NAVY MIL-N-81460 B-1977 NAVIGATION SET RADAR AN APN-182(V)《AN APN-182(V)型雷达的航海装备》.pdf

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1、f . _. _- - MIL-N-83460B 58 7777906 0370745 5 m -7 MI 1,-N -8 1 4 GOB (AS) 8 February 1977 - - - Supcrscding 18 July 19 72 MIL-N-81460d(AS) MILITARY SPECIFICATION Navigation Set, Radar AN/APN-l82(V) This Specification has been Approved by the Naval Air Systems Command, Department of the Navy 1. SCOP

2、E 1.1 Scope - The equipment covered by this specification shall determine and present the three orthogonal components of aircraft velocity (along-heading, across heading, and vertical) referenced to the aircraft coordinate system. * 1.2 Classification - The equipment covered by this specification sh

3、all consist of the following items: Item Receiver-Transmitter Radar or - Receiver-Transmitter Radar or Rcceiver-Transmitter Control-Iradicator Converter, Signal Data Mounting, Signal Data Converter or APPl. Para. - l Aircraft, Installation of MIL-E -54 O0 Electronio Equipment, Aircraft, General Spec

4、ification for MIL-T-5422 Testing, Environmental, Aircraft Electronic Equipment MIL-1-6181 Interference Control Requirements, c aircraft Equipment MILX -6781 ControI Panel; Aircraft Equipment; Rack or Console Mounted MIL-M-7793 Meter, Time Totalizing MIL-E-17555 Electronic and Electrical Equipment an

5、d Associated Repair Parts, Preparation for Delivery of MIL-T-18303 Test Procedures ; Preproduction and Acceptance for Aircraft Electronic Equipment; Format for Nomenclature and Nameplates for Aeronautical Electronic and Associated Equipment MIL-N-18307 Naval Air Systems Command AR-5 Microelectronic

6、Devices Used in Avionic Equipment, Procedures for Selection and Approval of 3 Licensed by Information Handling ServicesLicensed by Information Handling ServicesMIL-N-L960B 58 E 7777706 0370749 2 E Ml L-N-814O.l3(AS) may be obtained upon application to the Commanding Officer, Publications aiid Forms

7、Center, Code 1051, 5801 Tabor Avenue, Philadclphia, Pennsylvania 19120, 3. REQUIREMENTS 3.1 Preproduction - This specification makes provisions for prepro- duction testing. 3.2 Parts and Materials - In the selection of parts and materials, fulfill- ment of major design objectives shall be the prime

8、consideration. In so doing, the following shall govern: (1) . Microelectronic technology shall be considered and micro- electronic items shail conform to requirements specified herein. (2) Other parts and materials- requirements shall conform to Specification MIL-E-5400. (3) Nonrepairable subassembl

9、ies shall be used in accordance with Speciiication AR-10 and as outlined in Specification MIL-E-5400. (4) ._ When previously produced mdels of this equipment did not use nonrepairable subassemblies, the design shall not be changed o employ nonrepairabe assemblies without the approval of the procurin

10、g activity. 3.2.1 Nonstandard Parts and Materials Approval - Approval for the use of nonstandard parts and materials (including electron tubes, transistois, and diodes) other than microelectronic devices shall be obtained as outlined in Specification hIIL-E-5400. Microelectronic devices shall be app

11、roved as outlined in AR-5. 3.2.2 Microelectronic Modular Assemblies - When used, Microelectronic Modular A ssemblics shall meet the requirements of Specification AR-5. Con- formal coatings, eiicapsulants, embedments or potting materials used with modular assemblies containing integrated circuits and

12、 discrete parts shall be easily re- movable without damage to the assembly, 3.2.3 Modules - The electronic portions of the equipment shall be func - tionally modularized in accordance with Specification AR-IO. 5 Licensed by Information Handling ServicesMIL-N-81460B(AS) I c 3.3 Designand Construction

13、 - The equipment shall conform with all tho applicable requirements of Specification MIL-E-5400 for design, coktruc - I tion and workmanship, except as otherwise specified herein. I consistent with good design. The actual total weight will vary with tho particular components selected. using MILSTD-7

14、85 as a guide. On a reorder from a supplier who has previously produced the equipment the program previously used may be continued unless I otherwise indicated in the contract or order. tory performance, continuously or intermittently for a period of at least 500 hours without the necessity for read

15、justment of any controls which are inaccessible to the operator during normal use. 3.3.2.2 Op erating Life - The equipment shall have total operating life of 5000 hours with reasonable servicing and replacement of parts, Parts requir- ing scheduled replacement shall be specified by the contractor. 3

16、.3.2.3 Reliability in Mean Time Between Failure (MTBF - The equip- ment shall have 150 hours of mean (operating) time between failures when tested and accepted as outlined under the requirements of 4.4.3. 3.3.2.4 Time Totalizing Meter - The following units shall contain time totalizing nieters in ac

