1、 INCH-POUND MIL-DTL-32129A (OS) 10 March 2009 SUPERSEDING MIL-DTL-3212926 November 2003 DETAIL SPECIFICATION CATAPULT, AIRCRAFT EJECTION SEAT, CKU-7A/A ASSEMBLY This specification is approved for use by the Naval Sea Systems Command. Department of the Navy, and is available for use by all Department
2、s and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers the requirements for the CKU-7A/A Rocket Catapult. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in sections 3, 4 or 5 of this specification. This section does not inc
3、lude 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 all specified requirements of documents cited in sections
4、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 otherwise specified, the issues of the
5、se documents are those cited in the solicitation or contract. DEPARTMENT OF DEFENSE SPECIFICATIONS MIL-P-46994 Pellet, 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 Comments, suggestions, or questions on
6、 this document should be addressed to DEPARTMENT OF THE NAVY, Indian Head Division, NSWC, Code E11G3, Document Control, 4072 North Jackson Road, Suite106, Indian Head, MD 20640-5115 OFFICIAL BUSINESS, or emailed to amanda.pennnavy.mil. Since contact information can change, you may want to verify the
7、 currency of this information using the ASSIST Online database at http:/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 networking permitted without license from IHS-,-,-MIL-DTL-3
8、2129A (OS) 2DEPARTMENT OF DEFENSE STANDARDS MIL-STD-413 Visual Inspection Guide for Elastomeric O-rings MIL-STD-810 Environmental Test Methods and Engineering Guidelines MIL-STD-1168 Ammunition Lot Numbering and Ammunition Data Card MIL-STD-1907 Inspection, Liquid Penetrant and Magnetic Particle, So
9、undness 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 http:/assist.daps.dla.mil/quicksearch/ or from the Standardization
10、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 document to the extent specified herein. Unless otherwise specifi
11、ed, the issues are those cited in the solicitation or contract. DRAWINGS Naval Surface Warfare Center, Indian Head Division (CAGE Code 14083) DL512-174-0110 Catapult, Aircraft Ejection Seat, CKU-7A/A Assembly (Application for copies should be addressed to: DEPARTMENT OF THE NAVY, Indian Head Divisio
12、n, NSWC, Code E11G7, Document Control, 4072 North Jackson Road, Suite 106, Indian Head, MD 20640-5115 OFFICIAL BUSINESS.) 2.3 Non-Government publications. The following documents form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents ar
13、e those cited in the solicitation or contract. AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM) E 1444 Standard Practice for Magnetic Particle Examination E 1742 Standard Practice for Radiographic Examination (Copies of this document are available online at http:/www.astm.org/ or from the American
14、Society for Testing and Materials Customer Service, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959.) AMERICAN NATIONAL STANDARD INSTITUTE/AMERICAN SOCIETY FOR QUALITY ANSI/ASQC Z1.9 Sampling Procedures for Inspection by Variables ANSI/ASQC Zl.4 Sampling Procedures and Tables for Inspection
15、by Attributes Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-32129A (OS) 3(Copies of this document are available online at http:/webstore.ansi.org/ansidocstore/default.asp, or from the American Society for Quality, PO Box 3005, 611 E. Wiscon
16、sin Ave., Milwaukee, WI 53201-4606.) SOCIETY OF AUTOMOTIVE ENGINEERS SAE AS17983 Compass, Magnetic, Pilots Standby (Copies of this document are available online at http:/www.sae.org/, or from the Society of Automotive Engineers, 400 Commonwealth Drive, Warrendale, Pennsylvania, United States, 15096-
17、001.) 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 precedence. Nothing in this document, however, supersedes applicable laws and regulations unl
18、ess 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. 3.2 Materials. All materials, parts, and assemblies shall be in accordance with DL512-174-0110 and this s
19、pecification. 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 or CCU-149/A impulse cartridges. 3.2.1.1 CCU-149/A Impulse Cartridge. The primary components for the CCU-149/A cartridge are the percussion
