1、z- - MIL-C-85LLILIC 14 = 7777706 0363877 7 W MILITARY SPECIFICATION F-Y-c7/7 MIL-C-85144C(AS) 22 OCTOBER 1986 SUPERSEDING MIL-C-85144B( AS) 4 February 1985 CONTROL SECTION, GUIDED MISSILE FOR AIM/RIM-7M, GUIDED MISSILE This specification is approved for use within the Naval Air Systems Command, Depa
2、rtment of the Navy, and is available for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification establishes the requirements for manu- - facture and acceptance of the Control Section, Guided Missile, referred to herein as the “assembly“. 1.2 Classifi
3、cation. The following control section configurations are covered by this specification. Type I: Type IL: WCU-S/B, Drawing 917AS6200-1 and 2. WCU-5A/B, Drawing 917AS6200-3, WCU-5B/B, Drawing 917AS9074, or WC-5C/B, Drawing 917AS9868. Beneficial comments (recommendations, additions, deletions) and any
4、pertinent data which may be of use in improving this document should be addressed to: Commanding Officer, Naval Air Engineering Center, Systems Engineering and Standardization Department (SESD), Code 93, Lakehurst, NJ 08733, by using the self-addressed Standardization Document Improvement Proposal (
5、DD Form 1426) appearing at the end of this document or by letter. - - _ AMSC No. NIA )FSC420 1 DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. THIS DOCUMENT CONTAINS 4-6 PAGES. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from
6、 IHS-,-,- MIL-C-85144C 14 W 9779906 0363878 9 MIL-C-85144C(AS) 1.3 (U) Control section classes. Control sections described by this specification are of the following classes, depending on the level of procurement. a. Class I: Control sections fabricated for procurement at the missile guidance set le
7、vel. b. Class II: Control sections fabricated for procurement at the control section level (see 3.1.2). 2. APPLICABLE DOCUMENTS 2.1 Government documents. 2.1.1 Specifieations and standards. The following specifications and standards form a part of this specification to the extent specified herein. U
8、nless otherwise specified, the issues of these documents shall be those listed in the issue of the Department of Defense Index of Specifications and Standards (DoDISS) and supplement thereto, cited in the solicitation. SPECIFICATIONS MIL IT ARY MIL-P- 1 16 MIL-H-5606 MIL-G-85142 STANDARDS FEDERAL FE
9、D-STD-102 MILITARY MIL-STD-129 MIL-STD-454 MIL-STD-16 9 S MIL-STD-45662 2 Preservation, Methods of. Hydraulic Fluid, Petroleum Base; Aircraft, Missile, and Ordnance. Guidance-Control Sections for Guided Missile AIM/RIM-7M. Preservation, Packaging, and Packing Levels . Marking for Shipment and Storag
10、e. Standard General Requirements for Electronic Equipment. Environments, Working, Minimum Standards for. Calibration Systems Requirements. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-%I 3 c MIL-C-85LqqC 14 9779906 O363899 O MIL-C-85144C(AS) 2.1.2
11、 Other Government documents and drawings. The following other Government documents and drawings form a part of this specification to the extent specified herein. Unless otherwise specified, the issues shall be those in effect on the date of the solicitation. DOCUMENTS NAVAL AIR SYSTEMS COMMAND (Code
12、 Ident 30003) WS-6536 DRAWINGS Procedures and Requirements for Preparation and Soldering of Electrical Connections. NAVAL AIR SYSTEMS COMMAND (Code Ident 30003) 9 17AS2 13 9 17AS216 Stud, Wing. Assembly, Wing and Stud. 9 17AS754 9 17AS6200 9 17AS8 148 9 17AS90 74 9 1 7AS9868 RAYTHEON COMPANY (Code I
13、dent 49956) 479512 Wing, Guided Missile SU-56A/B . Control Section, Guided Missile. Accumulator and Flow Valve. Control Section, Guided Missile WCU-SB/B. Control Section, Guided Missile WCU-5C /B . Control Section Housing. (Copies of specifications, standards, drawings, and documents required by con
14、tractors in connection with.specific acquisition functions should be obtained from the contracting activity or as directed by the contracting activity.) 2.2 Order of precedence. In the event of a conflict between the text of this specification and the references cited herein, the text of this speci-
