1、17 August 1973 . SUPERSEDING MIL-L-48063 (MU ) 18 April 1972 MILITARY SPECIFICATION LAUNCHER, ROCKET, LAU 68B/A SHIPPING ASSEMBLY This specification is approved for use by all activities of the Department of the Army. i 1. SCOPE 1 .l This specification covers the technical requirements , qual i ty a
2、ssurance and reliability provisions and special requirements not covered by the drawings for the parts and assembly of an external store type rocket launcher for shipping, storing, and launching 2.75 Inch Folding Fin Aircraft Rockets (FFAR), 2. APPLICABLE DOCUMENTS 2.1 The following documents of the
3、 issue in effect on date of initiation for bids or request for proposal, form a part of this specification to the extent specified herein. 0 SPECIFICATIONS MI L I TARY MIL-A-2550 MIL-A-8591 MIL-W-22248 MIL-S-45743 “ ;=. - STANDARDS MILITARY MIL-STD-i o5 Ammuni tion and Special Weapons , General Spec
4、ification For Airborne Stores and Associated Suspension Equipment, General Design Cri teria For lrleldments , Aluminum and Aluminum Al 1 oy Sol deri ng , Manual Type, High Re1 i abi 1 i ty Electrical , Electronic, Instrument, Comunication, and Radar for Aerospace, and Control Systems , Procedures Fo
5、r Sampling Procedure and Tables for Inspection by Attributes Licensed by Information Handling ServicesMIL-STD-129 MIL-STD-81 O MIL-STD-1167 MIL-STD-1168 MIL-STD-1235 DRAWINGS ARMY 3 56AS1 O0 Marking for Shipment and Storage Environmental Test Methods Ammunition Data Card Lot Numbering of Ammunition
6、Si ngl e and Mu1 ti 1 eve1 Continuous Sampl ing Procedures and Tables for Inspection by Attributes c. - Launcher, Rocket LAU 68B/A Shipping Assembly (Copies of specifications, standards, drawings and publicatins required by suppliers in connection with specific procurement functions should be obtain
7、ed from the procuring activity or as directed by the contract1 ng off i Cer). 3, REQU I REMENTS 3.1 Parts and materials. Parts and materials used in the manufacture of the rocket launcher shall conform to the applicable specifications as set forth herein and as listed on the pertinent drawings. .3.2
8、 Design and construction. 3.2.1 The design and contruction of the launcher and parts thereof shall be in accordance with drawings and this specification. The launcher shall be capable of shipping, storing and launching 2.75 Inch folding Fin Aircraft Rockets and will be tested using rockets with the
9、following physical characteristics: weight - 20.5 + 0.5 pounds; length - 53 t 2 inches; center of gravity 22 .t 2 inches fFom the forward end of therocket. The launcher shall be capableof use with both high and low speed fixed wing aircraft and rotary wing aircraft. The intervalometer (see 6.3) shal
10、l be capable of being assembled into an Aircraft Rocket Launcher and controlling its rocket firing sequence under all flight and environmental conditions. 2 Licensed by Information Handling Services 3.2.2 Soldering. All soldering shall be in accordance with MIL-S-45743. 3.2.3 Painting limitations. N
11、either primer nor paint shall be applied to threads, bearing or working surfaces as indicated in drawings and specifications. 3.2.4 Welding. Production of weldment shall not proceed before Government approval of the welding procedure and Qf the workmanship required by MIL-14-22248, Class III. 3.2.5
12、Epoxy and adhesive. Epoxy and adhesive shall conform to those specifications appearing on the applicable drawings and shall be applied in accordance with recommendations of the manufacturer, * t 3.2.6 Spring embrittlement. None of the springs used in the fabrication of the launcher shall break when
13、extended or distorted to the point of minimum permanent distortion. 3.3 Launcher electrical wiring, There shall be no failure of electrical wiring due to handling or environmental conditions. m 3.3.1 Grounding. All external parts of the launcher and intervalometer, when installed, shall be at ground
14、 potential regardless of selector switch position at all operating voltages. The resistance between each detent and every other detent shall be 0.1 ohm maximum. 3.3.2 Insulation resistance. The insulation resistance of the wiring harness after installation in the launcher shall be a minimum of 2 meg
15、ohms at 500 volts direct current (VDC), from conductor to conductor and conductor to ground. 3.3.3 Miring harness continuity. The continuity resistance of the . wiring harness after installation in the launcher shall not exceed 0.2 ohm. ;. L 3.4 Intervalometer performance requirements. The intervalo
16、meter shall be capable of providing firing pulses to launch nineteen (19) 2.75 Inch Folding Fin Aerial Rockets. The intervalometer shall operate in accordance with al 1 requirements when input power of 20 to 30 VDC is supplied through a 5 ohm, 25 watt resistor. The vol tage may be interrupted as a r
17、esult of any type of contact bounce and or switch chatter for a minimum of 5.0 milliseconds (ms) upon application of power without interferring with the proper operation of the intervalometer. 3.4.1 Single fire. The intervalometer in single fire mode shall supply a firing pulse to two Output Pins fo
