NAVY MS14168 REV A-1996 TIRE PNEUMATIC AIRCRAFT 22 X 6 6-10《22 X 6 6-10飞机汽轮胎》.pdf

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1、VSL43b8 REV A 9999932 0089131 760 MS SPECIFICATION SHEET I INCH-POUND 1 MS 14 168A(AS) 12 July 1996 SUPERSEDING MS 141 68(AS) 21 May 1976 TIRE, PNEUMATIC, AIRCRAFT, 22 X 6.6-10 This specification is approved for use by the Naval Air Systems Command, Department of the Navy, and is available for use b

2、y all Departments and Agencies of the Department of Defense. The requirements for acquiring the product described herein shd consist of this specification sheet and the issue of MIL-T-5041 listed in that issue of the Department of Defense Index of Specifications and Standards (DODIS S) specified in

3、the solicitation. SIZE PLY STATIC VERT iNFL BURST BEAD WEIGHT STATIC TREAD MOLD DEFLC RATING LOAD LOAD PRESS PRESS WIDTH LB. UNBAL 3/ SKID +3% - 1/ RATING LB. PSI PSI IN. MAX. 5112 OZ. DEPTH 4% LB. RATED MIN.- MAX. MIN. 22 X 6.6-10 22TL 14,150 60,000 304 1400 1.75 32.0 15 RIB 0.22 32 - 1/ TL- tubele

4、ss - 2/ Newtire - 31 The tire shall have not less than three and not more than five grooves. The tread grooves shall be shaped, insofar as practicable, so that foreign objects will not become trapped between the ribs. TIRE DATA The tire shall meet the following envelope dimensions for a new tire at

5、rated inflation and a grown and thrown tire at 400 psi inflation. RATED INFLATION GROWN AND THROWN MAX MAX TIRE DIMENSIONS (INCHES) MIN OUTSIDE DIAMETER 21.60 22.20 23.30 SECTION WIDTH 6.40 6.80 7.14 SHOULDER DIAMETER - 20.00 20.60 SHOULDER WIDTH 6.00 6.30 AMSC N/A 1 of5 FSC 2620 DISTlUl3UTION STATE

6、MENT A. Approved for public release; distribution is unlimited. Licensed by Information Handling ServicesflS141b8 REV A M 9999912 0089332 bT7 MS14168A(AS) RIM DATA (IN INCHES) WIDTH FLANGE LEDGE LEDGE FLANGE HEEL FLANGE FLANGE BETWEEN WIDTH DIAMETER WIDTH HEIGHT RADIUS RADIUS EDGE FLANGES RADIUS 5.5

7、0 0.875 10.00 1.75 1.00 0.250 0.625 O. 1275 The tire covered by this MS specification sheet shall be suitable for use and provide reasonable service life during all normal operations at takeoff and landing speeds indicated herein on all types of runways and on aircraft carriers. Test infiation press

8、ure: Test tire 1 shall be infiated to give a rated deflection at rated load. Test tires 2, 3, and 4 shall be inflated to 400 pounds per square inch (psi) adjusted for flywheel curvature. Test tire 1 shall complete sequences 1 through 8 as defined below without failure or visible deterioration other

9、than normal expected tread wear. The tire shall then be used for test K for information only with the results included in the qualification test report. NUMBER OF TEST DESCRIPTION SEQUENCE CYCLES TEST OPERATION 1 48 A TAXI - TAKEOFF 2 2 B TAXI - HIGH SPEED TAKEOFF 3 48 C LANDING - TAXI 4 2 D HIGH SP

10、EED LANDING - TAXI 5 1 E REJECTED TAKEOFF 6 24 F INBOARD CAMBERTAXI 7 24 G OUTBOARD CAMBERTAXI 8 4 H LONG TAXI Test tire 2 shall complete sequences 1 through 3 as defined herein without failure or visible deterioration other than normal expected tread wear. The tire shall then be used for test K for

11、 information only with the results included in the qualification test report. 2 Licensed by Information Handling Services8 MS 141 68A(AS) NUMBER OF TEST DESCRIPTION SEOUENCE CYCLES TEST OPERATION 1 45 I CATAPULT CONDITION 2 1 J BRULSE TEST 3 25 A TAXI - TAKEOFF Test tire 3 shall complete repeated cy

12、cles of test I until the tire shows evidence of failure or visible deterioration beyond normal tread wear. The tire shall complete not less than 45 successful cycles before failure. The results of this test are for information only with the number of cycles to failure noted in the qualification test

13、 report. Test tire 4 shall be infiated to 400 psi and loaded against a non-deflecting flat plate to a vertical load of 61,300 pounds at a camber of not less than 5.8 degrees. The tire shall remain fully infiated and intact. The loaded radius shall be measured and recorded during the vertical camber

14、loading procedure. This data may be used to prepare the load-deflection curve for the tire. Test tire 5 shall withstand test K. The minimum burst pressure shall be 1400 psi. TEST A Taxi - takeoff The tire shall be taxied on the flywheel at 30 miles per hour (mph) for 10,000 feet with 6,500 pounds lo

15、ad. Immediately following the taxi roll, the flywheel shall be accelerated at an average rate of 7.87 feet/sec/sec fiom O mph to a speed of 145 mph. The tire shall be unlanded after a takeoff roll distance of 2,920 feet has been covered. The initial takeoff load of 6,500 pounds shall be . decreased

