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MIL-STD-1797A.pdf
CONTENTS
1. SCOPE
2. APPLICABLE DOCUMENTS
2.1 Government documents
2.2 Non–Government publications.
2.3 Order of precedence.
3. DEFINITIONS
3.4 Parameters.
3.5 Terms used in high angle of attack requirements
4. REQUIREMENTS
4.1 General requirements
4.2 Flying qualities requirements for the pitch axis.
4.2.1 Pitch attitude dynamic response to pitch controller
4.2.2 Pilot–induced pitch oscillations.
4.2.3 Residual pitch oscillations.
4.2.3 Residual pitch oscillations.
4.2.4 Normal acceleration at pilot station.
4.2.5 Pitch trim changes.
4.2.6 Pitch axis response to other inputs
4.2.7 Pitch axis control power
4.2.8 Pitch axis control forces
4.2.9 Pitch axis control displacements
4.3 Flying qualities requirements for the normal (flight path) axis
4.3.1 Flight path response to attitude change
4.3.2 Flight path response to designated flight path controller.
4.3.3 Flight path control power
4.3.4 Flight path controller characteristics.
4.4 Flying qualities requirements for the longitudinal (speed) axis
4.5 Flying qualities requirements for the roll axis
4.5.1 Roll response to roll controller
4.5.8 Roll axis control power
4.5.9 Roll axis control forces and displacements
4.6 Flying qualities requirements for the yaw axis
4.6.1Yaw axis response to yaw and side–force controllers
4.6.2Yaw axis response to roll controller.
4.6.3 Pilot–induced yaw oscillations.
4.6.4Yaw axis control for takeoff and landing in crosswinds
4.6.5Yaw axis response to other inputs
4.6.6Yaw axis control power.
4.6.7Yaw axis control forces.
