NAVY MIL-DTL-82945 B-2010 CATAPULT AIRCRAFT EJECTION SEAT CKU-10 A AND CKU-11 A ASSEMBLIES《CKU-10 A及CKU-11 A组件飞机弹射座椅弹射器》.pdf

1、INCH-POUND MIL-DTL-82945B (OS) 6 July 2010 SUPERSEDING MIL-DTL-82945A (OS) 21 January 1997 DETAIL SPECIFICATION CATAPULT, AIRCRAFT EJECTION SEAT, CKU-10/A AND CKU-11/A ASSEMBLIES This specification is approved for use by the Naval Sea Systems Command, Department of the Navy, and is available for use

2、 by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers the requirements for the CKU-10/A and CKU-11/A Rocket Catapults (see 6.1). 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are cited in Sections 3, 4, or 5 of this s

3、pecification. 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, users are cautioned that they must meet all specified requirements o

4、f documents cited in sections 3, 4, or 5 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 otherwi

5、se specified, the issues of these documents are those cited in the solicitation or contract. DEPARTMENT OF DEFENSE SPECIFICATIONS MIL-P-46994 Pellets/Granules Boron/Potassium Nitrate MIL-DTL-32124 Propellant, NSWC/IH-BC-15, NSWC/IH-BC-16, NSWC/IH-BC-17, NSWC/IH-BC-20, NSWC/IH-BC-21 and NSWC/IH-BC-22

6、 Comments, suggestions, or questions on this document should be addressed to Department of the Navy, Indian Head Division, NSWC, Code E12P, Document Control, 4123 Artisans Court, Suite 103, Indian Head, Maryland 20640-5085, OFFICIAL BUSINESS, or emailed to amanda.pennnavy.mil. Since contact informat

7、ion can change, you may want to verify the currency of this address information using the ASSIST Online database at https:/assist.daps.dla.mil/. AMSC N/A FSC 1377 DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited. Provided by IHSNot for ResaleNo reproduction or network

8、ing permitted without license from IHS-,-,-MIL-DTL-82945B (OS) 2 DEPARTMENT OF DEFENSE STANDARDS MIL-STD-413 Visual Inspection Guide for Elastomeric O-rings MIL-STD-810 Environmental Engineering Considerations and Laboratory Tests MIL-STD-1168 Ammunition Lot Numbering and Ammunition Data Card MIL-ST

9、D-1907 Inspection, Liquid Penetrant and Magnetic Particle, Soundness Requirements for Materials, Parts, and Weldments DOD-STD-2101 Classification of Characteristics MIL-STD-2102 Aircrew Escape Propulsion Systems; Vibration and Shock Tests for (Copies of these documents are available online at https:

10、/assist.daps.dla.mil/quicksearch/ or from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 19111-5094.) 2.2.2 Other Government documents, drawings, and publications. The following other Government documents, drawings, and publications form a part of this doc

11、ument to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation or contract. DRAWINGS Naval Surface Warfare Center, Indian Head Division (CAGE Code 14083) DL 513-174-0100 Catapult, Aircraft Ejection Seat, CKU-10/A Assembly DL 513-174-0200 Catapult, Ai

12、rcraft Ejection Seat, CKU-11/A Assembly (Application for copies should be addressed to the DEPARTMENT OF THE NAVY, Indian Head Division, NSWC, Code E11G7, Document Control, 4072 North Jackson Road Suite 106, Indian Head, MD 20640-5115 OFFICIAL BUSINESS.) 2.3 Non-Government publications. The followin

13、g documents form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract. AMERICAN SOCIETY FOR QUALITY ANSI/ASQ Z1.4 Sampling Procedures and Tables for Inspection by Attributes ANSI/ASQ Z1.9 Sam

14、pling Procedures and Tables for Inspection by Variables for Percent Nonconforming Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-82945B (OS) 3 (Copies of this document are available online at http:/webstore.ansi.org/ansidocstore/default.asp,

15、 or from the American Society for Quality, PO Box 3005, 611 E. Wisconsin Ave., Milwaukee, WI 53201-4606.) AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM) ASTM E 1417 Standard Practice for Liquid Penetrant Testing ASTM E 1742 Standard Practice for Radiographic Examination. (Copies of these document

16、s are available online at http:/www.astm.org or from the American Society for Testing and Materials Customer Service, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959.) SAE INTERNATIONAL SAE AS 17983 Compass, Magnetic, Pilots Standby (Copies of these documents are available on line at http:/w

17、ww.sae.org or from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001.) 2.4 Order of precedence. Unless otherwise noted herein or in the contract, in the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedenc

18、e. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. REQUIREMENTS 3.1 First article. When specified (see 6.2), a sample shall be subjected to first article inspection (see 6.3) in accordance with 4.3. 3.1.1 Pressure transd

19、ucers. All first article sample catapult assemblies shall be adapted for pressure transducers as specified in the contract or order (see 6.2 and 6.4). 3.1.2 Propellant aging. Propellant samples shall be prepared and tested in accordance with the requirements of 4.3.3. 3.2 Materials. All materials, p

20、arts, and assemblies shall be in accordance with the applicable DL and this specification. 3.2.1 Primary components. Only primary components from a single primary component lot shall be used in a production lot of loaded rocket catapults. 3.2.2 Propellant. The rocket motor propellant shall be in acc

21、ordance with MIL-DTL-32124, Type V and the catapult propellant shall be in accordance with MIL-DTL-32124, Type VI. 3.2.3 Material Definitions. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-82945B (OS) 4 3.2.3.1 Propellant batch. A propellan

22、t batch is a mix of ingredients, each ingredient composed of one homogeneous lot that is mixed at one time in one vessel, resulting in a homogeneous mixture. 3.2.3.2 Rocket motor grain assembly batch. A rocket motor grain assembly batch is a group of rocket motor grain assemblies cast from one prope

23、llant batch. 3.2.3.3 Rocket motor grain assembly lot. A rocket motor grain assembly lot is a group of rocket motor grain assemblies composed of one or more rocket motor grain assembly batches all having the same ingredient lots. 3.2.3.4 Catapult grain assembly batch. A catapult grain assembly batch

24、is a group of catapult grain assemblies cast from one propellant batch. 3.2.3.5 Catapult grain assembly lot. A catapult grain assembly lot is a group of catapult grain assemblies composed of one or more catapult grain assembly batches all having the same ingredients lots. 3.2.3.6 Rocket catapult lot

25、. A rocket catapult lot is a group of units composed of one lot of rocket motor grain assemblies, one lot of catapult grain assemblies, one lot of external igniter assemblies, and one lot of rocket motor igniters that are assembled at one time. 3.2.3.7 External igniter assembly lot. An external igni

26、ter assembly lot is a group of external igniter assemblies that are composed of one lot of percussion primers, one lot of BKNO3pellets, and one lot of BKNO3granules that are assembled at one time. 3.2.3.8 Rocket motor igniter lot. A rocket motor igniter lot is a group of external igniter assemblies

27、that are composed of one lot of BKNO3pellets and one lot of BKNO3granules that are assembled at one time. 3.2.3.9 Primary components. Primary components are all components containing explosive ingredients. These include the percussion primers, the external igniter assembly, the catapult grain assemb

28、ly, the rocket motor grain assembly, and the rocket motor igniter assembly. 3.2.3.10 Major metal parts. The major metal parts are the motor tube (Drawing 513-174-0101), the nozzle (Drawing 513-174-0102 or Drawing 513-174-0201), the motor tube head (Drawing 513-174-0110), the double tang lock (Drawin

29、g 513-174-0219), the breech (Drawing 513-174-0133), the launcher tube (Drawing 513-174-0146), and the trunnion (Drawing 513-174-0147). 3.3 Age of explosive components. The following paragraphs give the requirements for controlling the age of explosive components. 3.3.1 Propellant. The propellant is

30、defined as the rocket motor grain (rocket grain assembly per Drawing 513-174-0217) and the catapult grain (catapult grain assembly per Drawing 513-174-0218). For purposes of this section, loaded is defined as when the rocket catapult lot is released for lot acceptance testing. 3.3.1.1 Rocket motor g

31、rain. The rocket motor grain shall be loaded within 180 days of the oldest rocket motor propellant mix. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-82945B (OS) 5 3.3.1.2 Catapult grain. The catapult grain shall be loaded within 180 days o

32、f the oldest catapult propellant mix. 3.3.2 Other explosive components. The other explosive components are the percussion primer (Drawing 8799925), the BKNO3pellets (MIL-P-46994, Type II-A), and the BKNO3granules (MIL-P-46944, Type VII, 40/140 granulation). 3.3.2.1 Percussion primers. The percussion

33、 primers shall be loaded within 24 months of manufacture and certification or within 12 months of recertification. Loaded is defined as when the external igniter assembly (Drawing 513-174-0123) is complete. 3.3.2.2 BKNO3pellets and granules. The BKNO3pellets and granules shall be loaded into the roc