18、r each of the first nine applications of power. The firing pulse shall be a minimum of 1 .O0 ampere for 10 milliseconds (ms) minimum to each output pin within 30 ms after application of power. 3 Licensed by Information Handling Services3.4.2 Ripple fire. The intervalometer in ripple mode shall provi
19、de firing pulses to launch a full complement of nineteen (19) rockets in sequence. The sequence shall be pairs of pulses for the first nine selector switch positions. The first firing pulse shall be applied to the corresponding pin within 30 ms after application of power, and the interval between pu
20、lses shall be no less than 54 ms nor more than 70 ms. Each firing pulse shall be 1.00 ampere minimum per output pin with a dwell of 10 ms minimum. The overall time in ripple mode shall not exceed 700 ms from application of power to load position. ments of 3.4 through 3.4.2 when the rocket motor is s
21、imulated by use of a dummy load consisting of a 1.0 plus or minus (2) 10 percent (%) ohm resistor connected for 12 t 2 ms between each firing pin and ground, The intervalometer shall fnction properly when tested using a 1 .O f I 10% ohm load to simulate firing a single rocket. This will insure the i
22、ntervalometer will function properly when used in a launcher which fires one rocket per pulse (a 7 tube launcher) and also in a launcher which fires a pair of rockets per pulse (a 19 tube launcher). 3.4.3 Simulated firing. The intervalometer shall meet all require- .I 3.4.4 Radiation hazard provisio
23、n. The intervalometer shall ground all output pins when in the load and arm positions. The intervalometer shall not sequence out of the load position when power is applied. During operation, all output pins shall be grounded except those receiving a firing pulse. Grounding shall be verified by the p
24、resence of 5.0 millivolts maximum on any grounded output during application of power, The ground circuit shall ground the output with a resistance of not more than 0.1 ohm. 3.4.5 Bypass capability. The intervalometer in the ripple mode shall be capable of continuing through the entire sequence with
25、one or more output pins short circuited to ground or open circuited. In the slngle step mode, the intervalometer shall , in the event of a short circuit to ground or an open circuit on output pins or pin, attempt to fire and remain in place. The next application of power will sequence the intervalom
26、eter to the next station. The intervalometer bypass capability shall withstand short circuit current without damage. L 3.4.6 “Load“ circuit. The intervalometer shall have a load and arm switch. The load position shall internally ground all output circuits and prevent the intervalometer from being el
27、ectrically sequenced. The internal grounding shall be accomplished by means of the ground circuit 3.4.8. i 3.4.7 tArmi circuit. The intervalometer shall have a selector arm position to provide the ground circuit to all outputs, but wily al so allow for electrical sequencing. The intervalometer shall
28、 be manually switched from load position to the arm position to provide positive arming of the unit. * Licensed by Information Handling Services3.4.8 Ground Circuit. The intervalometer shall provide a grounding circuit to insure safety during loading and operation. The ground circuit shall ground al
29、l output pins when the intervalometer is in the load or arm position. As the intervalometer is advancing through its sequence, the ground circuit shall individually ground each output except those being energized. The ground circuit shall ground the output with a resistance of not more than 0.1 ohm.
30、 Grounding shall be verified by the presence of no more than 5 millivolts on any grounded output during the appl ication of power. 3.4.9 Sequencing. The intervalometer shall sequence through the output stations as called out on applicable drawings. The output stations may or may not be loaded. The i
31、ntervalometer shall continue through the sequence pattern even if power is removed and then re-applied. The time between application of power and output pul se shall not exceed 30 mill isecands. 3.4.10 Life. The intervalometer shall meet all requirements of 3.4 through 3.4.9after a minimum of 400 cy
32、cles in single mode and 400 cycles in ripple mode, 3.4.11 Environmental. The intervalometer shall meet all of the requirements of 3.4 through 3.4.9 before or after, as required, exposure to the following environmental conditions: 3.4.11.1 Humidi ty. In accordance with MIL-STD-810, Method 507, Proced
33、ure I. 3.4.11.2 Sand and dust. In accordance with MIL-STD-810, Method 51 O. i 3.4.11.3 Shock test. In accordance with MIL-STD-810, Method 516, Procedure IV, Figure 516-2, Amplitude A, Duration C. 3.4.11.4 Acceleration test, h accordance with MIL-STD-81 O, Method 513, Procedure II, Table 513-11. I 3.
