AIR FORCE MIL-T-5208 B-1967 TANK REMOVABLE LIQUID PROPELLANT ROCKET ENGINE GENERAL SPECIFICATION FOR《火箭发动机液体推进器的可拆卸邮箱的一般规定》.pdf

1、MIL-T-52088 28 W 7777906 0184532 3 W - i* L-T- 5 20 8B 30 Jun i967 Superseding -5208 (ASG) 5 July 1955 MI LI TARY SPEC1 FI CATION TANKS, REMOVABLE, LIQUID PROPELLANT ROCKET ENGINE, GENERAL SPECIFICATION FOR This Specification is mandatory for use by all Departments and Agencies of the Department of

2、Defense 1. SCOPE 1.1 Scope. This specification cavers the general requirements for removable tanks for liquid propellant rocket engine systems. 1.2 Classification. Rocket engine tanks shall be of the following types and classes, as specified (6.3) : Type I - For liquids Type II -For gases Class 1 -

3、For aircraft Class 2 - For vehicle-launched missiles Class 3 - For remotely launched missiles 2. APPLICABLE DOCUMENTS 2.1 The following specifications, standards, drawings, and publi- cations, of the issue in effect on date of invitation for bids or request for proposal, form a part of this specific

4、ation to the extent specified herein: SPECIFICATIONS Federal NN-P- 515 PPP-C-843 PPP=B-601 TT-s-735 Mi lit ary MIL-P- MILD-1000 MIL-C-5501 Plywood, Container Grade Cushioning Materials, Celluosic Boxes, Wood, Cleated-Plywood Standard Test Fluids, Hydrocarbon Preservation, Methods of Drawings, Engine

5、ering and Associated Lists Caps and Plugs, Protective, Dust and Moisture Seal Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-520B 28 M 77777Db 0384533 5 = I MI L-T- 5208B MIL-S-7742 Screw Threads, Standard Optimum Selected Series, General Spec

6、ifi- cation For Root With Increased Minor Diameter: General Specification For MIL-c-9437 Crate, Wood Open Fuel Tank External, As sembled MIL-Q-9858 Quality Program Requirenents MIL-S-8879 Screw Threads, Controlled Raius STANDARDS Federal Fed. Test Method Std. No. 791 Lubricants, Liquid Fuels, md Rel

7、ated Products; Methods of Testing Mi lit ary MIL-STD-129 Marking for Shipment and Storage MILSTD-130 1denti.tcation Marking of U.S. Militan Property MIL-STD-143 SpecificLtionc and Standards Order of Procedence for the Selection of MIL-STD-171 Finishing of Method and Wood Surfaces MIL-STD-i86 Protect

8、ive Finishing Systems for Rockets, Guided Missiles, Support Equipment and Related Materials MIL-STD-453 Inspection, Radiographic DRAWINGS Air Force-Navy Aeronautical Standard Drawing AN3 through AN20 Bolt, Machine, Aircraft HANDBOOKS MIL-HDBK-695 Military Standardization Handbook Rubber Products: Sh

9、elf Storage Life (Copies of specifications, standards, drawings, and publications required by suppliers in connection with s2ecific procurement functions should be obtained from the procuring activity or as directed by the con- tracting officer. ) 2.2 Other publications. The following documents of t

10、he issue in effect on date of invitation for bid or request for proposal, form a part of this specification to the extent specified herein. 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-5208B 28 W 7799706 011i534 7 MIL-T-5208B GOVERNMENT U.

11、 S. Department of Commerce National Bureau of Standards Handbook H28 (Part I) Screw Thread Standards for Federal Services (Application for copies should be addressed to the Superintendent of Documents, Government Printing Office, Washington, D. C. 20402. ) 3. REQUIREMENTS 3.1 Detail specification. A

12、 detail specification for tankage may be prepared following the form of this specification, for proposals when the tank is procured independent of the rocket engines, to define detail requirements for each application. Omission of reference in the detail specification to a particular requirement of

13、this specification shall be interpreted as compliance herewith. When departures are necessary from the requirements of this specification, the details of such departures shall be stated as specific requirements bearing the same section, para- graph heading, and numbering as in this specification. Wh

14、en a tank is procured as a component part of the rocket engine, any deviations to the tank specification shall be so specified in the rocket engine model specification . 3.2 Materials. Materials used in the manufacture of rocket engine tankage shall be of high quality and be suitable for the purpose

