1、, NIL-F-87GC 35 m 9999906 0387843 9 M - Y hIL-F-8785C 5 November 1980 SUPERSEDING 7 August 1969 MIL-F-8785E MILITARY SPECIFICATION FLYING QUALITIES OF PILOTED AIRPLANES This specification is approved for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 ScoDe. This speci
2、fication contains the requirements for the flying and handlins qualities, in flight and on the ground, of U.S. Military, manned, piloted airplanes except for flight at airspeeds below Vcon (MIL-F-83300). It is intended to assure flying qualities that provide adequate mission performance- and flight
3、safety regardless of design implementation or flight control system mechanization, The structure of the specification allows its use to guide these aspects in design tradeoffs, analyses and tests. 1.2 ADDliCatiOn, The flying qualities of all airplanes proposed or contracted for shall be in accordanc
4、e with the provisions of this specification. The requirements apply as stated to the combination of airframe and related subsystems. Stability augmentation and control augmentation are specifically to be included when provided in the airplane, The automatic flight control system is also to be consid
5、ered to the extent stated in MIL-P-9490 or PIIL-C-18244, whichever applies. The requirements are written in terms of cockpit flight controls that produce essentially pitching, yawing and-rolling moments. This approach is not meant to preclude other modes of control for special purposes, Additional o
6、r alternative requirements may be imposed by the procuring activity in order to fit better the intended use or the particular design. 1.3 Classification of airDlanes. For the purpose of this specification, an airplane shall be placed in one of the following Classes: Class I Small, light airplanes su
7、ch as Light utility Primary trainer Light observation Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: ASD/ENESS, Wright-Patterson AFE, OH 45433 by using the self-addressed Standardization Docume
8、nt Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter. THlS q3 :jjthe requirement shall apply to all Classes, When operational missions so dictate, an airplane of one Class may be required by the procuring activity to meet selected requirements ordinarily specifie
9、d for airplanes of another Class. 1.3.1 Land- or carrier-based designation, The letter -L following a Class designation identifies an airplane as land-based; carrier-based airplanes are similarly identified.by -C. When no such differentiation is made in a requirement, the requirement shall apply to
10、both land-based and carrier-based airplanes, 1.4 Flight Phase Categories. The Flight Phases have been combined into three Categories which are referred to in the requirement statements. These Flight Phases shall be considered in the context of total missions so that there will be no gap between succ
11、essive Phases of any flight and so that transition will be smooth. In certain cases, requirements are directed at specific Flight Phases identified in the requirement, When no Flight Phase or Category is stated in a requirement, that requirement shall apply to all three Categories. Flight Phases des
12、criptive of most military airplane missions are: Nonterminal Flipht Phases: Category A - Those nonterminal Flight Phases that require rapid maneuvering, precision tracking, or precise flight-path control. Included in this Category are: a. Air-to-air combat (CO) 2 Provided by IHSNot for ResaleNo repr
13、oduction or networking permitted without license from IHS-,-,-MIL-F-8785C b. Ground attack (GA) c, Weapon delivery/launch (WD) d. Aerial recovery (AR) e. Reconnaissance (RC) f. In-flight refueling (receiver) (RR) g. Terrain following (TF) h. Antisubmarine search (AS) i. Close formation flying (FFI.
