1、- MIL-DTL-8287bA 999990b 2005405 TTb MIL-DTL-S2876A(OS) 4 Aumist 1995 SUPERSEDING 15 November 1993 MIL-C-82876(OS) DETAIL SPECIFICATION CATAPULT, AIRCRAFT EJECTION SEAT, CKU-5B/A ASSEMBLY lis specijkation is approved for use by the Naval Sea Systems Command, Depanment of the Navy, and is available f
2、or use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers the requirements for the Rocket Catapult CKU-SB/A loaded assembly. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in sections 3 and 4 of this sp
3、ecification. This section does not include documents cited in other sections of this specification or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet ali specified requir
4、ements documents specified in sections 3 and 4 of this specification, whether or not they are listed. 2.2 Government documents. 2.2.1 Specifications, standards, and handbooks. The following specifications, standards, and handbooks form a part of this document to the extent specified herein. Unless o
5、therwise specified, the issues of these documents are those listed in the issue of the Department of Defense Index of Specifications and Standards (DODISS) and supplements thereto, cited in the solicitation (see 6.2). SPECIFICATIONS MILITARY MIL-s-9479 Seat System, Upward Ejection, Aircraft, General
6、 Specification for MIL-P-46994 Pellet. Boron Potassium Nitrate Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Commander, Indian Head Division, Naval Surface Warfare Center, Standardization Bran
7、ch (Code 8420), 101 Strauss Avenue, Indian Head, MD 20640-5035, by using the Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by sending a letter. AMSC NIA FSC 1377 DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.
8、Licensed by Information Handling ServicesProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- , MIL-DTL-8287bA 99999Ob 200540b 932 MIL-P-82652 MIL-P-82680 STANDARDS MILITARY MIL-STD-413 MIL-STD-414 MIL-sTD-453 MIL-STD-8 10 MIL-STD-1168 MIL-STD-1907 DOD-S
9、TD-2 10 1 MIL-STD-2 102 MS17983 MIL-DTL-82876A(OS) Propellant, Solid, Composite Propellant, Solid, Composite Visual Inspection Guide or Elastomeric O-rings Sampling Procedures for Inspection by Variables Inspection, Radiographic Environmental Test Methods and Engineering Guidelines Ammunition Lot Nu
10、mbering Inspection, Liquid Penetrant and Magnetic Particle, Soundness Requirements for Materials, Parts, and Weldments Classification of Characteristics Aircrew Escape Propulsion Systems; Vibration and Shock Tests for Compass, Magnetic, Pilots Standby (Unless otherwise specified, copies of federal a
11、nd military specifications and standards are available from Standardization Documents Order Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 191 11- 5094.) 2.2.2 Other Government documents, drawings, and publications. The following other Government documents, drawings, and publications form a
12、 part of this document to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation. DRAWINGS Naval Surface Warfare Center, Indian Head Division (CAGE Codes 19200 and 19203) DL66101 13 Catapult, Aircraft Ejection Seat, CKU-SB/A Assembly (Application for
13、copies should be addressed to: Commander, Indian Head Division, Navai Surface Warfare Center, Attn: Data Control Branch (Code 8410), Indian Head, MD 20640-5035.) 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-8287bA = 9999906 2005407 679 2
14、.3 Non-Government publications. The following documents form a part of this document to the extent specified herein. Unless otherwise specified, the issues of the documents which are DOD adopted are those listed in the issue of DODISS cited in the solicitation. Unless otherwise specified, the issues
15、 of documents not listed in the DODISS are the issues of the documents cited in the solicitation (see 6.2). AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM) E 165 Liquid Penetrant Inspection Method E 1444 Standard Practice for Magnetic Particle Examination (Application for copies should be addresse
16、d to the American Society for Testing and Materials, 1916 Race Street, Philadelphia, PA 19103.) AMERICAN SOCIETY FOR QUALITY CONTROL ANSUASQC Z1.4 Sampling Procedures and Tables for Inspection by Attributes (Application for copies should be addressed to the American Society for Quality Control, PO B
17、ox 3005, 61 1 E. Wisconsin Ave., Milwaukee, WI 532014336.) (Non-Government standards and other publications are normally available from the organizations that prepare or distribute the documents. These documents also may be available in libraries or other informational services.) 2.4 Order of preced