15、 fication shall take precedence. Nothing in this specification, however, shall supersede applicable laws and regulations unless a specific exemption has been obtained. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-tIIL-C-85144C 14 = 7777906 03637
16、00 3 II MIL-C-85144C(AS) 3 . REQUIREMENTS 3-1 Item description. The assembly shall consist of an autopilot, hydraulic control section, accumulator and flow valve assembly, alternating current (ac) to direct current (dc) converter, craft gyro assembly and missile tune converter. - 3.1.1 Class I contr
17、ol sections, Class I control sections shall meet all requirements specified herein, 3.1.2 Class II control sections. Class II control sections shall meet all requirements specified herein and in addition, each control section shall be tested in accordance with and meet all requirements of MIL-G-8514
18、2 with the exception that the reliability demonstration tests and contractor tests are not required. The vibration screening and preconditioning and electrical performance tests shall be conducted in accordance with MIL-G-85142 with a mating section, 3.1,3 Government-furnished property list. Unless
19、specified in the contract or purchase order (see 6.2,1), the Government will provide a list of ali Government-furnished property to the contractor. 3 . 2 3.2.1 Electrical performance, Each assembly shall meet theelectricai Character ist ics . performance requirements specified herein. 3.2.1.1 AC/DC
20、conversion. The outputs at the following contacts shall be as specified in Table I, 3.2-1.2 Gyro signals. 3.2,1.2.1 Over voltage period. The voltage at 522-15 (1200 Hz phase A) shall be 39.5 +3,0 Vtrms and at 522-34 (1200 Hz phase B) shall be 39.5 k3,O Vtrms when measured in the 2 seconds (s) interv
21、al that the 400 Hz power of 4.1,5.2 is applied. 3.2.1.2.2 Normal run period. The output at 522-15 (1200 Hz phase A) shall be 15.0 I1,5 Vtrms and at 522-34 (1200 Hz phase B) shall be 15.0 I1.5 Vtrms. 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
22、MIL-C-85144C 14 7977706 0363703 5 II MIL-C-85144C(AS) Contacts 520-D (Type i) J20-D (Type II) 520-T J20-V 521-13 521-15 521-17 521-18 521-19 521-37 521-32 521-33 521-35 521-27 523-1 523-2 523-3 523-1 1 523-14 523-15 523-16 TABLE I. AC/DC conversion. il Vdc - +30 I5 t26 25 +13 k2 -26.5 I2.5 - -i-43.5
23、 k1.5 +43.5 k1.5 +13 f2 3/ +26.5 22.5- 3/ -43.5 k1.5 -43.5 k1.5 +53 +5 -20.6 k2.0 Vdc 71 31 31 +20.6 k2.0 Vdc -20.6 k2.0 Vdc 71 +20.6 k2.0 Vdc- 21 Vtrms - 5.5 k1.5 (400 hertz (Hz) 15.0 k4.5 (400 Hz) 113.0 k6.5 (400 Hz) 113.0 k6.5 (400 Hz) 113 O k6.5 (400 Hz) 113.0 k6.5 (400 Hz) 31 113.0 k6.5 (400 Hz
24、) 71 113.0 k6.5 (400 Hz) - Volts direct current (Vdc) . 2 Volts true root-mean-square (vtrms) . 2 Measurements shall be performed within 2 seconds of grounding 520-U. 3.2.1.3 Prelaunch tuning logic. The assembly shall meet the following requirements: a. No signal. 2.17 k0.83 s and the output at 520-
25、S shall be not more than +1 Vdc when measured not less than 3 s after J20-U is grounded. No retune. No radar on. The output at 523-14 shall be +20.6 k2.0 Vdc for b. C. The output at 523-14 shall be 0.0 I0.5 Vdc. The output at 523-14 shall be 0.0 k0.5 Vdc. d. Enable command. when measured during the
26、interval that the +26.5 volts (V) input to 523-21 is applied. The output at 523-14 shall be +20.6 k2.0 Vdc Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I UIL-C-85L44C 14 7797706 0363702 7 3.2.1.3.1 Prelaunch tune. The output at 520-S shall change
27、from 0.0 k0.5 Vdc to +5.5 21.0 Vdc not less than 80 milliseconds (ms) and not more than 400 ms after the input to 523-33 is changed from a ground to +4.5 Vdc. The output at 1651-10 and 520-f shall, be +25.5 k1.0 Vdc. - 3.2.1.3.2 Missile ready latch, The output at 520-S shall be +5.5 51.0 Vdc. The ou
28、tput at 1651-10 shall be 0.0 t0.5 Vdc. 3,2.1.4 Roll drift. The output at 1651-21 shall not change at a rate in excess of tl0 millivolts direct current per second (mVdc/s). NOTE: Adjustment of 16A3R13 is allowed to meet this requirement. 3.2.1.5 Pitch and yaw launch drift/C-band. The outputs at 1651-
