase with power excitation ground to phase and the heading marker is set on O phase
45、with C to H and voltage X to Y null. When the heading marker is rotated cw to east, the voltage X to 2 will Increase before decreasing. O (north), then voltage X to 2 and Y to Z fill he in . 3,15.5 Heading marker servo zero. The heading command control transformer shall be connected to its servo sys
46、tem. The standard test transmtter shall be connected to the heading command CT In accordance with XYZ notation on figure 4. The excitation $voltage of the test transmitter C to H shall be in vhase with the servo vower ,xcitation voltage, pin AA to pin CC. The following conditions shall be satisficd-
47、 The heading marker shall position to 0 (gorth) on the azimuth ring when the a. dial of the standard test transmitter is at O . b. The heading marker shall rotate in an increasing heading Indication on the azimuth ring (cw) when the dial of the test transmitter synchro ia rotated in an increasing he
48、ading indication (dial ccw). 1 c. When the dial of the standard test transmitter is rotated in the increasing heading indication, the voltage C to H of the heading command CT shall be in the same phase sense with the voltage C to H of the standard test transmitter. 3-16 Command course. A means of se
49、lecting a desired course both automaticallv and Ilianually shall be provided. A course arrow, as shown on figure 2, that can rotate around the inside edge of the azimuth ring shall be driven by a servo system when excited by a remote device similar to the standard teat transmitter specified In 3.12, and shall be manually turned by a knob at the lower right corner of the tnstrument. As in the heading marker servo syst
