1、SUPERSEDING MIGSTD-176 1 March 1955 MILITARY STAN DARD WEIGHT AND BALANCE DATA REPORTING FORMS GUIDED MISSILES AND SPACE LAUNCH VEHICLES FOR FSC CLASS 1400 P 61 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-STD-37hA 34 7777733 0073340 7 I MIL-
2、STD-176A DEPARTMENT OF DEFENSE WASHINGTON, DOC. 20360 Weight and Balance Data Reporting Forms for Guided Missiles and Space Launch Vehicles 1. This standard has been approved by the Department of Defense and is mandatory for use by the Departments of the Army, the Navy, and the Air Force, effective
3、27 May 1963. 2. Recommended corrections, additions, or deletions should be addressed to Bureau of Naval Weapons, Nwy Dept., Washington, D.C., 20360. II Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-17bA 14 W 77777LL 0073341 O MIL-STD-176A C
4、ONTENTS Page Paragraph 1.1 1.2 1.3 2. 3. 4. 5. 5.1.1 5.1.2 5.1.2.14 5.1.3 6. SCOPE ._._._._ Concepts _. _-. Principles-.-.-.-.- _.-. REFERENCE DOCUMENTS DEFINITIONS AND ABBREVIATIONS _-. GENERAL STATEMENTS AND DETAIL REQUIREMENTS 6. REQUIREMENTS Summary Weight Statement (Part I) _._ Detail Weight St
5、atement (Part II) _.-_._- Structural Increments for Design Features Appendix I to Detail Weight Statement _._._ Weight and Balance Status (Part IIIA, Part WEIGHT SUMMARY FOR PERFORMANCE ANALYSIS APPENDIX II 4 6 6 7 10 10 11 WEIGHT STATEMENTS Part I. SUMMARY WEIGHT STATEMENT Part II. DETAIL WEIGHT ST
6、ATEMENT Part IIIA, IIIB, WEIGHT AND BALANCE STATUS Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-176A This revision to MIGSTD-176 dated 1 March 1955 is based on the cooperative efforts of the Military Services, Weight Engineers of the Missi
7、le Industry, representatives of the National Aeronautics and Space Administration, the National Committee of the Society of Aeronautical Weight Engineers and the Aero Space Industries Association. In general, this standard provides for the mass properties reporting of the complete spectrum of small
8、and large missiles and space launch vehicles. These reported data provide the technical background for weight control engineering, weight optimization studies, the derivation of pro- posal analysis techniques and provides inputs to industrial planning re- ports for measuring the national industrial
9、effort. The standard follows the general philosophy used in MIGSTD-254 Weight and Balance Data Reporting Forms for Aircraft and MIGSTD- 451 Weight and Balance Report Forms for Rotocraft and is adaptable to either manual or machine method preparation. V Provided by IHSNot for ResaleNo reproduction or
10、 networking permitted without license from IHS-,-,-WEIGHT AND BALANCE DATA REPORTING FORMS FOR GUIDED MISSILES AND SPACE LAUNCH VEHICLES 1. SCOPE 1.1 Scope. This document establishes weight statements and forms for procure- ment of weight and balance data for guided missiles, PARTS I, II and III her
11、eof, states the principles followed in the formulation of these statements and forms, furnishes in- structions where necessary for uniform com- pilation of the required weight and descrip- tive data, and provides a glossary of terms for which definitions may not be self evident on the weight stateme
12、nts and forms. The forms may be used for large and small mis- siles as well as booster vehicles employed for launching satellite or reentry payloads. 1.2 Concepts. The detail and summary weight statements have been predicated on the following basic concepts : (a) The primary purposes of the weight d
13、ata are to provide information in the most advantageous form for development and improvement of guided missiles weight estimating and optimization meth- ods and for mass characteristics control during design, construction and operation- al use of these vehicles. Such data and methods serve the signi
14、ficant functions of bringing avoidable adverse trends to light at an early state, pointing out areas in which design weight control can be most fruitful, establishing realistic weight goals, evaluating on a rational basis the weight costs of design features during evaluation of new configurations, d
15、eter- mining the deviations (from planned weight or mass characteristics) which occur under actual test or operating con- ditions, and providing timely controlled weight input to flight trajectory planning for changes during design and operation. (b) The secondary purpose of the weight data is to pr
16、ovide reasonably de- tailed information for engineering check- ing and reference purposes. 1.3 Principles. The following principles have been followed to implement the above basic concepts : (a) The total missile weight is sub- divided into functional and identifiable divisions that best serve the b
17、asic con- cepts for both large and small missiles. The missile is subdivided into identifiable steps and/or sections as shuwn in Figure 1 as an example. This breakdown is ac- complished by the use of vertical columns in the reporting forms which must be properly identified at the top of each column.
