1、M I L-C-23727A (WP) SUPERSEDING 1 SEPTEMBER 1965 M I L-G- 23 7 27 ( W Pl 15 JANUARY 1964 MILITARY SPECIFICATION COMPUTER SET, LOFT BOMB RELEASE AN/AJB-3A This specification has been approved by the Bureau of Naval Weapons, Department of the Navy. 1. SCOPE 1.1 Scope - The equipment covered by this sp
2、ecifidion shall provide the functions of an Classification - The AN/AJB-SA Loft Bomb Release Computer Set shall consist of all-attitude flight reference system plus a correlated loft bomb release system. the items listed in 6.9. 1.2 2. APPLICABLE DOCUMENTS 2.1 General - The documents listed in 6.11
3、of 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, fulfillme
4、nt of major (1) Microelectronic items shall conform-to requirements specified herein. (2) ther parts and materials requirements shall conform to Specification (3) Nonrepairable subassemblies, as outlined in Specification MIL-E-5400, shall be used when practicable. The general size of the subassembly
5、 and the amount of circuitry to be included therein shall be approved by the procuring activity. Nonrepairable subassemblies must be reliable. (See 6.4) (4) When previously produced models of this equipment did not use nonrepairable subassemblies, the design shall not be changed to employ nonrepaira
6、ble assemblies without the approval of the procuring activity. Nonstandard Parts and Materials Approval - Approval for the use of nonstandard Electron Devices - Electron tubes, transistors and diodes shall be chosen and applied design objectives shall be the prime consideration. in so doing the foll
7、owing shall govern: MIL-E-5400. 3.2.1 parts and materials shall be obtained as outlined in Specification MIL-E-5400. as outlined in Specification MIL-E-4682. 3.2.2 FSC 5826 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-C-23727A (WP) . *3.2.3
8、 Microelectronic Modular Assemblies - When used, Microelectronic Modular Assem- blies shall be described by a contractor procurement specification and must be approved by the procuring agency. Microelectronic Modular Assemblies (Microelectronic Circuits) (MICS) shall be contained within Maintenance
9、Modules (for example, on printed circuit cards). The choice of Micro- electronic Modular Assemblies shall be based on at least two sources of supply, which can be used interchangeably. *3.2.4 Modules, Maintenanc,e - The electronic portions of the equipment shall be divided into maintenance modules (
10、see Specification MIL-S-23603). Maintenance modules shall normally be considered repairable. *3.2,5 changeable at the MIC level, or at the Maintenance module level when approved by the procuring activity. (See 6.13) Microelectronic Interchangeability - Microelectronic circuits (MICS) shall be inter-
11、 3.3 Design and Construction - The equipment shall conform with all the applicable requirements of Specification MIL-E-5400 for design, construction and workmanship, except as otherwise specified herein. Total Weight - The total weight of the equipment, excluding cables, shall be a minimum consisten
12、t with good design and shall not exceed 77.5 pounds. *3.3.1 3.3.2 Reliability *3.3.2.1 Operational Stability - The equipment shall operate with satisfactory performance, continuously or intermittently for a period of at least 20 hours without the necessity for readjustment of any controls which are
13、inaccessible to the operator during normal use. reasonable servicing and replacement of parts. Parts requiring scheduled replacement shall be specified by the contractor, *3.3.2.2 ODerating Life. - The equipment shall have a total operating life of 5000 hours with No part shall have a life of less t
14、han 1000 hours. *3.3.2.3 Reliability in Mean Time Between Failures (MTBF) - The equipment shall have 200 hours of mean operating) time between failures when tested and accepted as outlined under the re- quirements of 4.4.3. accordance with Specification MIL-M-7793. Meters shall be included in the fo
15、llowing units: *3.3.2.4 Time Totalizing Meter - The equipment shall contain time totalizing meters in (1) Adapter -Compensator, Compass MX-2826A/AJB (2) Amplifier -Pow er Supply AM- 1931/A JB - 3 (3) Gyroscope Assembly, Displacement CN-494A/AJB-3 (4) Indicator, Attitude-Director ID-811/AJB-3A 3.3.3
16、Cabling and Connections *3.3.3.1 Cables and Connectors - The equipment shall provide for the use of cables and connectors in accordance with Specification MIL-E-5400. using external wiring in accordance with the applicable requirements of Specification MIL-W-5088. The external wiring shall be unshie
17、lded, 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 to its plugs may be easily accomplished. External cables and that portion of the connectors attached to the cable