14、Category E - Those nonterminal Flight Phases that are normally accomplished using gradual maneuvers and without precision tracking, although accurate flight-path control may be required. Included in this Category are : a. b. C. d. e. f. g. h. Climb (CL) Cruise (CR) Loiter (LO) In-flight refueling (t
15、anker) (RT) Descent (D) Emergency descent ( ED) Emergency deceleration (DE) Aerial delivery (AD). Terminal Flight Phases: Category C - Terminal Flight Phases are normally accomplished using gradual maneuvers and usually require accurate flight-path control. Included in this Category are: a. Takeoff
16、(TO) b, Catapult takeoff (CT) c, Approach (PA) d. Wave-off/go-around (WO) e . Landing (L) When necessary, recategorization or addition of Flight Phases or delineation of requirements for special situations, e.g., zoom climbs, will be accomplished by the procuring activity. Provided by IHSNot for Res
17、aleNo reproduction or networking permitted without license from IHS-,-,-MIL-F-8785C 1.5 Levels of flvina aualities. Where possible, the requirements of section 3 have been stated in terms of three values of the stability or control parameter being specified, Each value is a minimurn condition to mee
18、t one of three Levels of acceptability related to the ability to complete the operational missions for which the airplane is designed, The Levels are: Level 1 Flying qualities clearly adequate for the mission Flight Phase Level 2 Flying qualities adequate to accomplish the mission Fli3ht Phase, but
19、some increase in pilot workload or degradation in mission effectiveness, or both, exists Level 3 Flying qualities such that the airplane can be controlled safely, but pilot workload is excessive or mission effectiveness is inadequate, or both, Cateqory A Flight Phases can be terminated safely, and C
20、ategory B and C Fli9;ht Phases can be completed, 2, APPLICABLE DOCUMENTS 2.1 Issues of documents. The following documents, of the issue in effect on the date of invitation for bids or request for proposal, form a part of this specification to the extent specified herein: SPECIFICATIONS MILITARY MIL-
21、D-8708 MIL-A-8861 MIL-F-9490 MIL-C-1 8244 MIL-F-18372 MIL-W-25140 MIL-F-83300 MIL-S-83691 STANDARDS MIL-STD-756 Demonstration Requirements for Airplanes Airplane Strength and Rigidity Flight Loads Flight Control Systems - Design, Installation and Test of, Piloted Aircraft, General Specification for
22、Control and Stabilization Systems, Autonatic, Piloted Aircraft, General Specification for Flight Control Systems, Design, Installation and Test of, Aircraft (General Specification for) Weight and Ealance Control Data (for Airplanes and Rotorcraft) Flying Qualities of Piloted V/STOL Aircraft Stall/Po
23、st-Stall/Spin Flight Test Demonstration Requirements for Airplanes Reliability Prediction (Copies of specifications and standards required by contractors in connection with specific procurement functions should be obtained from the procuring activity or as directed by the contracting officer), 4 Pro
24、vided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3. REQUIREMENTS MIL-F-8785C 3.1 General reauirements 3.1.1 ODerational missions, The procuring activity will specify the operational missions to be considered by the contractor in designing the airplane to
25、 meet the flying qualities requirements of this specification. These missions will include all associated Flight Phases and tasks, such as takeoff, takeoff abort, landing and missed approach. Operational missions include the entire spectrum of intended usage to include aircrew upgrade and . training
26、. 3.1.2 LoadinQs. The contractor shall define the envelopes of center of gravity and corresponding weights that will exist for each Flight Phase. These envelopes shall include the most forward and aft center-of-gravity positions as defined in MIL-W-25140. In addition, the contractor shall determine
27、the maximum center-of-gravity excursions attainable through failures in systems or components, such as fuel sequencing, hung stores, etc., for each Flight Phase to be considered in the Failure States of 3.1.6.2. Within these envelopes, plus a growth margin to be specified by the procuring activity,
28、and for the excursions cited above, this specification shall apply. 3.1.3 Moments and DrOdUCtS of inertia. The contractor shall define the moments and products of inertia of the airplane associated with all loadings of 3.1.2. The requirements of this specification shall apply for all moments and pro
29、ducts of inertia so defined. 3.1.4 External stores, The requirements of this specification shall apply for all combinations of external stores required by the operational missions. The effects of external stores on the weight, moments of inertia, center-of-gravity position, and aerodynamic character
30、istics of the airplane shall be considered for each mission Flight Phase. When the stores contain expendable loads, the requirements of this specification apply throughout the range of store loadings. The external stores and store combinations to be considered for flying qualities design will be spe
31、cified by the procuring activity. In establishing external store combinations to be investigated, consideration shall be given to asymmetric as well as to symmetric combinations. 3.1.5 Confiaurations. The requirements of this specification shall apply for all configurations required or encountered i
