1、INCH-POUNDMIL-DTL-48568Dw/Amendment 117 December 2003SUPERSEDINGMIL-DTL-48568D24 May 1996DETAIL SPECIFICATIONCATAPULT, AIRCRAFT EJECTION SEAT, CKU-7/A ASSEMBLYThis specification is approved for use by the Naval Sea Systems Command, Department of the Navy, and isavailable for use by all Departments a
2、nd Agencies of the Department of Defense.1. SCOPE1.1 Scope. This specification covers the requirements for the CKU-7/A Rocket Catapult.2. APPLICABLE DOCUMENTS2.1 General. The documents listed in this section are specified in sections 3 and 4 of this specification. Thissection does not include docume
3、nts cited in other sections of this specification or recommended for additionalinformation or as examples. While every effort has been made to ensure the completeness of this list, documentusers are cautioned that they must meet all specified requirements of documents cited in sections 3 and 4 ofthi
4、s specification, whether or not they are listed.2.2 Government documents.2.2.1 Specifications, standards, and handbooks. The following specifications, standards, and handbooksform a part of this document to the extent specified herein. Unless otherwise specified, the issues of thesedocuments are tho
5、se listed in the issue of the Department of Defense Index of Specifications and Standards(DoDISS) and supplement thereto, cited in the solicitation (see 6.2).SPECIFICATIONSMILITARYMIL-S-9479 Seat System, Upward Ejection, Aircraft, General Specification forMIL-P-46994 Pellet, Boron Potassium NitrateC
6、omments, suggestions, or questions on this document should be addressed to Commander, Indian Head Division, NavalSurface Warfare Center, Technical Information Branch (Code 4230), 101 Strauss Avenue, Indian Head, Maryland 20640-5035, or emailed to pennlfih.navy.mil. Since contact information can chan
7、ge, you may want to verify the currency of thisaddress information using the ASSIST Online database at www.dodssp.daps.mil.AMSC N/A FSC 1377DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.Provided by IHSNot for ResaleNo reproduction or networking permitted without li
8、cense from IHS-,-,-MIL-DTL-48568D(OS)2MIL-P-82680 Propellant, Solid, CompositeMIL-P-82683 Propellant, Solid, CompositeSTANDARDSMILITARYMIL-STD-413 Visual Inspection Guide for Elastomeric O-ringsMIL-STD-414 Sampling Procedures for Inspection by VariablesMIL-STD-453 Inspection, RadiographicMIL-STD-810
9、 Environmental Test Methods and Engineering GuidelinesMIL-STD-1168 Ammunition Lot NumberingMIL-STD-1907 Inspection, Liquid Penetrant and Magnetic Particle, Soundness Requirements forMaterials, Parts, and WeldmentsDOD-STD-2101 Classification of CharacteristicsMIL-STD-2102 Aircrew Escape Propulsion Sy
10、stems; Vibration and Shock Tests forMS17983 Compass, Magnetic, Pilots Standby(Unless otherwise specified, copies of federal and military specifications and standards are available fromStandardization Documents Order Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094.)2.2.2 Other Gove
11、rnment documents, drawings, and publications. The following other Governmentdocuments, drawings, and publications form a part of this document to the extent specified herein. Unlessotherwise specified, the issues are those cited in the solicitation.DRAWINGSNaval Surface Warfare Center, Indian Head D
12、ivision (CAGE Codes 19200 and 19203)DL11820361 Catapult, Aircraft Ejection Seat, CKU-7/A Assembly(Application for copies should be addressed to: Commander, Indian Head Division, Naval Surface WarfareCenter, Attn: Data Control Branch (Code 8410), Indian Head, MD 20640-5035.)2.3 Non-Government publica
13、tions. The following documents form a part of this document to the extentspecified herein. Unless otherwise specified, the issues of the documents which are DOD adopted are thoseProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-48568D(OS)3liste
14、d in the issue of DODISS cited in the solicitation. Unless otherwise specified, the issues of documents notlisted in the DODISS are the issues of the documents cited in the solicitation (see 6.2).AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM)E 1444 Standard Practice for Magnetic Particle Examinat
15、ion(Application for copies should be addressed to the American Society for Testing and Materials, 1916 RaceStreet, Philadelphia, PA 19103.)AMERICAN SOCIETY FOR QUALITY CONTROLANSI/ASQC Z1.4 Sampling Procedures and Tables for Inspection by Attributes(Application for copies should be addressed to the
16、American Society for Quality Control, PO Box 3005, 611E. Wisconsin Ave., Milwaukee, WI 53201-4606.)(Non-Government standards and other publications are normally available from the organizations thatprepare or distribute the documents. These documents also may be available in libraries or otherinform