18、s shall not be supplied as part of the equipment. *3.3.3.2 Interconnection Cabling - The equipment shall be capable of satisfactory operation - 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-*3.3.4 Interchangeability of Reordered Equipment - .For
19、reordered equipment, interchange- ability shall exist between units and all replaceable assemblies, subassemblies, and parts of a designated model of any previously manufactured equipment, supplied or designated by the procuring activity. vulnerability of the equipment to radio interference shall be
20、 controlled within the limits of Specification 3.3.5 Interference Control - The generation of radio interference by the equipment and the MIL-1-6181. greatest extent practicable for ease of fidd testing and maintenance. for equipment identification shall be in accordance with Specification MIL-N- 18
21、307. 3.3.7 Nomenclature and Nameplates - Nomenclature assignment and nameplate approval Standard Conditions - The following conditions shall be used to establish normal *3.3.8 performance characteristics under standard conditions and for making laboratory bench tests. Temperature Altitude Normal Gro
22、und Vibration None Humidity Room ambient (25C I 5OC) Room ambient up to 90% relative humidity Input power voltage 115 +l.OV AC, 400 f 5 cps and 27.51 0.5V DC 3.3.9 Service Conditions - The equipment shall operate satisfactorily under any of the environmental service conditions or reasonable combinat
23、ion of these conditions as specified in Speci- fication MIL-E-5400 for Class 2 equipment, except as modified herein: the vibration requirements of Curves II and III of Specification MIL-E-5400, except the following items which shall operate satisfactorily when subjected to the vibration requirements
24、 specified. *3. 3. 9.1 Vibration - Each item of the equipment shall operate satisfactorily when subjected to Unit Requirement Proc. V, MIL-E-5272 Indicator, Attitude-Director ID-811/AJB-3A Gyroscope Assembly, Displacement Curve II, MIL-E-5400 CN- 494A/AJB- 3 extreme service conditions. v- With chara
25、cteristics as defined in MILrSTD-iO4 having limits as specified therein. The power required shall not exceed the spedified amounts. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_ MIL-C-23727A 58 W 979770b 0352442 7 fi- MIL-C-23727A (WP) (I) AC Pow
26、er (Three Phase) 115/200V, Category 200 VA (2) DC Power 28V, Category “B“, 1.5 Amps. Degraded Performance - Degraded performance will be permitted for voltage tran- *3,3.11.1 sients not exceeding O. 5 seconds during normal electric system operation. Operation shall be normal with no resulting damage
27、 to the equipment. sistance between isolated circuits and between each circuit and the case or connector shall be at least 50 megohms when a potential of 500V DC is applied for a period of 10 seconds. applicable requirements of Specification MIL-C-6781. The configuration of all control panels must b
28、e approved by the procuring activity prior to preproduction testing. Performance - Unless otherwise specified, values set forth to establish the require- ments for. satisfactory performance apply to performance under both standard and extreme service conditions. When reduced performance under the ex
29、treme conditions is acceptable, tolerance or values setting forth acceptable variations from the performance under the standard conditions will be specified. ODeratioa - The Loft Bomb Release Computer Set shall provide the functions of an all-attitude flight reference system plus a correlated loft b
30、omb release system. When operating as an all-attitude flight reference system, the system shall provide a continuous display of aircraft attitude through 360 degrees in roll, pitch and azimuth. A rate of turn display shall also be provided. Roll, pitch;and heading outputs shall also be provided for
31、use by other systems. The heading portion of the system shall have the following modes of operation: *3.3,12 Dielectric Strength - The materials used and the design shall be such that the re- *3.3.13 Control Panels - All rack or console mounted control panels shall conform to the 3.4 *3.4.1 (1) Slav
32、ed - providing gyro-stabilized heading referenced to magnetic north as established by the associated compass transmitter. (2) Free - providing gyro-stabilized heading referenced to a grid system established by the operator. (3). Compass - providing unstabilized heading referenced to magnetic north a
33、s established by the associated compass transmitter. When operating in the loft bomb release mode, the system shall provide an additional display to direct the pilot through the proper maneuver. The display shall include an indication of roll correction nec- essary to correct for aircraft yaw or rol