17、cordance with SDecification MIL-M-7793 Converter, Signal Data CV-2476/APN-l82(V) MS-17322 Power Supply PP-G043/APNi182(V) MS-17322 3.3.3 Cabling and Connections - I use of cables and connectors in accordance with Specification MIL-E-5400, Licensed by Information Handling ServicesMIL-N-8L460B 58 9799

18、906 017075L O 3.3.3.2 Interconnection Cabling - The equipment shall be capable of satisfactory operation using external wiring 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 my

19、be shielded when demonstrated as necessary to meet interference control require- ments and provided the assembly of the cable to its plugs may be easily accomp- lished, External cables and that portion of the connectors attached to the cables shall not be supplied as part of the equipment. 3.3.4 Con

20、trol Panels - All rack or console mounted control panels shall conform to the applica%e requirements of Specification.MIL -C -6781. The configuration of all panels must be approved by the procuring activity prior to preproduction testing. 3.3.5 Interchangeability - The equipment shall meet the inter

21、change- ability requirements of Spcification MIL-E-5400. 3.3.6 Interference Control - The generation of radio interference by the equipment and the vulnerabiliy of the equipment to radio interference shall be controlled within the limits of Specification. MIL-1-6181. 3.3.7 Maintenance Provisions and

22、 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 testing and maintenance as specified in MIL-STD-415. 3.3.8 Nomenclature and Nameplates - Nome

23、nclature and serial number assignment, nameplate approval, and identification marking shall be in accor- dance with Specification MIL-N-18307. (Also see Para. 6,5) 3.3.9 Standard Conditions - The following conditions shall be used t establish normal performance characteristics under standard conditi

24、ons and for making laboratory bench tests Temperature Room ambient (25C 5 5C) Altitude Normal ground Vibration None Humidity Room ambient up to 90% relative humidity input Power Voltage 115 22.0 VAC, 400 5 5 Hz single-phase 7 Licensed by Information Handling Servicesc MIL-N-81460B(AS) I 3.3.10 Servi

25、ce Conditions - The equipment shall operatc satisfactorily under any of the environmental service conditions or reasonable combination of these conditions as specified in Specification MIL-E-5400 for Class 1A equipment, except as modified herein. 3.3.10.1 Vibration - The equipment shall operate sati

26、sfactorily when I subjected to the vibration requirements of Curve III of SDecification MIL-E-5400. I quirementa over the temperature range -40C to +55“C. From -40C to -55OC the equipment shall operate but performance accuracy tolerances may be increased by a factor of 2, * 3,3.10.3 Altitude - Over

27、the temperature range of -4OOC to +55“C, the equipment shall meet the performance requirements from zero feet (on the runway) to a maximum altitude of 20,000 feet over land and over water at Sea States Codes I through 9 as defined in ASCC.AIR STD 53/14. 3.3.11 Warm-up Time - The time required for th

28、e equipment to warm-up prior to operation shall be kept to a minimum and shall not exceed 1 minute under standard conditions and 2 minutes at extreme service conditions. 3,3.12 Input Electrical Power - 3.3.12.1 9, erating Power - The equipment shall meet all applicable requirements of MIL-STD-704 an

29、d shall give specified performance when ener- gized from the following power sources having characteristics and limits as defined in MIL-STD-704, The power required shall not exceed the specified amounts. (1) AC Power (single Phase), 115V, Category B, 210 VA. more than O. 10 amp at. 28 volts. 3.3.12

30、.3 Degraded Performance - begraded performance will be per- mitted for voltage transients not exceeding O. 5 second during normal electric system operation. weration shall return to normal with no resulting damage to the equipment. Licensed by Information Handling Services3.3.12.4 Standby Power - Th

31、e equipment shall provide for a standby position whereby rated voltage shall be applied to all circuits except to the trans- mitter which shall remain silent. The standby power shall not exceed 160 VA. *3.3.12.5 Cooling - The equipment shall operate satisfactorily without the need of external coolin

32、g (e. g. , cooling air, heat sinks) over the temperature and altitude range specified in 3.3.10.2 and 3.3.10.3 when adequate space is provided- for normal convection airflow. 3.4 Performance- Unless otherwise specified, values set forth to estab- lish the requirements-for satisfactory performance ap

33、ply to performance under both standard and extreme service conditions. When reduced performance under the extreme conditions is acceptable, tolerances or values setting forth acceptable variations from the performance under the standard conditions are specified. 3.4.1 Operation - The equipment shall

34、 measure the along heading, across heading and vertical components of velocity in aircraft coordinates, of a rotary wing aircraft in flight. The equipment shail generate and transmit three narrow continuous wave beams of electromagnetic energy downward by means of a non- stabilized Radar Receiver-Tr