17、ational services.)2.4 Order of precedence. In the event of a conflict between the text of this document and the referencescited herein, the text of this document takes precedence. Nothing in this document, however, supersedesapplicable laws and regulations unless a specific exemption has been obtain
18、ed.3. REQUIREMENTS3.1 First article. When specified (see 6.2), a sample shall be subjected to first article inspection (see 6.4) inaccordance with 4.3.3.2 Materials. All materials, parts, and assemblies shall be in accordance with DL11820361 and thisspecification.3.2.1 Primary components. Only prima
19、ry components from a single primary component lot shall be used ina production lot of loaded rocket catapults.3.2.2 Propellant. The rocket motor propellant shall be in accordance with MIL-P-82680, Class I.3.3 Age of explosive components. The following paragraphs give the requirements for controlling
20、 the ageof explosive components.3.3.1 Propellant. The propellant is defined as the rocket motor grain (sleeve and grain assembly perDrawing 11820365) and the cartridge grain (cartridge grain assembly per Drawing 10534739). For purposesof this section, loaded is defined as when the rocket catapult lo
21、t is released for lot acceptance testing.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-48568D(OS)43.3.1.1 Rocket motor grain. The rocket motor grain shall be loaded within 360 days of the oldest rocketmotor propellant mix.3.3.1.2 Cartridge
22、grain. The cartridge grain shall be loaded within 180 days of the oldest cartridgepropellant mix.3.3.2 Other explosive components. The other explosive components are the percussion primer (Drawing11820864) and the BKNO pellets (MIL-P-46994, Type II-A).33.3.2.1 Percussion primers. The percussion prim
23、ers shall be loaded within 24 months of manufacture andcertification or within 12 months of recertification. Loaded is defined as when the cartridge case is crimpedonto the cartridge head assembly.3.3.2.2 BKNO pellets. The BKNO pellets shall be loaded into the cartridge head assembly within 123 3mon
24、ths of the certification date. Loaded is defined as when the rocket catapult lot is released for lotacceptance testing.3.4 Performance and product characteristics. The rocket catapults shall meet the following performanceand product characteristics when test fired at G2165, 70, and 165G45F using an
25、ejected weight of 459 pounds. Therocket angle shall be set at 40 degrees (see Drawing 11820363).3.4.1 Ballistics. The rocket catapults shall meet the ballistic requirements specified in table I.3.4.1.1 Other requirements. In addition to meeting the ballistic requirements, none of the following shall
26、occur during test firing of rocket catapults:a. No unit component, including but not limited to catapult components, O-rings, springs, orpieces of propellant shall be ejected. The only exceptions are small pieces of the cartridge grainABS tubing that are regularly ejected after rocket motor separati
27、on.b. No component subject to loading shall fail.c. No excessive nozzle erosion, hot spots, or burnthrough shall occur.d. No leakage of ballistic gas past a sealing surface, except for nozzle/retainer interface O-ring,shall occur.3.4.2 Initiation. Initiation input for test is 1,100 psi pressure sour
28、ce producing a 30,000 to 50,000 psi persecond positive rate of change.3.5 Torque. The booster tube (Drawing 10551422) and head (Drawing 10551412) assembly and thelauncher tube (Drawing 10551423) and mount (Drawing 10551413) assembly, when seated with a torque of400 +50, G210 inch-pounds, shall not b
29、e loosened or deformed when subjected to a breakaway torque of 200inch-pounds.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-48568D (OS)5TABLE I. Ballistic performance requirements for a 459-pound ejected weight.65 2F 70 2F 165 2FParameterMi
30、n Max Min Max Min MaxCatapultInitiation pressure, Pact(psi) 250 550 250 550 250 550Rate of change of acceleration, A (g/sec), see 6.3.5 - 300 - 300 - 300Separation velocity1/, CSv (ft/s), see 6.3.4 37 - 40 - 42 -Ignition delay, CId (ms), see 6.3.2 - 30 - 30 - 30Axial thrust, CFmax (lbf), see 6.3.11
31、- 7000 - 7000 - 7300Launch time, CLt (ms), see 6.3.3 - 210 - 200 - 200Dynamic response index, DRI, see 6.3.10 - 18 - 18 - 22Acceleration, A (g), (reference)3/- 20 - 18 - 20Rocket MotorResultant impulse, RIr (lbf/sec), see 6.3.9 1100 - 1100 - 1100 -Ignition delay, RId (ms), see 6.3.6 - 25 - 25 - 25Ac
32、tion time, RAt (ms)2/, see 6.3.7 - 550 - 450 - 450Resultant thrust, RFmax (lbf), see 6.3.8 - 7350 - 7350 - 7600Thrust angle (reference)3/40 40 401/ Nominal separation velocities are: 39.0 ft/s at -65 F and 47.0 ft/s at 165F.2/ Nominal rocket motor action time is: 460 ms at -65F and 330 ms at 165F.3/
33、 Record for information only.3.6 Residual magnetism. The rocket catapult assembly, when passed in front of an MS17983 compass alongthe entire length of the catapult (see figure 1) shall not cause the compass indicator to deflect more than 5degrees in either direction. The test shall be performed in
