1、INCH POUND MIL-DTL-32127A (OS) 03 August 2005 SUPERCEDING MIL-DTL-32127 9 February 2005 DETAIL SPECIFICATION CATAPULT, AIRCRAFT EJECTION SEAT, CKU-5C/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 Rocket Catapult CKU-5C/A loaded assembly. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in sections 3, 4 or 5 of this specification. This sect
3、ion 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 all specified requirements of documents sp
4、ecified 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 otherwise specifie
5、d, the issues of these 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, and NSWC/IH-BC-20 Comments, suggestions, or questions on this docu
6、ment should be addressed to Commander, Indian Head Division, Naval Surface Warfare Center, Technical Information Branch (Code 4230), 101 Strauss Avenue, Indian Head, Maryland 20640-5035, or emailed to amanda.pennnavy.mil. Since contact information can change, you may want to verify the currency of t
7、his address 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-32127A
8、(OS) 2 DEPARTMENT 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, Soundne
9、ss Requirements for Materials, Parts, and Weldments MIL-STD-2102 Aircrew Escape Propulsion Systems; Vibration and Shock Tests for DOD-STD-2101 Classification of Characteristics (Copies of these documents are available online at http:/assist.daps.dla.mil/ or from the Standardization Documents Order D
10、esk, Building 4D, 700 Robbins Avenue, 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 specified, the issues o
11、f these documents are those cited in the solicitation. DRAWINGS Naval Surface Warfare Center, Indian Head Division (CAGE Code 14083) DL512-174-0068 Catapult, Aircraft Ejection Seat, CKU-5C/A Assembly (Application for copies should be addressed to: Commander, Indian Head Division, Naval Surface Warfa
12、re Center. Attn: Technical Information Branch (Code 4230). Indian Head. MD 20640-5035.) 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 are those cited in the solicitation
13、or contract. AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM) E 1742 Standard Practice for Radiographic Examination B 165 Liquid Penetrant Inspection Method E 1444 Standard Practice for Magnetic Particle Examination (Copies of this document are available online at http:/www.astm.org or from the Ame
14、rican Society for Testing and Materials Customer Service, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959.) AMERICAN SOCIETY FOR QUALITY ANSI/ASQ Zl.4 Sampling Procedures and Tables for Inspection by Attributes Provided by IHSNot for ResaleNo reproduction or networking permitted without lice
15、nse from IHS-,-,-MIL-DTL-32127A (OS) 3 ANSI/ASQ Z1.9 Sampling Procedures for Inspection by Variables (Application for copies should be addressed to the American Society for Quality, PO Box 3005, 611 E. Wisconsin Ave., Milwaukee, WI 53201-4606.) SOCIETY OF AUTOMOTIVE ENGINEERS SAE AS17983 Compass, Ma
16、gnetic, 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, 15096-001.) 2.4 Order of precedence. In the event of a conflict between the text of this document a
17、nd 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 article. When specified (see 6.2), a sample shall be subjected to first a
18、rticle inspection (see 6.5) in accordance with 4.3. 3.2 Materials. All materials, parts, and assemblies shall be in accordance with DL512-174-0068 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
19、 rocket catapults or CCU-22B/A impulse cartridges. 3.2.1.1 CCU-22B/A Impulse Cartridge. The primary components for the CCU-22B/A cartridge are the percussion primer (Drawing 11820864), the BKNO3 pellets (MIL-P-46994, type II-A), the propellant ribbon (MIL-DTL-32124, Type II) and the cartridge grain
20、lot. 3.2.1.2 CKU-5C/A Rocket Catapult. The primary components for the CKU-5C/A catapult are the rocket motor grain lot and the rocket motor igniter (BKNO3 pellets per MIL-P-46994, type II-A and propellant chips per MIL-DTL-32124, Type IV). More than one lot of CCU-22B/A cartridges may be used in a C
21、KU-5C/A Rocket Catapult lot, 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 IV. The catapult propellant shall be in accordance with MIL-DTL-32124, Type II. 3.2.3 Material Definitions. 3.2.3.1 Propel
22、lant batch. A propellant 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 Propellant grain batch. A propellant grain batch is a group of grains (rocket motor or cartridge) cast from on
23、e propellant batch. 3.2.3.3 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. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IH
24、S-,-,-MIL-DTL-32127A (OS) 4 3.2.3.4 CCU-22B/A Impulse Cartridge lot. A cartridge lot is a group of units composed of one lot of each of the following; percussion primers, BKNO3 pellets, propellant ribbon and cartridge propellant grains, that are assembled at one time. 3.2.3.5 Rocket catapult lot. A
25、rocket catapult lot is a group of units composed of one lot of each of the following; rocket motor grains, BKNO3 pellets, and propellant chips, that are assembled at one time. 3.3 Age and moisture control of explosive components. The following paragraphs give the requirements for controlling the age
26、 and moisture of explosive components. 3.3.1 Propellant grains. The propellant grains are defined as the rocket motor grain (motor tube and grain assembly per Drawing 512-174-0071) and the cartridge grain (cartridge propellant grain per Drawing 512-174-0108-2). For purposes of this section, loaded i
27、s defined as when the rocket catapult lot is released for lot acceptance test. 3.3.1.1 Rocket motor grain. The rocket motor grain shall be loaded within 180 days of the oldest rocket motor propellant mix. 3.3.1.2 Cartridge grain. The cartridge grain shall be loaded (when the cartridge case is crimpe