35、ansmitter to illuminate three small areas o? the earths surface. The frequency of energy returned along each beam shall be continuously and directly compared with the frequency of radiated energy to pro- vide coherent detection of the magnitude and sense of the doppler frequency shift caused by airc

36、raft motion. The beams of radiated energy shall be directed rela- tive to the aircraft such that proper summing of the doppler frequency shift will be proportional to the aircraft.heading, drift and vertical velocities. The doppler frequency signals shall be converted to 400 Hz analog voltages propo

37、rtional to the three components of aircraft velocity. The equipment shall be entirely self- contained within the aircraft. The equipment shall provide output signals to the navigation computer. automatic-stabilization equipment, inertial velocity system, direction-velocity indicator, and ground spee

38、d-drift angle indicators. STBY, LAND/ALT, SEA, and TEST modes of operation shall be provided. Compensa- tion for sea bias error shall be provided in the SEA modes. In the SEA mode, the equipment shall be inhibited from searching for doppler signals below 853 Hz. 3.4.2. Frequency Characteristics - Th

39、e transmitted frequency shall be 13.300 f - 5 MHz. 3.4.3 tinuous wave (CW) . Modulation Characteristics -. The transmitted energy shall be con- 3.4.4 Transmitter Power Output - The transmitter powcr output shall be a minimum of 2.0 watts, . 9 Licensed by Information Handling ServicesNIIL-N-814 GOI3

40、(AS) 3.4.5 Acciiracy - 3.4.5.1 Navigational Accuracy - With the system properly installed and operating in the aircraft, the 400 Hz analog voltage outputs of heading velocity (Vha) and drift velocity (Vda) in aircraft coordinates, shall be accurate to O. 5% rms of ground speed (Vg) plus O. 5 knot. V

41、ertical velocity (Vza) shall be accurateto O. 5% rms of ground speed (Vg) plus 35 feet per minute, The accur- acy of the M= analog voltages of Vha and Vda sliall be accurate to 5% rms of ground speed (Vg) plus one knot and Vza shall be accurate to 5% rms of ground speed (Vg) plus 70 feet per minute.

42、 The stated accuracies shall be under the following conditions : (1) Vha is between -40 knots and +350 knots. (2) Pitch and roll angles are between -10 degrees and +10 degrees. (3) . The vector sum of Vha and Vda does not exceed 350 knots. (4) The vector sum of Vha and Vda does not exceed 60 knots w

43、hen Vha is negatiue. (5) Vda is between -100 knots and +lo0 knots. *3.4.5.2 Hover Resolution - The equipment shall detect the condition of a hover of a helicopter at altitudes up to 2500 feet over land and 1000 feet over water of sea states Codes 1 thru 5 in accordance with ASCC AIR STD 53/14. Helic

44、opter hover is defined as heading and drift velocities of less than *O. 5 knot and vertical velocity of less than +-15 feet per minute. 3.4.6 Memory Signal - When thc signal-to-noise ratio of any beam falls below that required to maintain accuracy stated in paragraph 3.4.5.1, the following shall occ

45、ur: (1) The last accurate velocity shall be stored as a memory function. (2) A memory signal shall be provided within one second to .external equipment by removal of a I-25 2 1 VDC signal. (3) A memory light indication shall be provided on the Control- Indicator within four scconds. The doppler loss

46、 and memory signals shall be capable of driving a load of 500 ohms, 10 Licensed by Information Handling Services3.4.7 outputs - * 3.4,7.1 DC Outputs - Analog DC voltages of heading, drift, and ver- tical velocities shall be provided. The appropriate output voltages shall be positive when the aircraf

47、t is moving aft, to port, or up. Conversely, the appropriate voltages shall be negative when the aircraft is moving forward, to starboard, or down. The tinie constmt of the DC outputs shall be 300 - + 100 milliseconds referenced to the AC outputs. With each output loaded with 500 ohms k 25 ohms, the

48、 DC outputs to the accessory equipment shall be as follows: Velocity Calibrated Max. Speed Scale Factor Heading Velocity 40 knots Drift Velocity 40 knots 2.5 miiivolts/knot 2.5 millivolts/knot Vertical Velocity 1000 FPM O. 1 millivolt/FPM The input circuits of the accessory equipment will be isolate

49、d from ground, Three 1000-ohm shunting resistors shall be provided within the equipment to provide the proper impedance load when only one indicator is used. 3.4.7.2.1 Scale Factor and Phase - Four hundred Hertz analog voltages of hcading and drift velocities shall be provided at a scale factor of 30 iiiillivolts per knot times the line voltage divided by 115, and the scale factor of the vertical velocity shall be 1.5 millivolts per foot per minute times the line voltage divided by 115. The respective output signals of Vha, Vda, and Vza shall be in phase with the refere