18、ence. In the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. REQUIREMENTS 3.1 first artic
19、le. When specified (see 6.2), a sample shall be subjected to first article inspection (see 6.5) in accordance with 4.3. 3.2 Materials. All materials, parts, and assemblies shall be in accordance with DL6610113 and this specification. 3.2.1 Primary components. Only primary components from a single pr
20、imary component lot shall be used in a production lot of loaded rocket catapults. 3.2.2 Propellant. The rocket motor propellant shall be in accordance with MIL-P-82680, Class m. 3.3 Age of explosive components. The following paragraphs give the requirements for controlling the age of explosive compo
21、nents. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-flIh-PL-A?876A 111 9999906 2005408 705 . 3.3.1 Propellant. The propellant is defined as the rocket motor grain (motor tube and grain assembly per Drawing 11744246) and the cartridge grain (cart
22、ridge case and grain assembly per Drawing 11740607). For purposes of this section, loaded is defined as when the rocket catapult lot is released for lot acceptance testing. 33.1.1 Rocket motor grain. The rocket motor grain shall be loaded within 180 days of the oldest rocket motor propellant mix. 33
23、.1.2 Cartridge grain. The cartridge grain shall be loaded (when the cartridge case is crimped) within 180 days of the oldest cartridge propellant mix. The crimped cartridge must be loaded into the rocket catapult within 240 days of oldest cartridge propellant mix. 3.3.2 Other explosive components. T
24、he other explosive components are the percussion primer (Drawing 11820864), the BKNO, pellets (MIL-P-46994, Type II-A), and the propellant shavings (MIL-P-82652). 33.2.1 Percussion primers. The percussion primers shall be loaded within 24 months of manufacture and certification or within 12 months o
25、f recertification. Loaded is defined as when the cartridge case is crimped. 33.2.2 BKNO, pellets and propellant shavings. The BKNO, pellets and propellant shavings shall be loaded into the rocket catapult within 12 months of the certification date. Loaded is defined as when the rocket catapult lot i
26、s released for lot acceptance testing. 3.4 Performance and product characteristics. The rocket catapults shall meet the following performance and product characteristics when test fired at -65“F, 70“F, and 165F using an ejected weight of 375 pounds. 3.4.1 Ballistics. The rocket catapults shall meet
27、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 occur during test firing of rocket catapults: a. No unit component, including but not limited to cartridge components, O-rings, springs, or piec
28、es of propellant shall be ejected. b. No component subject to loading shall fail. c. No excessive nozzle erosion, hot spots, or bumthrough shall occur. d. No leakage of ballistic gas past a sealing surface shall occur. 3.4.2 Initiation. Maximum allowed initiation pressure is 10,OOO psi. The rate of
29、pressurization input shall be 10,OOO to 50,000 psi/sec. 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE I. Ballistic Derformance requirements for a 375ound ejected weight. Component Motor Tube Launcher Tube Booster Tube -65OF 7O0F 165OF Min M
30、ax Min Max Min Max *OL Parameter Drawing Hydrostatic pressure (psi) 1 1726650 5,000 1 1726655 12,000 1 1726656 12,000 1 .o 30 - 30 1 .o 500 - 500 1 .o Resultant thrust, see 6.4.3 (lb,) - 5000 - 5000 - 5000 0.65 Thrust angle (reference)“ 52O 52 O 52 O - Resultant impulse, see 6.4.1 (Ib,/sec) 950 - 95
31、0 - 950 - Ignition delay, see 6.4.4 (ms) - 30 - Action time, see 6.4.2 md3 - 500 - 1/ DRI is defined in MIL-S-9479 (see 6.4.7). 2/ Nominal separation velocities are: 39.0 fs at -65OF and 47.0 ft/s at 165OF. 3/ Nominal rocket motor action time is: 460 ms at -65OF and 330 ms at 165OF. 4/ Record for in
32、formation only. 3.5 Hydrostatic pressure. The components listed in table II shall withstand the internai hydrostatic pressure specified for 15 seconds minimum when tested in accordance with 4.4.6.2. TABLE II. Hvdrostatic Dressure reciuirements. 3.6 Radiographic. Each loaded rocket catapult shall be
33、examined radiographically to ascertain the presence, condition, and correct placement of internai components. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NIL-DTL-8287bA 0b 2005410 363 . 3.7 Torque. The booster tube and breech assembly, when sea
34、ted with a torque of 35 f 2 inch-pounds, shall not be loosened or deformed when subjected to a breakaway torque of 17 foot-pounds. 3.8 Protective finish. Protective finish shall be in accordance with the applicable specifications and drawings and shall apply to all surfaces of the component regardle