18、 This makes it possible to handle multistage vehicles and also to give sec- tionalized breakdowns of smaller missiles. It is permissible to use the vertical columns for sectional breakdowns within a step of a multistage vehicle by using more than one column for a single step. However, once a particu
19、lar arrangement of columns has been? established dividing the vehicle. into steps and/or sections, the same arrangement must be used through- out the form for that particular missile. (b) Within the step and/or section breakdown, the weight has been broken down into functional and identifiable ma- j
20、or and minor components. Insofar as practicable, all tangible and readily iden- tifiable components and provisions for a specific function or installation have been allocated to the functional group, regard- less of geographic location and physical method of attachment. Where compromise of this prin
21、ciple was necessary because of multi-purpose function, items have been allocated geographically with as complete functional isolation and identification as possible. Examples of multipurpose items are doors and panels which serve as clo- sures for a structural surface as well as a particular install
22、ation function, and items which, because of their integral nature, make quantitative allocation impractical. 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-9999911 0073344 b I MIL-STD-17bA 14 MIL-STD-176A (c) The importance of consistent allo- cat
23、ion of weights by all contractors in completing the detail statement has been recognized. The amplifying instructions herein are furnished to insure consistency in allocation to the greatest extent prac- ticable. 2. REFERENCED DOCUMENTS 2.1 The following standard forms a part of this standard to the
24、 extent specified herein: STANDARD Military MIGSTD-12B-Abbreviations f or Use on Drawings. 3. DEFINITIONS AND ABBREVIATIONS Tem Step Stage Useful Payload Carried Mass Weight Empty Mission Load Fixed Definition The mass of that portion of a vehicle which may be physically separated from other portion
25、s by disconnecting at staging in- terfaces. (See Fig. 1) The mass of that portion of a vehicle consisting of a Step plus all Steps above. (See Fig. 1) The mass of scientific instru- ments, carga, weapons, etc., de- livered to their destinations. The mass of that portion of a vehicle above the interf
26、ace of the subject Step. The Carried Mass of Step 1 is Stage 2. (See Fig. 1) Those items that make up a basic empty vehicle weight. Does not include any fluids or lubricants. Those items that must be added to an empty vehicle weight for flight but are not normally ex- pendable; and those items that
27、are aboard for a specific mis- sion but not necessarily aboard for all flights. ABBREVIATIONS-When abbreviations are nccessary for write-ins or in machine tabu- lation methods, the abbreviations of Military Standard MIGSTD-12B shall be used wher- ever space permits. The following list sum- marizes a
28、cceptable abbreviations commonly used for weight data or used in PARTS, I, II, and III of this standard. Where more than one abbreviation is shown, the first given is preferred. accessory-access., acc adjust-ad j aerodynamic-aerodyn, aero alighting-alight ammunition-amm, ammo antennas-ant arresting-
29、arg attachment-att auxiliary-aux booster-bstr bracket-brkt brake-bk celestial-celest command-com compartment-compt condition-cond construction-const controls-cont conversion-conver c ylinders-cyl degrees-deg digmeter-dia distribution-distr doors-drs e jection-eject electrical-elec electronic-elect e
30、mergency-emer enclosure-encl, enc equipment-equip exhaust-exh extension-ext Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STAGE 1 L STGE 2 /INTER I FACE INTER FACE 1-2 I STEP 1 FWD SECTION SEEKER hence, limited write- in spaces are provided for exp
31、ansion of the listed groupings and for new instgllations. Insofar as practicable, nomenclature for write-ins shall identify the functions of the items, and allocation shall be made consist- ent with the principles outlined above in Section 1.3. Use of the words, “provision” and “installation,” shall
32、 be avoided unless further breakdown is given to indicate what is included in the item. Supplementary sheets may be inserted when insufficient space is provided for new or unusual instal- lations or expanded breakdowns. 4.3 All bolts, nuts, rivets, etc., and loose items of attachment shall be alloca
33、ted to the same group as the item being attached. 4.4 Equipment and system supports shall be allocated to the same group as the items being supported. Multipurpose supports shall be allocated to the primary function. Where a primary allocation cannot be deter- mined by cbservation, such as may occur
