NAVY MIL-B-8584 C-1970 BRAKE SYSTEMS WHEEL AIRCRAFT DESIGN OF《飞机设计车轮刹车系统》.pdf

1、ooMIL-B-85B4C12 Auxust 1970BUPERSSD2NGMIL-B-85B4B29 my 1963FIXL3TASY SPECIFICATIONBsASE SYSTFMS, WHEEL, A2RCSAFI!,DESIGN OFThis specification is mandatory for use by all Departmentsand Agencies of the Depnrtm.mt of Defense.1. SCOPE1.1 _ l%is specification covore the broke system deeign requirementsf

2、or aircraft equipped with wheel-type landing gear.1.2 Claasification. The brake systems shal1 ba either hydraulic or pneumatic;manually operated, power operated , manual-power operated; and shal 1 be of thefolloviqgtypes:Type I - Hanuol preseura generating: The control unitby manuo1 actuation.Type 1

3、1 - Power pressure generating: The control unitfrem a power generating system.Type III - 14mual pover pressure generating: Pre.ssurarated in a slave control unit which in turn operatesgenerates prea.mremeters pressureis manua 1ly gene-the main controlunit which meters fluid from n pre.sauregeneratin

4、g system.pe IV - Pewer-boosred manual preesure generating: The control unitgenerates preesure by manual actuation and, in addition, the manuallygenerated pressure ie boosted by pressure from a porergenerating system.pe V - Pover brake valve with emergency maeter cylinder: One part ofthe control unit

5、 meters pressure from R power generating syetem,and another part of the control unit eervee as a standby manualpressure generating unit when the power system ie inoperative.PSC 16304!9Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 , . 0 ,.,.,.11 L

6、 D -0 ,y+b2. APPLICASLR DOCUMSNTS* 2.1 The following documents of the issue in effect on date of invitationfor bids or request for proposal. form a Dart of this specification to theextent specifidSPECIFICATIONSMilitaryMIL-T-781MIL-W-5013MIL-w-5424MIL-H-5440MIL-P-5518MIL-v-5525MIL-C-6026MIL-P-703 W

7、ire Rope, Swa8ingWheel and Brake Assemblies: AircraftWire Rope, Steel, (Corrosion Resisting) Flexible,PrefOmed (For Aeronautical Use)Hydraulic Systems, Aircraft, Types I and 11, Design,Installation, and Data Requirements forPneumatic Systems, Aircraft; Design, Installation, andData Requirement forVa

8、lves, Aircraft Power BrakeControl Unit, Pressure Generating, Manually Operated,Aircraft Hydraulic Brake SystemPulleys, Groove, Antifriction-Bearing, Grease-Lubricated ,AircraftScrew Threads, Standard, Optimum Selected Series: Gene-ral Specification forCylinders; Hydraulic Brake, Master, Power Assist

9、edBrake Control Systems, Antiskid, Aircraft wheels: In-structions for Preparation of Specifications forHydraulic System Components, Aircraft and Missiles,General Specification forHose, Rubber, Hydraulic, Fuel and Oil ResistantHydraulic Systems, Manned Flight Vehicles, Type III,Design, Installation,

10、and Data Requirements forFlight Control Systeme - Design, Installation and Teatof, Piloted Aircraft, General Specification forFlight Control Systems, Design, Installation and Test of,Aircraft (General Specification for)Coupling Assembly, Hydraulic, Self-Sealing, Quick Dis-connectAircrew Station Cont

11、rols and Displays for Fixed WingAircrafta71Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-o*o*0MIL-s2o-250 AircrewStationControlsAircraft!4s33540 SafetyWiringand CotterAir Force-Naw AeronauticalAN6204 Valve, Hydraulic Blcedcr(Copies of specification

12、s, standards, drawings,UIL-B-8584Cand Oisplays for Rotary WingPinning, Ganernl Praccicef3forend publicetione required bysuppliers in-conncccion with specific procurement functione ehouId be obtainedfrom che procuring activity or as directed by chc contracting officer).3. RSQUIREHSNTS3.1 General requ

13、irements. The brake syetems covered by this specificationshe11 be operable under al1 conditione of weather and compatible with the type(temperature range) and class (pressure limits) of hydraulic or pneumatic sys-tems as specified in MIL-H-5440, MIL-P-5518, or HIL-H-BB91, whichever isapplicable.3.2

14、Selection of materials. Specificntione and standards for all materials,parte, and Government certiftcntf.onand approval of processes and equipment,which are not specifically deeignaced herein and which ore necessary for theexecution of this specification, ehnll be selected in accordance with procedu

15、resestablishedby the procuringactivity,exceptas providedin the follwingperagraph.3.2.1 Standardparts. Standardparts (MSor AN) shn11be usedvherevertheyare euitable for the purposeand shallbo identifiedon the drawing by theirpartnumbers. In theevent thereia no euitablecorrespondingetandardpart ineffec