29、19 and 1651-20 shall not change at a rate in excess of I35 mVdc/s. NOTE: Adjustment of 16R1 an 16R2, respectively, are allowed to meet these requirements. 3.2.1.6 Wing servos 1 and 3. The output at 1651-1 shall lag the 10 Hz input by not greater than 217 degrees (deg). 3.2.1.6.1 Gain margin. The out
30、put at 1651-1 shall be not greater than 0.05 volts root-mean-square (Vrms) when measured not less than 3 s after the pulse to 1651-14 has been applied. 3.2.1.7 Wing servo 2. The output at 1651-2 shall lag the 10 Hz input by not greater than 217 deg. 3.2.1.7.1 Gain margin. The output at 1651-2 shall
31、be not greater than 0.050 Vrms when measured not less than 3 s after the pulse to 16J1-15.has been applied. 3.2.1.8 Wing servo 4. The output at 1651-3 shall lag the 10 Hz input by not greater than 217 deg, 3.2.1.8.1 Gain margin. The output at 1651-3 shall be not greater than 0.05 Vrms when measured
32、not less than 3 s after the pulse to 1651-16 has been applied. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-85144C 14 9777706 0363903 7 e 3.2.1.9 Roll autopilot/3 Hz - 2 degrees peak-to-peak (deg p-p) roll yozzle. 3.2.1.9.1 Residual. The out
33、put at 1651-4 shall be O 150 millivolts direct current (mVdc), at 1651-24 shall be 117 +6 mVdc and at 1651-25 shall be 117 +6 mVdc. 3.2.1.9.2 Demodulators. The 3 Hz output at 1651-4 shall be negative for positive rotation (see Figure 1) and shall be 118 20.12 volts peak-to-peak (Vp-p), and the outpu
34、t at 523-5 shall be 754 275 millivolts peak-to-peak (mVp-p). mVp-p. The outputs at 1651-5 and 1651-6 shall be not greater than 75.5 3.2.1.9.3 High gain/A-band. The shaft of wing 2 or 4 shall move 1.64 k0.17 deg p-p. 3.2.1.9.4 Low gain/A-band. The shaft of wing 2 or 4 shall move 0.72 20.08 deg p-p. 3
35、.2.1.9.5 B-band. The shaft of wing 2 or 4 shall move 1.45 k0.15 deg P-P. 3.2.1.9.6 C-band. The shaft of wing 2 or 4 shall move to 3.63 20.37 deg p-p. 3.2.1.9.7 High speed/D-band/prelaunch. The output at 1651-9 shall be -1.8 k1.0 Vdc, at 523-28 shall be +5 21 Vdc, at 523-9 shall be +5 21 Vdc and at 5
36、23-30 shall be -4.5 20.4 Vdc. 3.2.1.9.8 Missile velocity (Vm) high gan/D-band. The shaft of wing 2 or 4 shall move 2.17 ir0.22 deg p-p and the output at 521-26 shall be 31 +1 vp-p. 3.2.1.9.8.1 Vm medium gain/D-band. The following shall apply: a. The output at 523-30 shall be -3.20 10.25 Vdc. b. The
37、shaft of wing 2 or 4 shall.move 3.41 20.35 deg p-p. 3.2.1.9.8.2 Vm low gain/D-band. The following shall apply: a. The output at 523-30 shall be -2.25 10.20 Vdc. b. The shaft of wing 2 or 4 shall move 4.92 i-0.50 deg p-p. 3.2.1.9.9 Surface launch/3 Hz - 2 deg p-p roll yozzle. The shaft of wing 2 or 4
38、 shall move 0.48 20.06 deg p-p and the output at 523-32 shall be +5 il Vdc, and at 521-1 shall be -23.5 25.0 Vdc. 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-85Z44C ZLJ = 7777706 0363704 O W MIL-C-85144C(AS) CRAFT YAW GYRO AXIS D POS IT I
39、 VE T UMBILICAL CRAFT PITCH GYRO AXIS RECEPTACLE HYDRAULIC INLET POSIT IVE PI TCH WING 3 - SHAFT AXIS ,CONTROL SECT I ON UP ROLL GYRO AXIS UP (WI JG 4 ROLL AXIS DOWN (WING 3 DN) YAW GYRO AXIS JP) PITCH GYRO AX1 POSIT IVE YAW GYROSCOPE ASSEMBLY (UNIT 14) FIGURE 1. Craft gyro input axis orientation. P
40、rovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-5144C 14 7777706 03b3705 2 I 3.2.1.9.10 Longitudinal accelerometer. The output at 1651-9 shall change at a rate of -0.98 kO.10 volts direct current/second (Vdc/s). 3.2.1.9.11 Roll command and timin
41、g. The output at 1651-2 shall change -0.19 IO.10 Vdc 0.60 k0.06 s after launch indication is applied, and shall be -2.63 t0.80 Vdc after 1.6 s, and shall stop changing (change not greater than 0.4 Vdc/s) in 3.0 k0.3 S. The output at 523-34 shall change from 12.5 k0.5 Vdc to +5 fl Vdc and the output
42、at 1651-11 shall change from 0.0 k0.5 Vdc to +5 k1 Vdc, 0.6 IO.1 s after 523-31 is changed to +5 Vdc. The output at 1651-27 shall change from +2.5 0.5 Vdc to +5 k1 Vdc and the output at 1651-12 shall change from 0.0 I0.5 Vdc to +5 +I Vdc at 3.0 k0.3 s after 523-31 is changed to +5 Vdc. 3.2.1.10 3.2.
