1、 - - MIL-A-23670A bb 797770b OL32OBL O M , I M I L- A-2 3 6?0A (WP) I NOVEMBER 1965 SUPERSEDING M IL-A-23670 (WEPI (MAY 1963 MILITARY SPECIFICATION ATTITUDE HEADING REFERENCE SYSTEM AN/ASN-50 (*) This specification has been approved by the Bureau of Naval Weapons, Department of the Navy. 1. SCOPE 1.
2、1 Scope - This specification covers design and all performance requirements for the Attitude Heading Reference System AN/ASN-50. 1.2 Classification - The attitude heading reference system shall consist of the items listed in 6.9. 2. APPLICABLE DOCUMENTS 2.1 General - The documents listed in 6.11 of
3、the issue in effect on the date of invitation for bids form a part of this specification to the extent specified herein. 3. REQUIREMENTS 3.1 *3.2 Preproduction - This specification makes provision for preproduction testing. Parts and Materials - In the selection of parts and materials, fulfillment o
4、f major (1) Parts and materials requirements shall conform to Specification MIL-E-5400. (2) Nonrepairable subassemblies, as outlined in Specification ML-E-5400, shall be used when practicable. The general size of the subassembly and the amount of circuitry to be included therein shall be approved by
5、 the procuring activity. Nonrepairable subassemblies must be reliable. I (See 6.4. ) (3) When previously produced models of this equipment did not use nonrepairable subassemblies, the design shall not be changed to employ nonrepairable assemblies without the approval of the procuring activity. desig
6、n objectives shall be the prime consideration. in so doing the following shall govern: *3.2.1 Nonstandard Parts and Materials Approval - Approval for the use of nonstandard parts and materials shall be obtained as outlined in Specification MIL-E-5400. *3.2.2 Electron Devices - Electron tubes, transi
7、stors anti diodes shall be chosen and applied as outiined in Specification MIL-E-4682. I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I - MIL-A-23670A hb 474770h O332082 2 MIL-A-23670A (WP) ( *3.3 Design and Construction - The equipment shall conf
8、orm with all the applicable re- quirements of Specification MIL-E-5400 for design, construction and workmanship, except as otherwise specified herein, *3.3.1 mum consistent with good design and shall not exceed 51.5 pounds. Component weights are: Total Weight - The total weight of the equipment, exc
9、luding cables, shall be a mini- (1) Displacement Gyroscope 26.5 lbs. (2) Amplifier-Power Supply 8.3 lbs. (3) Compass Adapter 13.2 lbs. (4) Compass Controller 2.0 lbs. (5) Rate Switching Gyroscope 1.5 lbs. 3.3.2 Reliability *3. 3.2.1 Operational Stability - The equipment Lall operate with satisfactor
10、y performance, continuously or intermittently for a period of a least 20 hours without the necessity for readjustment of any controls which are inaccessible to the operator during normal use, *3.3.2.2 Operating Life - The equipment shall have a minimum total operating life of 5000 hours with reasona
11、ble servicing and replacement of parts. Parts requiring scheduled replacement shall be specified by the contractor. hours of mean (operating) time between failures when tested and accepted as outlined under the re- quirements of 4.4. 3. 3.3.2.4 *3.3.2.3 Reliability in Mean Time Between Failures (MTB
12、F) - The equipment shall have 325 Time Totaliziw Meter - The equipment shall contain time totalizing meters in accord- ance with Speciication MIL-M-7793. Meters shall be included in the following units. Unit Amplifier-Power Supply Displacement Gyroscope Compass Adapter - Type of Meter MS17323 MS1732
13、3 MS17322 3.3.3 Cabling and Connections - *3.3.3.1 Cables and Connectors - The equipment shall provide for the use of cables and con- nectors in accordance with Specification MIL-E-5400. *3.3.3.2 Interconnection Cabling - The equipment shall be capable of satisfactory operation using external wiring
14、 in accordance with the applicable requirements of Specification MIL-W-5088. The external wiring shall be unshielded, except that a minimum number of the individual wires may be shielded when demonstrated as necessary to meet interference control requirements and provided the assembly of the cable t
15、o its plugs may be easily accomplished: External cables and that portion of the connectors attached to the cables shall not be supplied as part of the equipment. applicable requirements of Specification MIL-C-6781. The configuration of all control panels must be approved by the procuring activity pr
16、ior to preproduction testing. Interchangeability - The equipment shall meet the interchangeability requirements as defined in Speciication MIL-E-5400. *3.3.4 Control Panels - All rack or console mounted control panels shall conform to the *3.3.5 il 2 Provided by IHSNot for ResaleNo reproduction or n
17、etworking permitted without license from IHS-,-,-I MIL-A-23670A 66 M 7777706 0332083 4 MIL-A-23670A (WP) *3.3.6 Jnterference Control - The generation of radio interference by the equipment and the vulnerability of the equipment to radio interference shall be controlled within the limits of Specifica