34、 for fairings, fairleads, supports for wire har- ness, brackets, etc. an arbitrary allocation may be made. 4.5 Where provisions are made in both weight empty and mission load categories for a given installation, allocation shall be made to the weight empty or mission load in accordance with the cate
35、gory allocation as- signed in the model or detail specification or in the general design specifications and/or instructions of the procuring activity. If a conflict in category allocation of any item occurs between weight statement and model or detail specification, the latter shall govern in all ca
36、ses. 4.6 All items of power distribution systems (electrical, hydraulic, and pneumatic) , in- cluding fluid in the respective tubing for hydraulic systems, from main distribution points to actuating units shall be allocated with the items operated. All components from source of power to main distrib
37、ution points shall be considered to comprise the main system. The distribution system for a given item shpll be assumed to include all components which would be unnecessary and could be removed if power actuation of the item were to be eliminated. Where several successive branches frcm a distributio
38、n sys- tem are involved, and a clear CU main dis- tribution point is not readily apparent, it shall be assumed that power is supplied to a given geographic location primarily for the function requiring the largest power, and to other functions in the sequence of descending power requirements. 4.7 Wh
39、en abbreviations are necessary for write-ins due to lack of space, the abrevia- tions as required by Section 3 shall be used. 4.8 When business machine methods are utilized and reports are produced automat- ically by machines, all pages as shown on the Summary and Detail Weight Statements (Parts I r
40、tively lighter construction and serve the function primarily of stiffening the cover or skin to maintain contour un- 8 der load. Longerons serve to distribute the load longitudinally along with lon- gitudinal partitions which contribute to body strength. (c) Exterior Finish. This includes paint and
41、finish for protection from the elements. Any interior finish is coded to the item it covers. 5.1.2.3 Aerodynamic Surfaces (Page 2 and 3). This group is used for all primary lift- ing and aerodynamic control surfaces, both fixed and movable. 5.1.2.3.1 Page 2. Identify the various wings such as “verti
42、cal,” “horizontai,” etc. Auxiliary control surfaces which are at- tached to the wings shall be listed on page 3-“Surfaces.” (a) Leading Edge (item 16, 41) is de- fined as all st.ructure forward of the front spar. (b) Trailing Edge (Item 17, 42) is de- fined as all structure aft of the rear spar. (c)
43、 Core (Item 12, 37) is defined as sandwich hexcell (alum., stl., etc) or foam. (d) Exterior finish is to be allocated to covering. (e) Insulation in the wing, fin or sta- bilizer shall be a “write-in” item. (f) Wing-body splices and fittings are (9) Identify aero surface heat shields. 5.1.2.3.2 Page
44、 3. The surfaces on this page are to be identified and labeled whether “fixed” or “moveable.” Also identify aero- dynamic surface heat shields. 5.1.2.4 Body Group (Pages 4 and 5). The body group is arranged so that separate sec- tions may be broken down within each step column for multi-stage vehicl
45、es. Where total section weights as assembled are desired by the procuring agency and the above body format is used, addition sheets may be added to other groups where applicable to show to be allocated to the wing. Provided by IHSNot for ResaleNo reproduction or networking permitted without license
46、from IHS-,-,-MIL-STD-37bA LL( 7777713 0073353 3 breakdows by section. The body pages are broken up into distinct structural divisions compatible for booster or aerodynamic mis- siles. Identify sections which are integral fuel tanks by suitable title for example “for- ward fuel tank.” Identify by wri
47、te-in or note that structure which is jettisoned during flight boost phase. Write in, where appli- cable, the items used to provide the vehicle with the flexibility to operate in adverse environment ; for example, (a) ablative ma- terial or other protection for high tempera- ture environment, (b) in
48、tegral structural provisions for liquid cooling. 5.1.2.5 Takeoff and Recovery (Page 6). This group is intended to contain items which are primarily used for missile launch- ing and recovery. Enter descriptive or loca- tion data, as appropriate, for clarification of the function served. 5.1.2.6 Propulsion Group (Pages 7, 8, 9, 10, and il). This group covers those items whose primary function is to provide flight path thrust or acceleration. Other propul- sion devices, such as those used for electrical power or to maintain control of orientation are coded elsewhere. (Except for thr
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