43、1.10.1 Residual. The output at 1651-6 shall be O k50 mVdc. 3.2.1.10.2 B-band. The shaft of wing 1 (or 3) shall move 8.79 k0.88 deg Yaw gyro gain/3 Hz - 2 deg p-p yaw yozzle. p-p, the outputs at 16JL-4 and 1651-5 shall be not greater than 59 mVp-p and 75.5 mVp-p, respectively, and at 1651-6 the 3 Hz
44、output shall be 1.51 10.15 Vp-p and shall be positive for positive rotation (see Figure 1). 3.2.1.10.3 C-band. The shaft of wing 1 (or 3) shall move 15.73 11.58 deg P-P 3.2.1.10.4 D-band. The shaft of wing 1 (or 3) shall move 21.5 k2.2 deg P-P 3.2.1.10.5 A-band. The shaft of wing 1 (or 3) shall move
45、 3.96 k0.40 deg P-P. 3.2.1.10.6 Surface launch. The shaft of wing 1 (or 3) shall move 3.22 i0.32 deg p-pc 3.2.1.11 Yaw synthetic stability. 3.2.1.11.1 A-bandlboost. The shaft of wing 1 (or 3) shall move 1.61 20.17 deg p-p. 3.2.1.11.2 A-band/glide. The shaft of wing 1 (or 3) shall move 0.79 kO.09 deg
46、 p-p. 3.2.1.12 3.2.1.12.1 Residual. The output at 1651-5 shall be O +50 mVdc. 3.2.1.12.2 B-band. The shaft of wing 2 or 4 shall move 8.79 f0.88 deg p-p, the outputs at 1651-6 and I6J1-4 shall be not greater than 75.5 mVp-p and 59 mVp-p, respectively, and at 1651-5 the 3 Hz output shall be 1.50 k0.15
47、 Vp-p and shall be negative for positive rotation (see Figure 1). Pitch gyro gain/3 Hz - 2 deg p-p pitch yozzle. 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.2.1.12.3 C-band. The shaft of wing 2 or 4 shall move 15.73 f1.58 deg P-P* 3.2.1.12.4
48、D-band. The shaft of wing 2 or 4 shall move 21.5 I2.2 deg P-P* 3.2.1.12.5 A-band. The shaft of wing 2 or 4 shall move 3.96 I0.40 deg PP* , 3.2.1.12.6 Surface launch. The shaft of wing 2 or 4 shall move 3.22 k0.32 deg p-p. 3.2.1.13 Pitch synthetic stability. 3.2.1.13.1 B-band/boost. The shaft of wing
49、 2 or 4 shall move 3.01 20.31 deg p-p. 3.2.1.13.2 B-band/glide. The shaft of wing 2 or 4 shall move 1.48 -0.16 deg p-p. 3.2.1.14 Guidance command loop (1 Hz 1.38 Vp-p input). 3.2.1.14.1 A-band/glide. The shaft of wing 1 (or 3) shall move 4.93 The shaft of wing 2 or 4 shall move 4.93 I0.50 deg p-p. 20.50 deg p-p. 3.2.1.14.2 B-band/boost. The shaft of wing 1 (or 3) shall mov