16、ton dote of invitationforbide,commercialportemay be used providedtheyconform to al1 requirement of this specificetion and mre than one sourceis available for replacement.3.3 Design. The deeign and installation of circraft brokfng systems shall bein accordance with the applicable requirements of MIL-

17、H-5440, MIL-P-5518,MIL-H-8775, MIL-H-8891, or MIL-F-18372 and MIL-F-9490 and shell employ to thefulleet possible extent the stnndord components listed therein. TYpO IV brakesystems hall be used on all carrier-baead oircraft for which the type I systemwwld be inadequate to hold tha aircraft on a 10”

18、alope at maximum design grossweight. A type II brake system IMY be used for carrier-boeed nircroft whichhave an antiskid control Wstem. Where type I or type IV manual eyatems alone. . . .will not meet the 10 slope requirements, a type 11, III, or Vused, but epecial provisions10” slope without the ue

19、e ofsho11 be incorported to hold thenormal pOwer-generatin8 eystems.sys_temshall beaircroft on theAll detachable3Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-B-8584cI*components and parts shall be safetied in accordance with MS33540 or secured

20、by an approved method that wi 11 prevent loosening.3.3.1 Wheels and brakes. Wheel and brake aeaemb lies shall conform to therequirements of MIL-W-5013 and the applicable standards.3.3.2 Normal brake controls. Right and left brakes shall “be separatelyactuated and shall be so designed that they can b

21、e applied by toe force onbrake pedals on the rudder controls except for bicycle gear or quadricyclegear, where other suitable brake controle may be used s“bject to approval ofthe procuring activity. Pedal location shall conform to the requireme”ta ofMIL-STO-203 or MIL-STO-250, as applicable. The bra

22、ke pedal linkages shall be sodesigned that a comfortable angle of approximately 90” betw”een the pilots footand his lower leg is maintained throughout the full range of movement of therudder pedals and seat. Strength sha11 be provided in the brake pedal and as-sociated linkage to withstand 300 pound

23、s applied at the tip of the pedal withno yielding. The desired shape and travel of the brake pedals and the brakecontrol device shall be as free as possible of friction and lot motion (Beefigures l-and 2). Means shall be provided to positively return the brake ped-als to the off position when toe fo

24、rce is removed from the pedals. No pumpingsha11 be allowed 1“ order to meet the deceleration and parking requirements.3.3.2.1 Manual Iy operated systems, type 1. Manual hydraulic braking controlsystems shall incorporate a brake control unit or units which shall conform to a71MIL-C-6026. The total di

25、splacement of the control unit shall be at least 25percent greater than the maximum displacement, including line expansion re-quired to hold the wheels locked against a 33 slope for aircraft at maximumdesign gross weight and a 20 slope for helicopters at design alternate grossweight. The control uni

26、t shall preferably be connected directly to the brakepedal lever. The compressible medium of the temperature compensating devicein the concrol unit shall be designed with a minimum preload of 50 percent anda minimum bottoming load of 125 percent of the parking pressure required tohold aircraft on an

27、 lB” slope at maximum design gross weight and to hold heli-copters on a 10 slope at design alternate gross weight. This device shallhave fluid displacement equivalent to the change in volume of the fluid in thebrake system, neglecting the reservoir, under a temperature change of 44 .4C(112”F) . Manu

28、al braking control systems shall be such that:(a) A foot force of between 15 and 20 pounds at the tip of the pedal shall berequired to cause initial movement of the brake pedal.(b) A foot force of between 75 and 125 pounds at the tip of the pedal shalldevelop the torque required on the landplane lan

29、ding design gross weight orat design alternate gross weight brake stop conditions of the table entitled4Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-,.,: ro0FuLCRUM /Ifir16RAD3- -l_,+ M6.X RCtDMIL-B-8584C+!T9 MAXS MIN1 j - -.- .- DIMENSIONS IN INC

30、HESFIGURE 1. BrakePedalShape50Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-B-8584CMAX TRAVEL PARKING BRAKEON -MANUAL SYSTEM ONLYMAX SERVICE TRAVEL/ MANuAL SYSTEMRANGE OF TRAVEL FOR MAXIMUMBRAKE PRESSURE- POWER SYSTEMBRAKE OFF POSITION-MANUALOR

31、 POWER SYSTEMIFuLCRUM 36BRAKE PEDALJFLOOR LINEFIGURE 2. Brake Pedal TravelProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.- 100tlIbfI-8584C“wheelBrakeCnpncityRcquirementa”of UIL-W-5013. Rv3brake pressure thusobtained shall be connisccnt with the ttv

32、erngeof the repeated dynamometertests of the brako in the lmdplnno hnding dcalgn gross wei8ht condition orat deafen alternnte Sross woi8ht.(c) The trcive1 of tho pednl for full brnko application ahnll ba an indicatedon fi8ure 2. It shall not exceed 30” whilo mcacin8 the requircmmnta of sub-paragraph

