ARMY MIL-T-63533-1981 TURRET SUBSYSTEM UNIVERSAL (UTS) FOR ARMAMENT SUBSYSTEM HELICOPTER 20MM M97E1& M97E2《M97E1和M97E2型20MM直升机武器子系统通用(UTS)炮塔子系统》.pdf

《ARMY MIL-T-63533-1981 TURRET SUBSYSTEM UNIVERSAL (UTS) FOR ARMAMENT SUBSYSTEM HELICOPTER 20MM M97E1& M97E2《M97E1和M97E2型20MM直升机武器子系统通用(UTS)炮塔子系统》.pdf》由会员分享，可在线阅读，更多相关《ARMY MIL-T-63533-1981 TURRET SUBSYSTEM UNIVERSAL (UTS) FOR ARMAMENT SUBSYSTEM HELICOPTER 20MM M97E1& M97E2《M97E1和M97E2型20MM直升机武器子系统通用(UTS)炮塔子系统》.pdf（37页珍藏版）》请在麦多课文档分享上搜索。

1、27 December 1981 MILITARY SPECIFICATION TURRET SUBSYSTEM, UNIVERSAL (UTS) FOR ARMAMENT SUBSYSTEM, HELICOPTER, 2OMM: M97E1 AND M97E2 The specification is approved for use by the U.S. Army Armament Research and Development Command, and is available for use by all Departments and Agencies of the Depart

2、ment of Defense. 1. SCOPE 1.1 Scope. This specification contains quality assurance provisions and preparation for delivery for Universal Turret Subsystem (LITS) for the Armament Subsystem, Helicopter, 20MM: M97E1 and M97E2. 2. APPLICABLE DOCUMENTS 2.1 Government documents. 2.1.1 Specifications and s

3、tandards. Unless otherwise specified (see 6.2), the following specifications and standards of the issue listed in that issue of the Department of Defense Index of Specifications and Standards (DoDISS) specified in the solicitation, form a part of this specification to the extent specified herein. SP

4、ECIFICATIONS MILITARY MIL-E-5400 - Electronic Equipment, Airborne, MIL-E-6051 - Electromagnetic Compatibility MIL-W-63150 - Weapons and Support Materiel, General Specification for. Requirements, Systems. Standard Quality Assurance Provisions for. 1 .o IO5 Provided by IHSNot for ResaleNo reproduction

5、 or networking permitted without license from IHS-,-,-MIL-T-63533 LO = 779770b 0351758 7 STANDARDS MILITARY MIL-STD-105 - Sampling PrGcedures and Tables for Inspection by Attributes. MIL-STD-129 - Marking For Shipment and Storage. MIL-STD-410 - Nondestructive Testing Personnel Qualification and Cert

6、ification. MIL-STD-461 - Electromagnetic Interference Characteristics Requirements for Equipment. Characteristics. MIL-STD-704 - Aircraft Electric Power MIL-STD-810 - Environmental Test Methods. 2.1.2 Other Government documents, drawings, and publications. The following other Government documents, d

7、rawings, and publications form a part of this specification to the extent specified herein. DRAWINGS US ARMY ARMAMENT RESEARCH AND DQVELOPMENT COMMAND (ARRADCOM) 11830963 - Turret Subsystem, Universal PACKAGING DATA SHEET P11830963 c Turret Subsystem, Universal (Copies of specifications, standards,

8、handbooks, drawings and publications required by manufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer.) 2.1.3 Order of precedence. In the event of a conflict between the text of this specification a

9、nd the references cited herein, the text of this specification shall take precedence. 3. REQUIREMENTS 3.1 Materials. Materials shall be in accordance with the applicable drawings, specifications and standards. 3.2 Parts. All parts shall comply with applicable drawings, specifications and standards.

10、2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-63533 LO 7777706 0353759 7 I MIL-T-63533(AR) 3.3 Universal turret subsystem (UTS). The UTS shall comply with all requirements specified on Drawing (Dwg). F11830963, all associated drawings, and

11、with all requirements specified in applicable specifications and standards. The UTS covered by this specification shall be configured for use on AH-IS series helicopters. The UTS is an electric-powered turret which shall accomodate the M197 (20MM) gun. A simplified electrical block diagram is shown

12、in Figure 1. 3.3.1 Major component list. Major components of the UTS are listed in Table I. TABLE I. Major components. TITLE Turret Assembly Gun Drive Assembly Recoil Adapter Assembly Gun Control Assembly Logic Control Assembly Turret Control Assembly Storage/Feed Assembly - 20MM Drive Motor Assembl

13、y Pressure Transducer Assembly S 1 i der Assembly DRAWINGS F11830962 F198F734 Dll8 30 567 F11830418 F11830922 F11830908 F11830886 D905D490 C116C3555 C11830565 3.4 Characteristics. 3.4.1 Performance. 3.4.1.1 Positioning accuracy. The turret shall assume a position not to exceed 3 milliradians (mr) in