15、 intended, and be procured to Federal or Military specifications, wherever possible, When contractors specifications are used for materials which affect performance or durability of a tank, such specifications shall be approved by the Government prior to any preliminary and preproduction tests. The

16、use of non-Governmental specifications shall not constitute waiver of Government inspection. The material employed in the construction of any tankage shall be compatible with the fluid which it contains. 3.2.1 Critical materials, The use of critical materials as listed herein shall be held to a mini

17、mum. The estimated weight of each of the following materials based on the raw stock and finished parts required in the construction of a rocket engine tank shall be submitted by the contractor with the design drawings at the same time they are submitted for initial release. The final data shall be m

18、ade available to the procuring activity upon request after completion of 10 production units, Chromium Cobalt Columbium Molybdenum Natural rubber Nickel Tungsten 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-5208B 28 W 7997706 038LI535 7 MI

19、 GT-5208B 3.2.2 Metals. All materials from which the tank is constructed shall be resistant to or suitably protected from corrosion caused by atmospheric conditions as well as attack by the contained propellant. The procedures specified in MIL-STD-171 shall be followed where appli- cable. are in con

20、tact with the propellants. where contact with the propellant is not involved, provided that suitable precautions are taken to prevent electrolytic corrosion. The use of dissimilar metals shall be avoided where such metals Dissimilar metals may be used 3.2.3 Selection of materials. Specifications and

21、 standards for all materials , parts , and Government certification and approval of processes and equipment , which are not specifically designated herein and which are necessary for the execution of this specification, shall be selected in accordance with MIL-STD-143 except as provided in the follo

22、wing paragraph. 3.2.3.1 Standard parts, Standard parts (LUS and AN) shall be used wherever they are suitable for the purpose, and shall be-identified on the drawing by their part numbers, bolts, nuts, cotter pins, etc., may be used only if MS, AKj FIAS, etc, parts are not available for a particular

23、design application and if they meet the quality standards of these parts, Commercial parts such as screws, 3.3 Design and construction. 3.3.1 Design standards, MS and AND design standards shall be used wherever applicable . 3.3.2 Drawings. The requirements of the approved manufacturers drawings or o

24、f the procuring activitys drawings are applicable as requirements of thi 8 specif i cation. 3.3.2.1 Approval of drawings for preliminary tests, Manufacturers drawings shall De approved by the procuring activity prior to starting the construction of the preliminary test tanks. tanks are those tanks c

25、onstructed for the purpose of conducting prelimin- ary tests as specified in 4.4. The preliminary test 3.3.2.2 Release of drawings for preproduction tests, Manufacturers drawings will be released by the procuring activity prior to starting the construction of tanks for the preproduction test tanks,

26、The preproduction test tanks are those tanks constructed for the purpose of conducting pre- production tests as specified in 4.5. 3.3.3 Capacity. The design gross capacity and the design usable capacity of a tank shall be as specified by the procuring activity or as specified in the rocket engine mo

27、del specification, whichever is applicable (6.3.7 and 6.3.8). 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-5208B 28 7797706 0184536 O 3.3.3.1 TYP e I tanks. The gross and usable capacity of type I production tanks shall be within the range

28、 of +3 to O percent up to a maximum of O to +i5 gallons of the designed gross and usable capa- cities of the tank. 3.3.3,l.l EXP ansion space, Propellant tank capacity shall include a suitable volume for the expansion of the propellant subject to the approval of the procuring activity. This expansio

29、n volume shall be determined on the basis of a 100F (37.8OC) temperature rise of the pro- pellant if not specified otherwise in the rocket engine model specifica- tion or by the procuring activity, from a reference temperature specified in the rocket engine model specification or by the procuring ac

30、tivity, It shall also include any additional capacity that may be necessary for expansion of the propellant resulting from aerodynamic heating, 3a3.3.2 Typ e II tanks. The gross capacity of type II production tanks shall be within the range of +3 to O percent of the designed capacity of the tank. 3.