32、n .the applicable Flight Phases of 1.4. A (crew-) selected configuration is defined by the positions and adjustments of the various selectors and controls available to the crew except for pitch, roll, yaw, throttle and trim controls, Examples are: the flap control setting and the yaw damper ON or OF
33、F. The selected configurations to be examined must consist of those required for performance and mission accomplishment. Additional configurations to be investigated may be defined by the procuring activity. 3.1.6 State of the aimlane. The State of the airplane is defined by the selected configurati
34、on together with the functional status of each of the airplane components or systems, throttle setting, weight, moments of inertia, center-of-gravity position, and external store complement. The trim setting and the positions of the pitch, roll and yaw controls are not included in the definition of
35、Airplane State since they are often specified in the requirements. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-F-8785C 3.1.6 . 1 AirDlane Normal States. The contractor shall define and tabulate all pertinent items to describe the Airplane N
36、ormal (no component or system failure) State.(s) associated with each of the applicable Flight Phases. This tabulation shall be in the format and shall use the nomenclature specified in 6.2. Certain items, such as weight, moments of inertia, center-of-gravity position, wing sweep, or thrust setting
37、may vary continuously over a range of values during a Flight Phase, The contractor shall replace this continuous variation by a limited number of values of the parameter in question which will be treated as specific States, and which include the most critical values and the extremes encountered duri
38、ng the Flight Phase in question. 3.1.6.2 AirDlane Failure States, The contractor shall define and tabulate all Airplane Failure States, which consist of Airplane Normal States modified by one or more malfunctions in airplane components or systems; for example, a discrepancy between a selected config
39、uration and an actual configuration. Those malfunctions that result in center-of-gravity positions outside the center-of-gravity envelope defined in 3.1.2 shall be included. Each mode of failure shall be considered, Failures occurrinq in any Flight Phase shall be considered in all subsequent Flight
40、Phases, 3.1.6.2.1 AirDlane SDecial Failure States. Certain components, systems, or combinations thereof may have extremely remote probability of failure during a given flight. These failure probabilities may, in turn, be very difficult to predict with any degree of accuracy, Special Failure States o
41、f this type need not be considered in complying with the requirements of Section 3 if justification for considering the Failure States as Special is submitted by the contractor and approved by the procuring activity, i I 3.1.7 ODerational Fliuht EnveloDes. The operational flight envelopes define the
42、 boundaries in terms of speed, altitude and load factor within which the airplane must be capable of operating in order to accomplish the missions of 3.1.1. Envelopes, for each applicable Flight Phase shall be established with the guidance and approval of the procuring activity, In the absence of sp
43、ecific guidance, the contractor shall use the representative conditions of table I for the applicable Flight Phases, 3.1.8 Service Fliaht EnveloDes. For each Airplane Norrnal State the contractor shall establish, subject to the approval of the procuring activity, Service Flight Envelopes showing com
44、binations of speed, altitude and normal acceleration derived from airplane limits as distinguished from mission requirements, For each applicable FliSht Phase and Airplane Normal State, the boundaries of the Service Flight Envelopes can be coincident with or lie outside the corresponding Operational
45、 Flight Envelopes, but in no case shall they fall inside those Operational boundaries. The boundaries of the Service Flight Envelopes shall be based on considerations discussed in 3.1.8.1, 3.1.8.2, 3.1.8.3 and 3.1.8.4. 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without li
46、cense from IHS-,-,-MIL-F-878SC 15 H 9777906 0187847 T M FLlCHT PHASE CATEGORY A TABLE- I. AIRSPEED ALTITUDE LOAD FACIOR 1 I FLIGHT PHASE I oain(Momin) 10 max (Mo max I I I I I I I I I 1 I I AIR-TO-AIR COMBAT (Co) : n,. MU T MSL 1.3 Vs. GROUND AITACK (GA) MAT MSL Combat -1 .O n, 1.4 vs Ceiling Medium
47、 -1.0 - I I WEAPON DELIVERY/LAUhCH MSL Combat range MAT -5 t WD 1 Ceiling ALRIAL RECOVERY (AR) MRT 1.2 vs MSL n,. .S Combat Ceiling I RECONNAISSANCli (RC) 1.3 Vs MSL *. Combat MAT Ceiling TAKEOFF (TQ) MSL Vmax Minimum Noma1 Takeoff Speed I APPROACH (PA) MSL Vmax Minimurn Normal Approach Speed WAVE-O
48、FF/CO-AROUND (Wo) MSL Vnax Miniqum Noma1 Approach Speed LANDING (L) I Minimum Normal Landing Speed I Combat 10,000 ft. Medium 2 .o + Cei 1 ing cruising1 : i : Ceiling Cruising Ceiling Cruising Ceiling 2*o Cruising 2,0 Ceiling Ceiling Cruising 2,0 Cruising 2.0 Ceiling 10,000 ft 0 2.0 10,000ft. .S 2.0
49、 - “L .S 9 10,000ft. 2 .o Appropriate to the operational aission. 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I MIL-F-8785C L5 U 9777706 O187848 1 m MIL-F-8785C 3.1.8.1 Maximurn service sDeed. The maximum service speed, Vmax or Mmax, for each altitude is the lowest of: a. The maximum permissible speed b. A speed which is a safe margin below the speed at which intolerable buffet