14、 the azimuth and elevation axes from a command static position for any position within the turret angular coverage. target on a hard stand of at least 50,000 pounds per inch spring rate and with zero error signal applied to the turret, shall be capable of firing a continuous 100-round burst so that

15、80 percent of the rounds fired fall within or cut a circle of diameter not greater than 12 milliradians. 3.4.1.2 Dispersion. The turret, mounted 1000 inches from the 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-T-63533 LO 9999906 0351960 5

16、M MIL-T-63533. (AR) U 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.4.1.3 Firing rates. The turret subsystem shall have a firing rate of 730 + 50 shots per minute (SPM) under standard conditions. - 3.4.1.4 Turret angular coverage. 3.4.1.4.1 Azi

17、muth. The turret shall traverse electrically 110 + 0.5 degrees to the right and 110 + 0.5 degrees to the left of the helicopter butt line 0.00 straight forward position. The turret rotation shall be limited by electrical stops set for a maximum of 3 degrees before reqching the mechanical stops. The

18、mechanical stops shall prevent turret rotation beyond 113 degrees to the right and left at full turret traverse velocity. 3.4.1.4.2 Elevation/depression. The turret shall traverse the weapon to the maximum elevation that can be allowed in reference to the airframe and the rotor tip path plane (see T

19、able II for elevation limits versus azimuth position). Electrical limits shall be provided in accordance with Table II. Mechanical stops shall prevent turret movement beyond the maximum elevation limits of Table II at full turret traverse velocity. Both elevation and depression shall be measured fro

20、m a plane parallel with the turret mounting surface. Mechanical and electrical stops shall be provided for depression. Depression angular travel for the weapon systems shall be 50 degrees minimum. TABLE II. Turret elevation limits. Degrees Degrees Elevation Azimuth Mechanical Electrical O0 100 200 3

21、0 40 56O Straight line to 1100 17.25O 14.75O 18.430 15.93O 20.500 18 .O00 21. 40 18.900 23.00 20.500 23.000 20.500 16 .50 13. loo NOTE: Mechanical limits shown are maximum. Electrical limit tolerance is + 0.5 degree and must always activate prior to contacting mechanical limit. 5 Provided by IHSNot

22、for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-b3533 LO m 777770b 0353962 7 m 3.4.1.5 Turret velocity and acceleration. 3.4.1.5.1 Azimuth slew rate. The turret azimuth slew rate shall be a minimum of 60 degrees per second. Full azimuth rotation of 220 degrees le

23、ft or right shall be a maximum of 4.2 seconds. Operation of the turret at any slew rate shall be smooth and not result in any oscillatory or erratic movements. 3.4.1.5.2 Elevation/depression slew rate. The turret elevation and depression slew rate shall be a minimum of 50 degrees per second. The max

24、imum travel (elevation to depression or depression to elevation) of at least 65 degrees shall be attained in a maximum of 1.8 seconds. Operation of the turret at any slew rate shall be smooth and not result in any oscillatory or erratic movement. 3.4.1.5.3 Azimuth velocity error. With the azimuth co

25、mmand signal to the turret changing at a constant rate corresponding to a gun movement of 5 degrees per second in azimuth, the position error shall not exceed 2 milliradians. 3.4.1.5.4 Elevation velocity error. With the elevation command signal to the turret changing at a constant rate corresponding

26、 to gun movement of 5 degrees per second in elevation, the position error shall not exceed 2 milliradians. 3.4.1.5.5 Slew acceleration. The UTS shall accelerate the turret at a minimum rate of 120 degrees/sec2 in any axis or combination of axes. The acceleration shall be determined using a step inpu

27、t to accelerate the turret from a standstill condition. Operation of the turret at maximum slew rate shall not result in any oscillatory or erratic movements, 3.4.1.5.6 Functional check-slew rate. During functional check or boresighting, at the operators discretion, a signal with reference to ground

28、 shall be supplied to the turret. As long as this signal is present, the turret/gun azimuth and elevation slew rates shall be limited to a 6 + 2 degrees per second velocity, This signal and slew rate shall have no adverse effect on boresight accuracy. for: 3.4.1.6 Weapon stowage. The UTS shall provi

29、de the capability a. Fixed forward firing b. Stow the gun during flight and during landing for ground clearance c. Stow the gun in the event of loss of system power at speeds up to 100 knots, 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-63

30、533 10 m 7797706 0351963 O m MIL-T-63533(AR) 3.4.1.6.1 Fixed forward firing. A fixed forward firing position shall be provided in which the gun will be positioned at O + 0.5 degree azimuth with respect to helicopter buttock line 0.00 and O + 0.5 degree elevation relative to the turret mounting surfa

31、ce in accordance with Drawing 11830963. The turret shall assume the fixed forward firing position upon command from the pilot or gunner and shall be capable of being boresighted in this posit ion. 3.4.1.6.2 Normal stow. The normal stow position for the UTS shall be O + 1 degree in azimuth and 11 + 1

32、 degree in elevation relative to-turret mounting surface. Whenever the UTS action switches are released or there is no fixed forward firing command, the weapon shall assume and maintain the normal stow position. 3.4.1.6.3 Emergency stow. In the event of an aircraft or UTS - power failure, the turret