34、l errors, and pitch steering commands to direct the pilot through a pull-up maneuver to a 4g loop up to the point of bomb release. The system shall also provide a signal to produce an aural warning tone and a tone indicating start of the pull-up maneuver, provide a signal to initiate bomb release at
35、 a preselected pitch angle, and cancel the bomb maneuver if excessive aircraft yaw occurs. Means shall also be provided for the pilot to select the desired time delay between initiation of the bomb run and pull-up and to select either a preset low angle (less than 90) or a preset high angle bomb re-
36、 lease. Conditions - The system shall provide the performance specified when the components and associated equipment are interconnected and power is applied in accordance with Figure 1. Unless otherwise specified, the deviation compensation of the compass adapter shall be adjusted to compensate for
37、heading errors and the roll and pitch trim of the attitude indicator shall be adjusted for zero trim. *3.4.1.1 *3.4.2 Erection and Synchronization - Within 88 seconds after initial application of power, the OFF flag in the attitude indicator shall disappear from view. Within 3. O minutes after initi
38、al application of power, the pitch and roll indication shall be within i2.0 of the position of the - 4 =-. *- Y - 1 _ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I I J905 PT06P-10-16 ,J JI5018 FLUX J906 PTO6P-IO-16Sx J 907 J908 PTO6P-IO-16S F J90
39、9 PTO6P-IO-16S J911 PTO6P-18-32S) TEST CONNECTOR NOTE: h A B C o E F L A e C E F c ). J F L h h F F I 1 1 L 2 - m - J910 TO6P-18-32SW J801A J801B JSOIC JBOID JBOIE J801F JBOIG JBOIH JBOIJ JBOIK JBOIM JBOIP JBOIR JBOIS JBOIW JBOIX J903 I rPT06P-12-IOS NEUTRAL OC GROUNO JIOID Lr A K ERECTION CUTOUT J9
40、04 PTO6P-18-32S xi: uiMuTH-; i 28V 0C EXC SOURCE4 cx NEUTL SOURCE+ MIMUTH CT OUTPUT+ AZIMUTH AMPL INPUT- w SWITCHING UNIT AUTOSYN EXC 26V 400fH y :x cz -i i AUTOSYN WTPUT CLUTCH 28VOC- d, AIP CUTOUT MAN. COMPASS- f TURN CUTOUT INPUT- TURN CUTOUT INPUT- Q AIP CM MAN COLIP SLEW- h j - ADAPTER- COMPENS
41、ATOR, COMPASS MX- 2826A/AJB DEFGHJKLMNPR - J1501X - c1501i - J 1501D - J1501F - J1501E - J1502J - J205b - J598Z - J598Y - J598X - J1501P J205L J205K dl - JPOSM I.X,Y,Z AND H,C DESIGNATIONS ARE IN ACCORD WITH AIRINC SYNCHRO SYSTEMS MANUAL INDEX REFERENCE. ROLL-180. PITCH-180* AZIMUTH-O* ROTATIONAL RE
42、FERENCE POSITIVE c“ edct G 1 z 01 h ROLL-RIGHT BANK PITCH-CLIMB AZIMUTH- INCREASE HDG. 2.AK DENOTES AIRCRAFT EQUIPMENT. 3.CONNECTOR PART NUMBERS ARE BENDIX NUMBERS. 4.S-701 FUNCTIONS (OFF AS SHOWN) 1.TIHED LO ANGLE 2.TIHED HI ANGLE 3. I NST. HI ANGLE I Provided by IHSNot for ResaleNo reproduction or
43、 networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-+ c1 rIMER,INTERVAL TD-PJGA/AJ B-3 a + L z a t+ ,o !?$ TEST CONNECTOR PI502 PT06P-20-41P JI502 PTOOE-20-41s RATE GYR )PITCH C -IV MIDC ILLUM LIGHT ! PU
44、LL UP GND SIG GND INDICATOR- ATTITUDE DIRECTOR ID-II/AJB-3A CONTROLLER-COMPASS SYSTEM - C-2984/AJB-3 A Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-23727A 58 9 9777906 0352447 b 9 MIL-C-23727A (WP) displacement gyroscope relative to local gr
45、avity vertical. Within 10 minutes after initial application of power and with the system operating in the SLAVED mode, the heading indication shall agree with the compass transmitter heading within 13.5“ and the needle of the SYNC IND on the controller shall be within 1/4 of the arc from the center
46、to the end of the scale. *3.4.2.1 Erection Rates - With the spin axis of the vertical gyro deflected 10“ from local gravity vertical in roll, the low erection rate in roll shall be 1.3 I O. 7 degrees per minute. With the spin axis of the vertical gyro deflected 20“ from local gravity vertical in pit
47、ch, the low erection rate in pitch shall be 1.3 I O. 7 degrees per minute. Azimuth Operation - Switching to the SLAVED mode or operating the PUSH TO SYNC button when in the SLAVED mode shall cause the heading indication to synchronize to within 13.5“ of the compass transmitter heading at a minimum r
48、ate of 20“ per second. Within 5 seconds after the heading indication has stabilized, the needle of the SYNC IND meter shall be within 3/4 of the arc from the center to the end of the scale. *3.4.3 *3.4.3.1 Set Heading - With the system operating in the FREE mode, operation of the PUSH TO TURN contro
49、l shall cause the heading indication to change at a rate approximately proportional to the degree of rotation of the control. Rotation to the right (R) shall cause the heading indication to increase and rotation to the left (L) shall cause the indication to decrease. When the PUSH TO TURN control is released, the heading indication shall stop changing. rotation through 360“ in roll, pitch and azimuth smoothly and shall not