16、linearly with time to 3,000 pounds at 26 seconds after the start of the takeoff roll and decreased to zero pounds at the end of the takeoff roll. TEST B Taxi - high speed takeoff The tire shall be taxied on the flywheel at 30 mph for 10,000 feet with 6,500 pounds load. Immediately following the taxi

17、 roll, the tire shall be loaded and its speed increased linearly as follows: TIME (SEC) LOAD &B) SPEED (MPH) DISTANCE (FT) O 7000 O O 13.6 6200 132 1319 14.1 5200 137 1418 26.6 900 223 4718 26.8 O 224 4784 TEST C Landing - taxi. The tire shall be landed against a flywheel rotating at a peripheral sp

18、eed of 156 mph. The flywheel speed shall then be decreased until a roll distance of approximately 4030 feet has been covered. The average deceleration rate shall be 3.52 feedsecsec between 156 and 132 mph, and 3 Licensed by Information Handling Services MS14168 REV A 9999912 0089134 4T MS14168A(AS)

19、9.68 feet/sec/sec between 132 and O mph. The tire load shall be increased linearly with time to 3,000 pounds in 1.5 seconds after landing, increased linearly with time to 3,600 pounds in 8.5 seconds, increased linearly to 5,900 pounds in 3.5 seconds, and maintained at 5,900 pounds until the tire has

20、 come to a stop. Immediately foliowing the landing cycle, taxi the tire on the flywheel for 10,000 feet under 5,500 pounds load at 30 mph. TEST D High speed landing - taxi. The tire shall be landed against a flywheel rotating at a peripheral speed of 2 18 mph. The flywheel speed shall then be decrea

21、sed until a roll distance of approximately 7,995 feet has been covered. The average deceleration rate shali be 3.26 feet/sec/sec between 21 8 and 198 mph and 8.0 feet/sec/sec between 198 and O mph. The tire load shall be increased linearly with time to 2,000 pounds in 1.5 seconds after landing, main

22、tained at 2000 pounds for 7 seconds, increased linearly to 4,200 pounds in 3.5 seconds, then decreased linearly with time to 3,400 pounds at 45 seconds after the start of the landing roll. Immediately following the landing cycle, taxi the tire on the flywheel for 10,000 feet under 3,400 pounds load

23、at 30 mph. TEST E Rejected takeoff The tire shall be taxied on the flywheel at 30 mph for 10,000 feet with 6,500 pounds load. Immediately following the taxi roll, the tire shall be loaded and its speed increased linearly as follows: TIME (SEC) O 13.7 14.0 20.2 23.8 23.9 25.0 61 .O LOAD &B) 6500 5200

24、 4300 2250 500 O 2,400 9,400 SPEED (MPH) O 132 135 184 206 207 225 O DISTANCE ET1 O 1329 1388 2839 3869 3899 4,248 10,188 Immediately &er the tire is stopped, continue tire taxi on the flywheel at 30 mph for 10,000 feet with 6,500 pounds vertical load. TEST F Inboard camber taxi. The tire shd be tax

25、ied against a flywheel rotating at a peripheral speed of 30 mph with 6,850 pounds load for a distance of 2,500 feet with the plane of the tire inclined inboard at an angle of 15 degrees. TEST G Outboard camber taxi. Perform the test F spectrum with the plane of the tire 15 degrees outboard. 4 Licens

26、ed by Information Handling Servicesc 9 b TEST H TEST I TEST J TEST K MS 14 168A(AS) Long taxi. The tire shall be landed on the flywheel rotating at a peripheral speed of 30 rnph for 30,000 feet with 6,500 pounds load. Catauult condition. The tire shall be accelerated from O to 80 mph within 6 second

27、s at a constant load of 2,000 pounds. Over a distance of 340 feet at a constant speed of 80 mph, the load shall be increased to 40,700 pounds within 0.55 second, decreased to 20,000 pounds within 0.3 second, increased to 40,700 pounds within 0.3 second, decreased to 30,000 pounds within 0.3 second,

28、and increased to 40,700 pounds within 0.45 second. The tire shall be maintained at a load of 40,700 pounds for the remainder of the catapult distance and then unlanded. Bruise test. The tire shall be loaded against a 1 -5/8 inch diameter length of plain round bar stock or arresting gear cable with a

29、 vertical load of 60,000 pounds. After release of this load, the tire shall be subjected to the same loading condition at a location 180 degrees from the initial point of loading. Burst test. The tire pressure shall be increased until the tire fails. The pressure, failure description, and location s

30、hall be reported in the qualification test report. Air retention. The tire shall be inflated to a pressure of 400 psi and allowed to stand for 24 hours at which time the pressure drop due to growth shall be replaced. The tire shall then stand for an additional 24 hours at which time the pressure sha

31、ll be measured and the tire inspected. The air pressure loss shall not exceed 5 percent and the tire shall not reveal any appearance and performance defects such as sidewall blisters, tread separation, etc ualification test report. The qualification test report shall list the results of all qualific

32、ation tests and construction details of the qualification test sample in the general form shown in figure 4 of MIL-T-504 1 with dimensions listed at a rated inflation and 400 psi. A sketch of the tire profile at rated inflation and 400 psi shall be included in the report. The report shall list the manufacturers test number. Preparing Activity: Navy - AS (Project 2620-N3 1 O) 5 Licensed by Information Handling Services