18、tion MIL-1-6181. *3.3.7 Maintenance Provisions and Field Testing - Provisions for maintenance shall be as specified in Specification MIL-E-5400. Specific test points and test facilities shall be provided to the greatest extent practicable for ease of field shop maintenance. for equipment identificat
19、ion shall be in accordance with Specification MIL-N-18307. formance characteristics under standard conditions and for making iabaratory bench tests. *3. 3.8 Nomenclature and Nameplates - Nomenclature assignment and nameplate approval Standard Conditions - The following conditions shali be used to es
20、tablish normal per- *3.3.9 Temperature Altitude Normal Ground Room ambient (25OC f 5C) Vibration None Humidity Room ambient up to 90% relative humidity input power voltage 115 I 1.0/200 I 2. O VAC and 27.5 I O. 5 VDC *3.3.10 Service Conditions - The equipment shall operate satisfactorily under any o
21、f the envir- onmental service conditions or reasonable combination of these conditions as specified in Specification MIL-E-5400 for Class 2 equipment, except as modified below (see 42.2). Vibration - The equipment, with the exception of the compass controller, shall operate satisfactorily when subje
22、cted to the tests of MIL-E-5272, Procedure XI however, they may be connected to other control circuitry provided up to 6 high impedance control transformers hav- ing characteristics as defined above can be operated externally from each. The internally excited pitch and outer roll synchro transmitter
23、s shall have a lead from the stator center tap brought out to connector terminals (Table III) for use in failure detection circuits. 3.5.1.1.5.1 Synchro Zeroing and Sensing - The transmitting synchros on the vertical gyro axes of freedom shall be zeroed and their lead terminals of Table I connected
24、to satisfy the pro- cedures of 3.5. l. l. 5.1. 1 through 3. 5.1.1.5.1.5 for the identification of the terminals. The angular spread between the nulls of the two synchros on the outer roll axis ( and on the pitch axis) shall not exceed O. 4“. The null voltages shall not exceed 30 millivolts. 3.5. 1.1
25、.5.1.1 Externallv Excited Pitch Svnchro - Terminals c and K Table I shall be con- nected to the power lead terminal A, Table II and terminal L of Table I shall be connected to the power lead terminal Dy Table II. The voltage across terminals a and b, and the voltage across terminais L and a or b of
26、Table I shall be measured with the gimbals at zero displacement, The voltage across terminals a and b of Table I shall be at the minimum and the voltage across L and a or b of Table I shall be less than the voltage applied to terminals A and D of Table II. The voltage across terminals a and c and ac
27、ross b and c of Table I shall be measured as the reference assembly is rotated in climb about the pitch gimbal. The voltage across terminals a and c, Table I shall increase before decreas- ing and the voltage across the terminals b and cy Table I shall decrease before increasing. 3.5.1.1.5.1.2 Exter
28、nally Excited Outer Roll Synchro - Terminals W and H of Table I shall be connected to the power lead terminal A of Table II, and terminal J of Table I shall be connected to the power lead terminal D of Table II. The voltage across terminals U and V of Table I and the voltage across terminals J and U
29、 or V of Table I shall be measured with the gimbal at zero displacement. The voltage across terminals U and V of Table I shall be at the minimum and the voltage across J and U or V of Table I shall be less than the voltage applied to terminal A and D of Table II. The voltage across terminals U and W
30、 and across V and W of Table I shall be measured as the reference assembly is rotated about the outer roll gimbal in right roll. The voltage across terminals U and W shall increase before decreasing and the voltage across the terminals V and W shall decrease before increasing. lo Provided by IHSNot
31、for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-A-23670A 66 7779706 0332073 3 W I MIL-A-23670A (WP) TABLE I Displacement Gyroscope Assembly Output Connector (5381) Bendix P/N PM2H-18-32P, or equal, to mate with MS3116P-18-32S or equal Terminal A B C D E H Rotor F C
32、 Rotor G H Rotor 3 H C Rotor J HRotor K C Rotor L H Rotor M X Stator N Y Stator P Z Stator R X Stator S Y Stator T Z Stator U X Stator V Y Stator X X Stator Y Y Stator Z Z Stator 1 W Z Stato h Y Stator j Z Stator c Z Stato Function Spare Spare Spare Roll Switch - 90“ - 270“ Azimuth CX, C, TOP Azimut
33、h CX, BOTTOM 115 VAC excit. - F to G in phase with Tx“ to 1fZ7t at zero displacement 115 VAC excit. - H to J in phase with 115 VAC excit. - K to L in phase with “Z1! to qtXrl at zero pitch h 0u.cx-DG . 7Ztt to tqX“ at zero roll Pitch CX - EXT. Azimuth CX - BOTTOM Azimuth CX - TOP Roll CX - DG Roll C