34、4.11.5 High temperature. In accordance with MIL-STD-810, Method 501 , Procedure I for 8 hours min. 3.4.11.6 Low temperature. In accordance with MIL-STD-810, Method 502, Procedure I for 8 hours min. , at minus (-) 54 degrees (O) C (-65OF). 3.4.11.7 Salt fog test. In accordance with MIL-STD-810, Metho
35、d 509. 3.4,11.8 Vibration test. In accordance with MIL-STD-810, Method 514, Procedure I, Curve J, and Procedure II, Part 3, Curve AF. i. 5 Licensed by Information Handling Services3.4.11.9 Static Firing. The intervalometer shall be capable of being installed in a launcher, approved by the Procuring
36、Activity, and of firing rockets in accordance with 3.4. 3.5 Launcher performance requirements. The launcher shall safely and reliably carry and launch seven (7) 2,75 Inch Folding Fin Aircraft Rockets. The launcher shall operate in accordance with al 1 requirements when input power of 20 to 30 VDC is
37、 supplied through a 5 ohm, 25 watt resistor. The voltage may be interrupted as a result of any type of contact bounce and or switch chatter for a maximum of 5.0 milliseconds (ms) upon application of power without interferring with the proper operation of the intervalometer. 3.5.1 .Launcher functiona
38、l test. The launcher shall meet all the requirements of 3.4 through 3.4.9 when the rocket motor is simulated by use of a dummy load consisting of a 1 .O + 10% ohm resistor connected between each contact and the corresponding dtent for 12 5 2 ms duration. When the intervalometer is installed in a lau
39、ncher, only the first seven (7) outputs are used, 3.5.2 Loading. When assembled in the launcher the total of all irregularities in any tube must not be sufficient to prevent loading or removal of a 2.75 Inch FFAR. The force to move the rocket through the tube shall not exceed 20 pounds. 3.5.3 Prepar
40、ation for firing. Contact arm must adequately contact the rocket igniter contact surface to sufficiently transmit a pulse which shall fire a rocket. 3.5.4 Detent operation. The rocket must be positively held in place in the tube by the detent assembly regardless of launcher orientation or environmen
41、t. The detent shall not release a rocket at a pull force of 310 pounds minimum and 350 pounds maximum, The rocket locking portion of the detent shall fully retract to release the rocket when 20 pounds force is applied to the detent perpendicular to the axis of the tube. The detent shall electrically
42、 ground the rocket. shall be pressurized with air to 5.0 ponds per square inch (psi) and the leak rate shall not exceed 3.0 centimeters per second (sec). 3.5.5 Pressure retention. The launcher shipping assembly (356AS100) 3.5.6 Environmental. The launcher shall safely and reliably carry and launch s
43、even (7) 2.75 Inch FFAR after subjection to the following condi ti ons : 3.5.6.1 High temperature. The launcher without shipping covers shall be subjected to High Temperature in accordance with MIL-STD-810, Method 501 Procedure I. 6 Licensed by Information Handling ServicesL 3.5.6.2 Low temperature.
44、 The launcher without shipping covers shall be subjected to low temperature in accordance with MIL-STD-810, Method 502, at -54C (-65OF) for 24 hours min. 3.5.6.3 Shock. The loaded launcher without shipping covers shall he subjected to shockin accordance with MIL-STD-810, Method 516, Procedure I with
45、 the exception that only the vertical and longitudinal axis shall be tested, The vertical half size shock pulses shall have a peak of 10.0 gs and an 18 ms duration and the longitudinal half sine pulses shall have a peak of 13.5 gs and an 18 ms duration. The launcher shall retain all the inert rocket
46、s without damage at all “g“ levels within the tolerance. 3.5.6.4 Vibration. The loaded launcher without shipping covers shall be subjected to vibration in accordance with MIL-STD-810, Method 514, Procedure I, Curve C. 3.5.6.5 Salt fog_. The launcher shall be subjected to Salt Fog in accordapce with
47、MIL-STD-810, Method 509 with the exception that the test period shall be 50 hours, 3.5.6.6 Static Loading Tests. The launcher, without shipping covers, shall be subjected .to the following static loads in accordance with MIL-A-8591, The launcher center section shall be sumended from a pylon simulati
48、ng a bomb rack having 14“ suspension. Applicationof test loadings shall be achieved in such a manner that the loads are equally dlvided among the launching tubes a and are uniformly distributed over the length of each. The side (horizontal) and downward loadings shall be applied simultaneously. Load
49、ings shall be as fo1lows: a. 2750 5 20 pounds (13 g) acting downward. b. 1800 - + 20 pounds (8.5 g) to the side(horizonta1). c. 2750 - + 20 pounds (13 g) acting rearward. d. 2750 - + 20 pounds (13 g) acting forward. 3.5.6.7 Rough handling. The launcher, fully loaded, shall be dropped four times from 30 + 1 inch at 45 + 1 degree angle onto a solid concrete surface. SubsequenTly, the launchr shall be subjected to and pass the Pressure Retention Test. 3.5.6.8 Firing. The launcher shall be capable of igniting all functional rocket in a normal manner in both single and ripple modes