35、ss of configuration. 3.9 Residual magnetism. The rocket catapult assembly, when passed in front of an MS17983 compass along the entire length of the catapult (see figure 1) shall not cause the compass indicator to deflect more than 5 degrees in either direction. Pilots Standby Compass BAS17983 6“ Mo
36、ve from this Position To this Position Plan view NOTE: Device and compass shall lie in a common horizontal plane FIGURE 1. Lavout for determination of residual mametism in device. 3.10 Environmental. The rocket catapult assemblies shall withstand the environmental conditioning of. 3.10.1 through 3.1
37、0.4. Rocket catapult assemblies subjected to this conditioning shall show no evidence of deterioration of propellant or disarrangement of components when examined in accordance with 4.4.6.1 and shall meet the ballistic performance requirements of 3.4 when test fired in accordance with 4.3.2. 3.10.1
38、High temperature. The rocket catapult shall withstand the high temperature test of 4.3.1.1. 3.10.2 Vibration. The rocket catapult shall withstand the vibration test of 4.3.1.2. 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-8287bA 0b 20054
39、Ll 2TT MIL-DTL-82 876A(OS) 3.10.3 Temperature shock. The rocket catapult shall withstand the temperature shock test of 4.3.1.3. 3.10.4 Thirty-day storage test. The rocket catapult shall withstand the 3Oday storage test of 4.3.1.4. 3.11 Identification markings. Each rocket catapult shall be marked in
40、 accordance with Drawing 66101 13 with an identification label, an instruction label, a warning label, and an installation label. 3.11.1 Production lot designation. The production lot number shall follow MIL-STD-1168. The construction of the lot number shall be as follows: XXX 93 D 002 407 abcde Whe
41、re: a = Manufacturers identification code. b = The year of manufacture of the oldest batch of propellant (cartridge or rocket motor) in the lot. c = The month of manufacture of the oldest batch of propellant (cartridge or rocket motor) in the lot expressed as an alpha code in accordance with 4.1.3 o
42、f MIL-STD- 1168. d = Lot interfuc number (controlled by Indian Head Division, Naval Surface Warfare Center, Code 5120, Indian Head, MD 20640-5000 or contracting activity). e = Lot sequence number - lot number (manufacturer is responsible for the assignment of lot numbers. 3.12 Workmanship. The workm
43、anship shall be that required by the applicable drawings, referenced specifications, and the best industrial practices governing the quality production of interchangeable parts for maintaining the dimensions, finishes, tolerances, and quality specified herein. Ail components and assemblies shall be
44、free from burrs, contamination, corrosion, sharp edges, or foreign material which could result in malfunction of the unit or components, or be a safety hazard in handling. 4. VERIFICATION 4.1 Classification of inspections. a. First article inspection (see 4.3) b. Conformance inspection (see 4.4) 4.2
45、 Inspection conditions. Unless otherwise specified in the contract or purchase order (see 6.2), inspection conditions shall be as follows: a. Temperature: Room ambient 65 to 95F b. Altitude: Normal ground c. Vibration: None d. Humidity: Room ambient to 95 percent relative, maximum 7 Provided by IHSN
46、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-B27bA 0b 200541i2 136 4.3 First article inspection. Unless otherwise specified in the contract or order (see 6.2), a first article sample shall consist of three blocks of rocket motor propellant, three blocks o
47、f catapult propellant, two motor tube and grain assemblies, two cartridge case and grain assemblies, and eighteen loaded rocket catapult assemblies. The rocket catapult assemblies shall be adapted for pressure transducers (see 6.8); and all first article samples shall be manufactured using the metho
48、d and procedures proposed for production. The first article samples shall be subjected to the tests of 4.4, with the exception of the test firing of 4.4.5, followed by environmental testing, radiographic examination, and static firing in the sequence specified in table III. Acceptance of the first a
49、rticle sample shall be based on no defects in the sample. Any production of the rocket catapult assemblies by the contractor prior to approval of the first article samples shall be at the contractors risk. First article samples shall not be included as part of the quantity specified for delivery in the contract (see 6.2). 43.1 Environmental tests. 4.3.1.1 High temperature. The rocket catapult assembly shall be subjected