34、ket motor igniter (Drawing 513-174-0107) within 12 months of the certification date. Loaded is defined as when the rocket motor igniter is complete. The BKNO3pellets and granules shall be loaded into the cartridge case assembly (Drawing 513-174-0119) within 12 months of the certification date. Loade

35、d is defined as when the cartridge case assembly is crimped. 3.3.2.3 External igniter assembly and rocket motor igniter assembly. The external igniter assembly (Drawing 513-174-0123) and the rocket motor igniter (Drawing 513-174-0107) shall be loaded into the rocket catapult within 6 months of their

36、 completion. Loaded is defined as when the rocket catapult lot is 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 -65F, 70F, and 165F using an ejected weight of

37、347 1 pounds. 3.4.1 Ballistics. The rocket catapults shall meet the ballistic performance parameters specified in table I. 3.4.1.1 Ballistic Definitions. See figure 1 for a graphical representation of some of the definitions given below. 3.4.1.1.1 Rocket motor resultant impulse. The rocket motor res

38、ultant impulse is obtained by integrating the resultant thrust of the rocket motor over the action time. 3.4.1.1.2 Rocket motor action time. Action time is determined from the normal thrust-time curve, and is defined as the time interval from the 10 percent of maximum thrust on the initial rise of c

39、urve to the corresponding 10 percent of thrust on the declining portion of the curve. 3.4.1.1.3 Rocket motor resultant thrust. The rocket motor resultant thrust is obtained by vectorially adding the two maximum components of rocket thrust that occur at one time. 3.4.1.1.4 Rocket motor ignition delay

40、. Rocket motor ignition time is the elapsed time from separation to 10 percent of maximum thrust, as measured on the rising portion of the normal thrust-time curve. 3.4.1.1.5 Catapult ignition delay time. Catapult ignition delay time is the elapsed time from the first indication of shearing of the f

41、iring pins until the first indication of catapult thrust. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-82945B (OS) 6 3.4.1.1.6 Catapult separation velocity. Catapult separation velocity is defined as the average velocity of the simulated e

42、jected weight propelled horizontally at catapult separation measured over the interval from separation to 12 inches after separation. 3.4.1.1.7 Catapult dynamic response index (DRI). The DRI is representative of the maximum dynamic compression of the vertebral column of the human body. In physical t

43、erms, the DRI is calculated by mathematically describing the human body in terms of an analogous, lumped parameter mechanical model consisting of a mass, spring, and damper. The DRI is determined from the equations (1) and (2). 22222dtzddtddtdnn (1) gDRIn max2 (2) Where: = compression of spring = 0.

44、224 (damping ration of the model) n = 52.9 radians/sec (undamped natural frequency of the model) 22dtzdcatapult acceleration Substituting given numerical values, these equations become: 222227987.23dtzddtddtd max9.86 DRI 3.4.1.1.8 Catapult launch time. Catapult launch time is the time between the fi

45、rst indication of thrust on the thrust-time curve until separation. 3.4.1.1.9 Catapult axial thrust. The maximum thrust from the thrust-time curve that occurs during the catapult launch time. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-82

46、945B (OS) 7 01tt Catapult Ignition Delay Time 241ttfootCatapult Separation Velocity maxAF Catapult Axial Thrust-maximum maxnF Rocket Motor Normal (vertical) Thrust-maximum 23tt Rocket Motor Ignition Delay 35tt Rocket Motor Action Time FIGURE 1. Performance Curves Provided by IHSNot for ResaleNo repr

47、oduction or networking permitted without license from IHS-,-,-MIL-DTL-82945B (OS) 8 TABLE I. Ballistic performance requirements for a 347-pound ejected weight. -65F 70F 165F Parameter Min Max Min Max Min Max AQL Catapult Initiation pressure, (psi) 350 550 350 550 350 550 Dynamic response index, (DRI

48、)1/ 18.0 18.0 22.0 0.65 Separation velocity, (ft/s)2/33 33 33 0.65 Ignition delay, (ms) 10 10 10 0.65 Axial thrust (lbf) 7000 7000 7000 1.0 Launch time (ms) 260 260 260 1.0 Rocket Motor Resultant impulse, (lbf/sec) 960 960 960 1.0 Ignition delay, (ms) 30 30 30 1.0 Action time, (ms)3/ 535 535 535 1.0 Resultant thrust, (lbf) 5000 5000 5000 0.65 Thrust angle (reference)* CKU-10/A CKU-11/A 47.5 54.5 47.5 54.5 47.5 54.5 1/ DRI is defined in section 3.4.1.1.7. 2/ Nominal separation velocities are: 37.0 ft/s at -65F and 46.0 ft/s at 165F. 3/ Nominal rocket motor action time is