33、 shall automatically return to O + 5 degrees in azimuth and a minimum of +10 degrees in elevation from the straight forward position at speeds up to 100 knots. The position shall be maintained under all flight conditions. The UTS shall provide a 28 Vdc signal to a panel indicator when the turret is

34、in the emergency stow condition. 3.4.1.6.4 stow locks. The stow locks or mechanisms shall hold the turret or gun in the stow position. They shall not hinder the movement of the UTS whenever the power drive is in operation. A method for manually releasing these locks shall be provided for ground serv

35、icing. 3.4.1.7 Firing interruption. The UTS gun firing circuit shall be interrupted and the weapon cleared without firing when any of the following conditions exisk: a. After any actuation command to fire any fixed forward firing wing store. b. The boreline of the firing barrel of the weapon differs

36、 from the commanded boreline position in either azimuth or elevation by more than 1.5 degrees, including 180 degrees out-of-concidence. c. Whenever the weapon is in stow or commanded to the normal stow position as described in 3.4.1.6.2, the weapon firing circuits shall be disabled. 3.4.1.7.1 Wing s

37、tores safety interlock. A safety interlock shall be included in the UTS to prevent wing stores firing unless the gun is within 5 degrees of the O degree azimuth position. 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_- _e- MIL-T-63533 10 rn 9999

38、906 03519bq 2 rn 3.4.1.7.2 Firing interruption indication. Whenever the gun firincr circuit is interrupted as described in 3.4.1.7, the UTS shall-provide a pulsed siinal with reference to ground to the sighting system, 180 pulses per minute at a 50 percent duty cycle. When the gun is not in an inter

39、rupt mode, this signal shall be a steady ground signal. 3.4.1.7.3 Time delay. A time delay of 1 t 0.5 seconds shall be incorporated in the UTS firing interruption-circuit before gun firing can be resumed after release of the RMS trigger switch. 3.4.1.8 Rounds counter. The turret subsystem shall prov

40、ide a signal pulse for each round cycled through it. This signal shall be used to actuate a helicopter cockpit indicator (which shows the number of rounds remaining in the ammunition feed system) and the turret mounted rounds totalizer of 3.4.1.8.1 (which shows total number of rounds cycled through

41、the turret assembly). The counting signal accuracy shall be correct to within t 3 percent of actual number of rounds cycled. (The cockpit indicator has a requirement of being correct to within 50 rounds per complement; however, the actual amount of ammunition remaining shall not be less than the amo

42、unt indicated.) The sensor that generates the signal pulse shall sense all UTS usage including live rounds, dummy rounds, and dry cycling. 3.4.1.8.1 Rounds totalizer. The rounds totalizer shall indicate the total number of rounds cycled through the subsystem. The rounds totalizer shall act independe

43、ntly of the gun. This rounds totalizer shall be non-resetable. 3.4.2 Weight, The components of the UTS, excluding gun and ammunition, shall not exceed the weight limits specified in below, Title Drawing Weight Limit (pounds ) Turret Assembly Electronic Components Gun Control Logic Control Turret Con

44、trol Pressure Transducer 11830962 11830418 11830922 11830908 116C3555 179,O 28.8 0.8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-e MIL-T-63533 LO W 9977906 0353965 4 W _ MIL-T-63533(AR) Feed System Mechanical Components 11830866 With Spring MS245

45、86-815 Recoil Adapter 11830567 Slider 11830565 Gun Drive Assembly 189F134 Bolts (8 used) MS21250-06004 93.9 23.8 3.4.3 Boresight. Boresighting shall be conducted using the provisions for azimuth and elevation on the UTS and it shall be performed by 2 persons in 15 minutes or less excluding aircraft

46、set-up time. 3.4.4 Reliability (first article inspection only). The UTS, excluding Government furnished guns, ammunition, links and other hardware, shall have a minimum acceptable mean-missions-between-failures of not less than 10 missions. A reliability mission is the expenditure of 750 rounds of 2

47、0MM ammo during a 1.4 hour flight. These requirements shall be demonstrated to a 95 percent confidence. In order to demonstrate this requirement, a minimum of 23,000 rounds will have to be fired. 3.4.5 Environmental conditions (first article testing only). The UTS shall operate and meet the performa

48、nce requirements of 3.4.1 under any- of the environmentai conditions, r reasonable combination of these conditions, as specified below: 3.4.5.1 Natural environment. UTS components shall operate and withstand storage in the worldwide conditions as listed below: 3.4.5.1.1 Altitude. Operating O-20,000

49、feet; nonoperating and storage O-50,000 feet. 3.4.5.1.2 Temperature. Operating -65O to +1250F, non- operating, and storage -650 to +160F. 3.4.5.1.3 Humidity. Operating in relative humidity up to 100 percent including conditions where condensation is in the form of water and frost. 3.4.5.1.4 Salt atmosphere. Operation after being subjected to MIL-STD-810, Method 509.1 for 48 ho