34、X - VG (Internally excited rotor - neutral to ,0C in phase with “Z“ to qlX* at zero roll) Pitch CX - EXT Pitch CX - INT (Internally excited rotor - neutral to RfC in phase with “Z“ to “XIf at zero pitch) her roll CX (Internally excited rotor - neutral to OC in phase with fZ“ to ltXtl at zero displac
35、ement 3.5.1.1.5.1.3 Inner Roll Synchro - Terminal j of Table I shall be connected to terminal A of Table II. The voltage across g and h of Table I and the voltage across terminal D of Table II and terminal g or h of Table I shall be measured with the gimbals at zero displacement. The voltage across
36、terminals g and h shall be at the minimum and the voltage across terminal D of Table II and terminals g or h of Table I shall be less than the voltage applied to terminals A and D of Table II. The voltage across terminals g and j and across h and j of Table I shall be measured as the first gimbal (i
37、nner roll) is held and the reference assembly with the outer roll gimbal is rotated in right rolt The voltage across terminals g and j of Table I shall increase before decreasing and the voltage across terminals h and j shall decrease before increasing. 11 Provided by IHSNot for ResaleNo reproductio
38、n or networking permitted without license from IHS-,-,-MIL-A-23670A 66 7777706 0332072 5 1 MIL-A-23670A (WP) TABLE II Displacement Gyroscope Assembly Input Connector (J362) Bendix P/N PT02H-20-41P, or equal, to mate with MS3116P-20-41S or equal . Terminal Function B (0A) c (0B) D (0C) E F G H J K L
39、M N P R S T U V w X Y Z a b d e f g h i k m n P q r S t C j Input Power - 3 400 cps, 4 wire 2OOV line to line/ll5V line to neutral A, B, and #C phase rotation Spare Level- simal - Leveling excitation Leveling torquer control Leveling torquer fixed Pitch torquer A Pitch torquer B Pitch switch A Pitch
40、 switch B Pitch switch common Pitch capacitor Power failure Pitch segment switch Slaving torquer fixed Slaving torquer control 0 Pitch servo CT (H) Reserved Reserved Pitch generator output (c) Roll switch B Roll switch A Roll torquer excitation Roll torquer B Roll torquer- A Roll generator output (h
41、ot) Roll generator output (cold) Pitch generator output the maximum output shall be 10.2 f 1.2 volts at a phase angle of 30 I 2 lead. 3.5.3.7 (O) heading output. The differential synchro shall be zeroed such that when the rotor is excited by a synchro transmitter operating at its electrical zero, th
42、e stator output will be at its electrical zero + 180. 3.5.3.6.1 Synchro Zeroing - The output synchros shall be set at electrical zero for North 3.5.3.7.1 With the CX (5908) at 0 and the transmitter at O 1.5“ and slaving cutout, the output of the CXs (J909, and J902) shall be O“ f 12, and the output
43、of the CXs (5906 and 5907) shall be Oo I 18. The output of the CDX shall be 180 I 30. NOTE: The heading synchro is adjusted for zero when the voltage from X to Y is at a minimum and the dial reading is O (NORTH),. and with rotor lead C connected to stator lead Z the voltage from H to X shall be grea
44、ter than the voltage from H to C. The voltage between X and Z shall increase before decreasing for a rotation of the dial in increasing heading direction. For decreasing heading rotation of the dial, the voltage between X and Z shall decrease before increasing. I 26 - ., - . . . . . I Provided by IH
45、SNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-A-23b70A 66 7977706 OL32LO7 3 MIL-A-236704 (WP) 3.5.3.7.2 Clutched Synchro Zero - The output of the clutched synchro shall be O f 1“ with the clutch de-energized. With the clutch energized by 28 VDC the output sh
46、all increase for in- creasing heading and decrease for decreasing heading change up to f 25. Compass Mode Operation - In the Compass Mode Operation, the output data transmitters follow the Magnetic Compass transmitter input. (No directional gyro stabilization. ) The compass mode shall be initiated b
47、y an external signal from the mode selector switch. Static accuracy in the compass mode shall be f 1“ 30. extremes, the compass adapter shall meet the positioning accuracy, positioning rate, and synchron- izing requirements except as indicated below. Adjustment of deviation potentiometers shall not
48、be re- quired during environmental tests. 3.5.3.8 3.5.3.9 Performance at Environmental Extremes - When tested at environmental 3.5.3.9.1 Azimuth Servo - The free mode positional tolerances shall be increased from 30 max. to f 45 max. and dead zone from 20 to 30. Compass Mode - The positional toleran
49、ces shall be increased from 130 to Magnetic Slaving - The rate shall be increased from 3.5 and 7.5 degrees in 5 minutes to 2.5 and 8.5 degrees in 5 minutes, The positional accuracy shall be increased from 30 to 1. OO. 2.5O. 3. 5.3.9.1.1 2O. 3.5.3.9.2 3.5.3.9.3 Synchronization - The positional tolerances shall increase from I 2 to I Synchronization Indicator - The current through the 1100 ohm resistor shall increase from 5 microamperes or less to