33、 (b) nbovc.* (d) In all positions of the brake pedal or ch.?rudder linkage and the seat,ic ahal1 bo possible for tho pilot to apply sufficient stack brake torque tohold the wheels locked tigainata 33” slops for nircrnfc at maximum design grosswei8ht and a 20” S1OPC for hcllcoptera at dsi8n alternnce

34、 groan weight. Itshall be possible to meet thin requirement with tho brakes at n temperature of21C (70”F).3.3.2.2 Power-opcrntcd syntems, CYPCS 11 and III. Power-operated brake con-trol ayetems shall exhibitno objectionablecimclagbetween pedal movement andbraka reapon.se. Such systems shnl1 dcvalop

35、feel” at the pedale, in proportionto the amount of enorgizin8 force npplicd to the brake. Rydrnulic p0UC3rbrakevnlves hall conform to MIL-V-5525. lhonormal brnkc systam, including nccumu-latore if used, shal1 be daslgncd to prevant depletion of brake prtissuresupplydue to pi10C operation durin8 nor

36、mal lnndin8 run or ground hmd ling of the aLr-craft. ConaidorarionahouIdbo given co appropriatehydraulicpump operatingapeede.3.3.2.2.1 Pow? brakin8 ayatems shall be tmxh chat:(a) A foot forcoof botwcen 15 and 20 pounds at the tip of the pedal shall berequired to cauea initial mntcring throush tho po

37、vcr broke valve.* (b) A fmcforceof betwcah 65 to 85 pounds at chc tip of the pedal shalldevelop the torque required on the landplane landing design Srosa weisht or atdesign alternate 8ross weight brake stop conditions of the table entitled “WheelBrake Capacity Requirements” of WL-W-5013. The brake p

38、rcseure thus obtainedshall be consistent with the nverase of the repented dynanwme.cer tests of thebrake Ln the landplane landing design gross weight condition or at desisnalternate 8roas waisht.* (c) Brnkc pressure sufficient to hold the wheels locked shall be available atthe upper ranges of travel

39、 of the brake pedal or rudder linkage and the seat tohold against a 33” S1OPC for aircr4ftat maximum desi8n gross wei8ht and a 20slope for helicopters at design oltcrnntecross weight. It shall be possibIeco meet this condition with the brakes at a temperature of 21*C (70”F).4!3Provided by IHSNot for

40、 ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-B-8584C(d) The travel of the pedals shall be as shown on figure 2. It shall be be-tween 15 and 25 to produce the maximum available brake pressure.* 3.3.2.3 Controls of carrier-based aircraft, tvpes II. IV, and V systems.

41、On those carrier-based aircraft where power brake systems are required, thebrake control shall conform to MIL-c-7979. as applicable. With the Power sYe-ternoperative, the brakes shall meet the requirement for power-operated systems.With the power system inoperative, the systernshall meet the require

42、ments for*manually operated systems, except the deceleration capability at 175 poundsmaximum foot force shall be consistent with the aircraft operational require-ments as approved by the procuring activity. For helicopters, 175 poundswximum foot force shall produce a 5 foot per second per second dec

43、elerationat basic design gross weight. The braking capability must be adequate for aminimum aircraft braking coefficient of friction of 0.2.3.3.3 Emergency brake control system. All aircraft using types II and IIIbake systems shall be provided with an emergency brake system capable ofdecelerating th

44、e aircraft under the conditions specified in 3.3.2.2.l(b).If an emergency hydraulic system is used, metered differential brake controlshall be provided. The emergency system shall be completely independent ofthe normal system up to the shuttle valve or equivalent unit at the brake.A system wherein a

45、 failure of one-half of the normal system still allows thespecified decelerations with differential control is considered equivalentto a separate emergency system. When accumulators or air bottles are usedfor the emergency braking, they shall have s“fficient capacity to provide acleast 10 full brake

46、 applications, assuming brakes are adjusted to recommendedclearances, and of which the last shall provide a coefficient of 0.18 minimumbetween tire and runway recommended clearances. The volume of hydraulic fluidrequired should be based on pressures and displacements required to meet thespecified de

47、celeration applications considering three of the applications arewith cold brakes and seven are with hot brakes . If air bottles are used forthe emergency system, the lines between the air bottle control valve and theshuttle valve shall be automatically vented to the atmosphere when not in use.Whene

48、ver feasible, emergency brake systems shall function by continued pres-sure on the brake pedal. Emergency systems shall be designed to facilitateoperational checks. The emergency brake system shall be designed to precludeentrapment of the normal system fluid within any of the components whichcould p

49、revent the brake system from going into an emergency mode.3.3.4 General design requirements3.3.4.1 Brake t!ystemscm all aircraft shall be provided “ith a parking brakecontrol located a“d actwated in accordance with MIL-STO-203 a“d MIL-STO-250,aS applicable, exc”eptthat the parking lock may be omitted from jet-poweredga71-1Provided by IHSNot for ResaleNo reproduction or networking permitted without licen