20、 primer (Drawing 11820864), the BKNO3pellets (MIL-P-46994, type II-A), and the cartridge grain lot. 3.2.1.2 CKU-7A/A Rocket Catapult. The primary component for the CKU-7A/A catapult is the rocket motor grain lot. More that one lot of CCU-149/A cartridges may be used in a CKU-7A/A Rocket Catapult lot
21、, provided each lot of cartridges complies with 3.2.1.1. 3.2.2 Propellant. The rocket motor propellant shall be in accordance with MIL-DTL-32124, Type V. The catapult propellant shall be in accordance with MIL-DTL-32124, Type II. 3.2.3 Material Definitions. 3.2.3.1 Propellant batch. A propellant bat
22、ch 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 Propellant grain batch. A propellant grain batch is a group of grains (rocket motor or cartridge) cast from one propellant batch. 3.2.3.3
23、Propellant grain lot. A propellant grain lot is a group of grains (rocket motor or cartridge) composed of one or more propellant grain batches all having the same ingredient lots. 3.2.3.4 CCU-149/A Impulse Cartridge lot. A cartridge lot is a group of units composed of one lot of percussion primers,
24、BKNO3pellets and cartridge propellant grains that is assembled at one time. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-32129A (OS) 43.2.3.5 Rocket catapult lot. A rocket catapult lot is a group of units composed of one lot of rocket moto
25、r grains that is assembled at one time. 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 defined as the rocket motor grain (sleeve and grain assembly per Drawing 512-174-0128) and the
26、cartridge grain (cartridge grain assembly per Drawing 512-174-0108). 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 grain. The rocket motor grain shall be loaded within 360 days of the oldest rocket motor p
27、ropellant mix. 3.3.1.2 Cartridge grain. The cartridge grain shall be loaded (when the cartridge case is crimped) within 90 days of the cartridge propellant mix. The crimped cartridge shall be loaded into the rocket catapult within 240 days of the oldest cartridge propellant mix. 3.3.2 Other explosiv
28、e components. The other explosive components are the percussion primer (Drawing 11820864) and the BKNO3pellets (MIL-P-46994, Type II-A). 3.3.2.1 Percussion primers. The percussion primers shall be loaded within 24 months of manufacture and certification or within 12 months of recertification. Loaded
29、 is defined as when the cartridge case is crimped. 3.3.2.2 BKNO3pellets. The BKNO3pellets shall be loaded into the cartridge head assembly within 12 months of the certification date. Loaded is defined as when the cartridge case is crimped. 3.4 Performance and product characteristics. The rocket cata
30、pults shall meet the following performance and product characteristics when test fired at -65, 70, and 165F using an ejected weight of 459 pounds. The rocket angle shall be set at 40 degrees (see Drawing 11820363). 3.4.1 Ballistics. The rocket catapults shall meet the ballistic requirements specifie
31、d in table I. 3.4.1.1 Ballistic Definitions (see figure 1) . 3.4.1.1.1 Mechanical failure. A mechanical failure is defined as any deformation or breakage of a part, the occurrence of which is other than a design function 3.4.1.1.2 Catapult ignition delay time. Catapult ignition delay time (CId) is t
32、he elapsed time from the first indication of shearing of the firing pin shear pins (t0) to the beginning of the continuous rise (t1) on the catapult thrust-time record (see figure 1). Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-32129A (OS
33、) 5FIGURE 1. Thrust/time Curves 3.4.1.1.3 Catapult launch time. Catapult launch time (CLt) is defined as the time between the beginning of the continuous rise (t1) on the thrust-time curve and separation (t2). 3.4.1.1.4 Catapult separation velocity. Catapult separation velocity (CSv) is defined as t
34、he average velocity of the simulated ejected weight propelled horizontally at catapult separation measured over the interval from separation to 12 inches after separation. 3.4.1.1.5 Rate of change of acceleration. Rate of change of acceleration (A) is defined as the maximum change in acceleration oc