34、an area free from local magnetic effects.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-48568D(OS)Plan ViewNOTE: Device and compass shall lie in a common horizontal planeFIGURE 1. Layout for determination of residual magnetism in device.3.7
35、Nozzle O-ring integrity. The nozzle ball/retainer O-ring shall not show any leakage throughout theoperational range of the swivel nozzle when pressurized to 40 psig. Application of the 40-psig internal pressureto the sealed nozzle/retainer/sleeve assembly shall cause the nozzle to rotate fully.3.8 R
36、elease O-ring integrity. The release O-rings shall show no indications of leakage when the launchertube/mount assembly is pressurized to 200 psig.3.9 Nozzle/sleeve actuation force. The force required to move the sleeve an adequate distance to cause fullrotation of the nozzle in a complete nozzle/ret
37、ainer/sleeve assembly shall not exceed 25 lbf.3.10 Protective finish. Protective finish shall be in accordance with the applicable specifications and drawingsand shall apply to all surfaces of the component regardless of configuration.3.11 Radiographic. Each loaded rocket catapult shall be examined
38、radiographically to ascertain the presence,condition, and correct placement of internal components.3.12 Hydrostatic pressure. The components listed in table II shall withstand the internal hydrostatic pressurespecified for 15 seconds minimum when tested in accordance with 4.4.6.7.6Provided by IHSNot
39、 for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-48568D(OS)7TABLE II. Hydrostatic pressure requirements.Component Drawing Hydrostatic pressure (psi)Motor Tube 10551424 5,000Launcher Tube 10551523 11,000Booster Tube 10551422 11,0003.13 Environmental. The rocket
40、catapult assemblies shall withstand the environmental conditioning of3.13.1 through 3.13.4. Rocket catapult assemblies subjected to this conditioning shall show no evidence ofdeterioration of propellant or disarrangement of components when examined in accordance with 4.4.6.1 andshall meet the ballis
41、tic performance requirements of 3.4 when test fired in accordance with 4.3.2.3.13.1 High temperature. The rocket catapult shall withstand the high temperature test of 4.3.1.1.3.13.2 Vibration. The rocket catapult shall withstand the vibration test of 4.3.1.2.3.13.3 Temperature shock. The rocket cata
42、pult shall withstand the temperature shock test of 4.3.1.3.3.13.4 Thirty-day storage test. The rocket catapult shall withstand the 30-day storage test of 4.3.1.4.3.14 Identification markings. Each rocket catapult shall be marked in accordance with Drawing 11820361with an identification label, a warn
43、ing label, and an installation label.3.14.1 Production lot designation. The production lot number shall follow MIL-STD-1168. Theconstruction of the lot number shall be as follows:XXX 95 D 002 -007abcdeWhere:a = Manufacturers identification code.b = The year of manufacture of the oldest batch of cart
44、ridge propellant in the lot.c = The month of manufacture of the oldest batch of cartridge propellant in the lot expressed asan alpha code in accordance with 4.1.3 of MIL-STD-1168.d = Lot interfix number (controlled by Indian Head Division, Naval Surface Warfare Center,Code 5120, Indian Head, MD 2064
45、0-5000 or contracting activity).e = Lot sequence number - lot number (manufacturer is responsible for the assignment of lotnumbers.3.15 Workmanship. The workmanship shall be that required by the applicable drawings, referencedspecifications, and the best industrial practices governing the quality pr
46、oduction of interchangeable parts formaintaining the dimensions, finishes, tolerances, and quality specified herein. All components and assembliesshall be free from burrs, contamination, corrosion, sharp edges, or foreign material which could result inmalfunction of the unit or components, or be a s
47、afety hazard in handling.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-48568D(OS)84. VERIFICATION4.1 Classification of inspections.a. First article inspection (see 4.3)b. Conformance inspection (see 4.4)4.2 Inspection conditions. Unless oth
48、erwise specified in the contract or purchase order (see 6.2), inspectionconditions shall be as follows:a. Temperature: Room ambient 65 to 95G45Fb. Altitude: Normal groundc. Vibration: Noned. Humidity: Room ambient to 95 percent relative, maximum4.3 First article inspection. Unless otherwise specifie
49、d in the contract or purchase order (see 6.2), a firstarticle sample shall consist of three blocks of cured propellant, two sleeve and grain assemblies, and eighteenloaded catapult assemblies. The rocket catapult assemblies shall be adapted for pressure transducers (see 6.7)and all first article samples shall be manufactured using the same methods and procedures proposed forproduction. The firs