31、3.4 TYP e I tank outlets. Unless otherwise specified by the procuring activity, the tank design shall provide full, continuous propellant supply to the rocket engine or boost pump for the design- operating conditions of the aircraft, missile, or vehicle application in which the tank is installed. Th

32、ese requirements shall be achieved under all flight and load conditions for time intervals specified by the procuring activity. parts shall be approved by the procuring activity. The requirement for and the location of drain 3.3.5 Filler connections. Filler connections for fluid tanks shall be subje

33、ct to approval by the procuring activity. 3.3.6 Durabilitx, The tank shall be constructed to withstand the conditions incident to shipping, storage, installation, and service use. 3.3.7 Access doors. Unless otherwise specified, suitable openings shall be provided for inspection and removal of foreig

34、n material. 3.3.8 Weight, The weight of production tanks shall not exceed the maximum value shown on the approved drawings, and unless otherwise specified, shall be within 23 percent of the average weight of the first 10 tanks. 3.4 Interchangeability, All parts having the same manufacturers part num

35、ber shall be directly and completely interchangeable with each other with respect to installation and perlormance. Changes in manu- facturers part numbers shall; be governed by the drawing number require- ments of MIL-D-1000. 3.5 Finish of cells or liners. The external surfaces of rubber cells shall

36、 be ozone resistant or suitably protected against the action of ozone and the propellant for which the tanks are intended, (Reference MIL-HDBK-695. ) 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-T-52088 28 m 777770b 0184537 2 MIL-T-5208B 3.

37、6 Threads. Conventional straight screw threads shall conform to the requirements of MIL-S-7742 and Handbook H28, Part I, or MIL-S- 8879. Duplicate parts, differing only in thread form, shall not be permitted, Unless otherwise specified, threaded parts smaller than 0.164 inch diameter shall have thre

38、ads in accordance with MIL-S-7742. When an allowance is required for applications in elevated temperature, corrosive atmosphere, or other conditions which may cause thread seizure, this allowance shall be obtained by increasing the diameters of the internal threads. 3.6.1 Locking threaded parts, All

39、 threaded fasteners shall be securely locked. with gaskets or seals where a specified torque is required without the specific approval of the procuring activity. Self-locking devices shall not be used in conjunction 3.7 Antiseize compounds. Antiseize compounds used in assembly shall be specified on

40、the contractors drawings and in the preproduction test report. 3.8 Riveting,. Rivets through the skin of all-metal tanks are not permitted. 3.9 Markings. Each part or assembly shall be marked with a part number, which shall be the same as the drawing number of that part or assembly. An assembly cons

41、ists of parts that are permanently fastened together by welding, brazing, soldering, or riveting. this marking are those parts that do not have a suitable or sufficient surface for a part number. order to provide tracability to records. be used in highly stressed areas, nor shall they be used in any

42、 way as to adversely affect the structural integrity of the part. Exceptions to In addition, parts shall be serialized in Indented markings shall not 3.9.1 Location of part numbers. The part number shall, when practicable, be located to permit its being read after assembly in the complete unit, effa

43、ced or obliterated, as a result of service usage, during the life of the part. The marking shall be such that it will not be 3.9.2 Access door covers. The exterior surface of all access door covers shall be durably and legibly marked “OUTSIDE“, 3.9.3 Assembly torque, The torque values required to as

44、semble the fittings and accessories to the tank or cell shall be durably and legibly marked on, or adjacent to, each fitting or accessory involved, on the side to which the torque wrench is applied. Where the torque required to assemble all fittings and accessories is the same, the proper torque val

45、ue shall be stenciled in a conspicuous place. 3.10 Loading conditions. 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- _ -_ - _. - MIL-T-5208 28 = 7777906 0184538 4 E - MIL-T-5208B 3.10.1 Strength. The rocket engine tank and its support shall be c

46、apable of providing elastic strength to sustain any and all com- binations of loading defined in 3.10.1.1 and 3.10.1.2, and providing ultimate strength integrity for i50 percent of these same conditions of loading. tion of the procuring activity when acceptable substantiating analy- tical data are f

47、urnished by the contractor. These design load factors may be modified at the discre- 3.10.1.1 Aircraft (lass i) rocket system tankage. All conditions of limit loading for aircraft rocket system tankage shall be determined by the use of load factors specified in figure 1. 3.10.1.2 Aircraft launched r

48、ocket system tankage (class 2). All conditions of limit loading for aircraft launched rocket system tankage while attached to the aircraft shall be determined by the use of the load factors specified in figure 2. 3.10.1.3 Remotely launched missile tankage (class 3). The flight maneuver loads shall b

49、e specified for each individual rocket system tankage in the rocket engine model specification. 3.10.2 Internal pressure loading conditions, The rocket engine tankage shall be designed to restrain the internal pressurization loading conditions specified in 3.10.2.1 and 3.10.2.2. 3.10.2.1 Limit pressure load. The rocket engine tank shall be designed to withstand, without permanent set in excess of that specified on approved drawings , the con