28、d) within 60 days of the oldest cartridge propellant mix. The crimped cartridge must be loaded into the rocket catapult within 180 days of oldest cartridge propellant mix. 3.3.2 Other explosive components. The other explosive components are the percussion primer (Drawing 11820864), the BKNO3 pellets
29、 (MIL-P-46994, Type II-A), and the propellant ribbon and chips (MIL-DTL-32124, Types II and IV). 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 is defined as when the cartridge case i
30、s crimped. 3.3.2.2 BKNO3 pellets, propellant ribbons and chips. The BKNO3 pellets and propellant chips for the rocket motor igniter shall be loaded into the rocket catapult within 12 months of the certification date. Loaded is defined as when the rocket catapult lot is released for lot acceptance te
31、sting. The BKNO3 pellets and propellant ribbon for the CCU-22B/A cartridge shall be loaded into the hous ing assembly and sleeve assembly within 12 months of the certification date. Loaded is defined as when the cartridge case is crimped. 3.3.3 Moisture control of explosive components. As a general
32、practice, the propellant grains and other explosive components shall be dried as a part of or immediately after the completion of manufacture, and then stored dry until ready for final loading. As a final precaution, the explosive components shall be dried (conditioned) again immediately before they
33、 are loaded. Specific drying requirements for each explosive component are provided in the subassembly and assembly drawings of DL512-174-0068. 3.4 Performance and product characteristics. The rocket catapults shall meet the following performance and product characteristics when test fired at -65 F,
34、 77 F and 165 F using an ejected weight of 375 pounds. 3.4.1 Ballistics. The rocket catapults shall meet the ballistic requirements specified in table I. 3.4.1.1 Ballistic Definitions. See figure 1 for a graphical representation of some of the definitions given below. Provided by IHSNot for ResaleNo
35、 reproduction or networking permitted without license from IHS-,-,-MIL-DTL-32127A (OS) 5 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 i
36、gnition delay time is the elapsed time from the first indication of shearing of the firing pin shear pins to first indication of catapult thrust. 3.4.1.1.3 Catapult separation velocity. Catapult separation velocity is defined as the average velocity of the simulated ejected weight propelled horizont
37、ally at catapult separation measured over the interval from separation to 12 inches after separation. 3.4.1.1.4 Catapult axial thrust. Catapult axial thrust is the maximum thrust from the thrust-time curve that occurs during the catapult phase. 3.4.1.1.5 Catapult dynamic response index (DRI). The DR
38、I 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 parameter mechanical model consisting of a mass, spring, and damper. The DRI is dete
39、rmined from the equations (1) and (2). d 2d + 2zwn dd + wn2 d = d 2 z (1) dt 2 dt dt 2 DRI = wn2 d max (2) g where: = compression of spring = 0.224 (damping ration of the model) n= 52.9 radians/sec (undamped natural frequency of the model) d 2 z = catapult acceleration dt 2 Substituting given numeri
40、cal values, these equations become: d 2 d + 23.7 dd + 2798d = d 2 z dt 2 dt dt2 DRI = 86.9 d max 3.4.1.1.6 Rocket motor ignition delay. Rocket motor ignition time is the elapsed time from separation (the point where the booster tube exits the nozzle) to 10 percent of maximum thrust as measured on th
41、e rising portion of the normal component rocket thrust trace. 3.4.1.1.7 Rocket motor action time. Action time is determined from the normal thrust-time curve, and shall be defined as the time interval from the 10 percent of maximum thrust on the initial rise of the curve to the corresponding 10 perc
42、ent of thrust on the declining portion of the curve. 3.4.1.1.8 Rocket motor resultant thrust. The rocket motor resultant thrust is obtained by vectorially adding the axial and normal components of rocket thrust. 3.4.1.1.9 Rocket motor resultant impulse. The rocket motor resultant impulse is obtained
43、 by integrating the resultant thrust of the rocket motor over the action time. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-32127A (OS) 6 t1 - t0 = Catapult Ignition Delay Time =241ttfoot Catapult Separation Velocity FAmax = Catapult Axial
44、 Thrust - maximum Fnmax = Rocket Motor Normal (vertical) Thrust - maximum t3 - t2 = Rocket Motor Ignition Delay t5 - t3 = Rocket Motor Action Time Figure 1. Performance Curves. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-32127A (OS) 7 3.4
45、.2 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 pieces of propellant shall be ejected. b. No component su
46、bject to loading 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. e. The thrust-time curve shall exhibit a shape that compares well with the established (or representative) curve for the unit. 3.4.3
47、 Initiation. Maximum allowed initiation pressure is 10,000 psi. The rate of pressurization input shall be 10,000 to 50,000 psi/sec. TABLE I. Ballistic performance requirements for a 375 pound ejected weight. -65 5 F 77 5 F 165 5 F Parameter Min Max Min Max Min Max AQL Catapult Initiation Pressure (p
48、si) 400 600 400 600 400 600 - Ignition delay (ms) - 10 - 10 - 10 .65 Dynamic response index (DRI) - 18 - 18 - 22 .65 Separation velocity1/ (ft/s) 35 - 35 - 35 - .65 Axial thrust (lb f) - 7000 - 7000 - 7000 1.0 Pressure (psi) 1200 - 1200 - 1200 - 1.0 Rocket Motor Resultant Impulse (lbf/sec) 950 - 950 - 950 - 1.0 Ignition delay (ms) - 15 - 15 - 15 1.0 Action time (ms)2/ - 500 - 500 - 500 1.0 Resultant thrust (lbf) - 5000 - 5000 - 5000 .65 Thrust angle (Degrees) (reference)3/ 52 52 52 1/ Nominal separation velocities are: 38.0 ft/s at -65 F and 45.0 ft/s at 165