35、curring in any 30-millisecond interval on the continuously rising portion of the acceleration time record (see figure 1). Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-32129A (OS) 63.4.1.1.6 Rocket motor ignition delay. Rocket motor ignitio
36、n time (RId) is the elapsed time from separation (the point on the catapult thrust trace where the trace begins to drop sharply) to 10 percent of maximum thrust, as measured on the rising portion of the normal component rocket thrust trace (see figure 1). 3.4.1.1.7 Rocket motor action time. Action t
37、ime (RAt) 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 the curve to the corresponding 10 percent of thrust on the declining portion of the curve (see figure 1). 3.4.1.1.8 Rocket motor resultant thrus
38、t. The rocket motor resultant thrust (RFmax) is obtained by vectorially adding the two maximum components of rocket thrust that occur at one time. 3.4.1.1.9 Rocket motor resultant impulse. The rocket motor resultant impulse (RIr) is obtained by integrating the resultant thrust (RFmax) of the rocket
39、motor over the action time. 3.4.1.1.10 Catapult dynamic response index (DRI). The DRI is representative of the maximum dynamic compression of the vertebral column of the human body. In physical terms, the DRI is calculated by mathematically describing the human body in terms of an analogous, lumped
40、parameter mechanical model consisting of a mass, spring, and damper. The DRI is determined from the equations (1) and (2). d 2 + 2n d + n2 = d 2 z (1) dt2 dt dt 2 DRI = n2 max (2) gwhere: = compression of spring = 0.224 (damping ration of the model) n= 52.9 radians/sec(undamped natural frequency of
41、the model) Substituting given numerical values, these equations become: d 2 + 23.7 d + 2798 = d 2z dt2 dt dt2 DRI = 86.9 max 3.4.1.1.11 Catapult axial thrust. Catapult axial thrust (CFmax) is the maximum thrust from the thrust-time curve that occurs during the catapult launch time. 3.4.2 Other requi
42、rements. 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 catapult components, O-rings, springs, or pieces of propellant shall be ejected. b. No component subject to loading
43、 shall fail. c. No excessive nozzle erosion, hot spots, or burn through shall occur. d. No leakage of ballistic gas past a sealing surface shall occur. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-32129A (OS) 7e. The thrust-time curve shal
44、l exhibit a shape that compares well with the established (or representative) curve for the unit. 3.4.3 Initiation. Initiation input for test is 1100 psi pressure source producing a 30,000 to 50,000 psi per second positive rate of change. 3.5 Torque. The booster tube (Drawing 512-174-0120) and head
45、(Drawing 10551412) assembly and the launcher tube (Drawing 512-174-0121) and mount (Drawing 512-174-0122) assembly, when seated with a torque of 400 +50, -0 inch-pounds, shall not be loosened or deformed when subjected to a breakaway torque of 200 inch-pounds. TABLE I. Ballistic performance requirem
46、ents for a 459-pound ejected weight. -65 5 F 70 5 F 165 5 F Parameter Min Max Min Max Min Max Catapult Initiation Pressure, Pnet(psi) 250 550 250 550 250 550 Rate of change of acceleration, A (g/sec), see 3.4.1.1.5, (reference) 3/- 300 - 300 - 300 Separation velocity1/, CSv (ft/s), see 3.4.1.1.4 37
47、- 40 - 42 - Ignition delay, Cld (ms), see 3.4.1.1.2 - 30 - 30 - 30 Axial thrust, Cfmax (lbf), see 3.4.1.1.11 - 7000 - 7000 - 7300 Launch time, CLt (ms), 3.4.1.1.3 - 210 - 200 - 200 Dynamic response index, DRI, see 3.4.1.1.10 - 18 - 18 - 22 Acceleration, A (g), (reference) 3/- 20 - 18 - 20 Rocket Mot
48、or Resultant Impulse, RIr (lbf/sec), see 3.4.1.1.9 1100 - 1100 - 1100 - Ignition delay, Rld (ms), see 3.4.1.1.6 - 25 - 25 - 25 Action time, RAt (ms)2/, see 3.4.1.1.7 - 550 - 450 - 450 Resultant thrust, RFmax (lbf), see 3.4.1.1.8 - 7350 - 7350 - 7600 Thrust angle (Degrees) (reference)3/40 40 40 1/ Nominal separation velocities are: 39.5 ft/s at -65 F and 45.5 ft/s at 165 F. 2/ Nominal rocket motor action time is: 420 ms at -65 F and 310 ms at 165 F. 3/ Record for information only. 3.6 Residual magnetism. The rocket catapult assembly, when passed in front of an SAE AS17983 co