4.7 Flying qualities requirements for the lateral flight path axis
4.8 Flying qualities requirements for combined axes
4.9 Flying qualities requirements in atmospheric disturbances
5. VERIFICATION
5.1 General requirements—verification
5.2 Flying qualities requirements for the pitch axis—verification
5.3 Flying qualities requirements for the normal (flight path) axis—verification
5.4 Flying qualities requirements for the longitudinal (speed) axis—verification
5.5 Flying qualities requirements for the roll axis—verification
5.6 Flying qualities requirements for the yaw axis—verification
5.7 Flying qualities requirements for the lateral flight path axis—verification
5.8 Flying qualities requirements for combined axes—verification
5.9 Flying qualities requirements in atmospheric disturbances—verification
6. NOTES
APPENDIX A
10. SCOPE
20. APPLICABLE DOCUMENTS
30. DEFINITIONS
3.1 Aircraft classification and operational missions.
3.2 Flight Phase Categories.
3.3 Levels and qualitative suitability of flying qualities
40. REQUIREMENTS
4.1 General requirements
4.1.1 Loadings.
4.1.2 Moments and products of inertia.
4.1.3 Internal and external stores.
4.1.4 Flight Envelopes.
4.1.4.1 Operational Flight Enve
4.1.4.2 Service Flight Envelopes.
4.1.4.3 Permissible Flight Envelo
4.1.5 Configurations and States of the aircraft.
4.1.6 Aircraft Normal States.
4.1.7 Aircraft Failure States.
4.1.8 Dangerous flight conditions.
4.1.9 Interpretation of subjective requirements.
4.1.10 Interpretation of quantitative requirements.
4.1.11 General flying qualities requirements
4.1.12 General flight control system characteristics.
4.1.13 General trim requirements
4.2 Flying qualities requirements for the pitch axis
4.2.1 Pitch attitude dynamic response to pitch controller
4.2.1.1 Long–term pitch response.
4.2.1.2 Short–term pitch response.
A. CAP
B. w sp Tq2 , z sp tq
C. Transient peak ratio, rise time, effective delay
D. Bandwidth, Time Delay
E. Closed–Loop Criterion
F. Time– and frequency–response criteria by Gibson
4.2.2 Pilot–induced pitch oscillations.
4.2.3 Residual pitch oscillations.
4.2.4 Normal acceleration at pilot station.
4.2.5 Pitch trim changes.
4.2.6. Pitch axis response to other inputs.
4.2.7 Pitch axis control power
4.2.8 Pitch axis control forces
4.2.9 Pitch axis control displacements
4.3 Flying quality requirements for normal (flight path) axis
4.3.1 Flight path response to attitude change
4.3.2 Flight path response to designated flight path controller.
4.3.3 Flight path control power
4.3.4 Flight path controller characteristics.
4.4 Flying qualities requirements for longitudinal (speed) axis
4.4.1 Speed response to attitude changes.
4.5 Flying qualities requirements for the roll axis
4.5.1 Roll response to roll controller
4.5.1.1 Roll mode.
4.5.1.2 Spiral stability.
4.5.1.3 Coupled roll–spiral oscillation.
4.5.1.4 Roll oscillations.
4.5.1.5 Roll time delay.
4.5.3 Linearity of roll response to roll controller.
4.5.4 Lateral acceleration at pilot station.
4.5.5 Roll characteristics in steady sideslip.
4.5.6 Roll axis control for takeoff and landing in crosswinds.
4.5.7 Roll axis response to other inputs
4.5.8 Roll axis control power
4.5.9 Roll axis control forces and displacements
4.6 Flying quality requirements for the yaw axis
4.6.1 Yaw axis response to yaw and side–force controllers
4.6.2 Yaw axis response to roll controller.
4.6.3 Pilot–induced yaw oscillations.
4.6.4 Yaw axis control for takeoff and landing in crosswinds.
4.6.5 Yaw axis response to other inputs
4.6.6 Yaw axis control power.
4.6.7 Yaw axis control forces.
4.7 Flying qualities requirements for the lateral flight path axis
4.7.1 Dynamic response for lateral translation.
4.8 Flying qualities requirements for combined axes
4.8.1 Cross–axis coupling in roll maneuvers.
4.8.2 Crosstalk between pitch and roll controllers.
4.8.3 Control harmony.
4.8.4 Flight at high angle of attack.
4.9 Flying qualities requirements in atmospheric disturbances
4.9.1 Allowable flying qualities degradations in atmospheric disturbances.
4.9.2 Definition of atmospheric disturbance model form.
4.9.3 Application of disturbance models in analyses.
APPENDIX BDETERMINING EQUIVALENT SYSTEMS
NOTE: MIL-STD-1797A has been redesignated as a handbook, and is to be used for guidance
purposes only. This document is no longer to be cited as a requirement. For administrative
expediency, the only physical change from MIL-STD-1797A is this cover page. However, this
document is no longer to be cited as a requirement. If cited as a requirement, contractors may
disregard the requirements of this document and interpret its contents only as guidance.
INCH-POUND
MIL-HDBK-1797
19 December 1997
SUPERSEDING
MIL-STD-1797A
28 June 1995
DEPARTMENT OF DEFENSE
HANDBOOK
FLYING QUALITIES
OF
PILOTED AIRCRAFT
This handbook is for guidance only.
Do not cite this document as a requirement.
AMSC N/A
FSC 15GP
DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited.
MIL–STD–1797A
DEPARTMENT OF DEFENSE
WASHINGTON DC 20402
Flying Qualities of Piloted Aircraft
1. This military standard is approved for use by all Departments and Agencies of the Department of Defense.
2. Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use
in improving this document should be addressed to: ASD/ENES, Wright–Patterson AFB, OH 45433–6503,
by using the self–addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at
the end of this document or by letter.
W A R N I N G
INFORMATION SUBJECT TO EXPORT CONTROL LAWS
This document contains information subject to the International Traffic in Arms Regulation (ITAR) and/or the
Export Administration Regulation (EAR) of 1979 which may not be exported, released, or disclosed to foreign
nationals inside or outside the United States without first obtaining an export license. A violation of the ITAR or
EAR may be subject to penalty of up to 10 years imprisonment and a fine of $100,000 under 22 U.S.C. or
Section 2410 of the Export Administration Act of 1979. Include this notice with any reproduced portion of this
document.
DESTRUCTION NOTICE. For classified documents, follow the procedures in DoD 5220.22–M Industrial
Security Manual, Section 11–19 or DoD 5200.1–R, Information Security Program Regulation, Chapter IX. For
unclassified, limited documents, destroy by any method that will prevent disclosure of contents or
reconstruction of the document.
ii
MIL–STD–1797A
FOREWORD
This standard is intended for use with fixed–wing aircraft supported primarily by aerodynamic force rather
than engine thrust. It also covers the handling characteristics of aircraft under piloted control on the ground,
and may be used with powered–lift aircraft in aerodynamic flight (above the conversion speed, Vcon ). This
standard also applies to piloted transatmospheric flight when flight depends upon aerodynamic lift and/or air
breathing propulsion systems. Flying qualities of military rotorcraft are specified in MIL–H–850l, while flying
qualities in V/STOL flight are the subject of MIL–F–83300.
For further background information, see Appendix C.
iii
MIL–STD–1797A
CONTENTS
Paragraph
Page
1.
1.1
1.2
2.
2.1
2.1.1
2.1.2
2.2
2.3
3.
3.1
3.2
3.3
3.4
3.4.1
3.4.2
3.4.3
3.4.4
3.4.5
3.4.6
3.4.7
3.5
4.
4.1
4.1.1
4.1.2
4.1.3
4.1.4
4.1.4.1
4.1.4.2
4.1.4.3
4.1.5
4.1.6
4.1.6.1
4.1.6.2
4.1.6.3
4.1.7
4.1.7.1
4.1.7.2
4.1.7.3
4.1.7.4
4.1.7.5
SCOPE
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Purpose
Applicability
1
1
1
APPLICABLE DOCUMENTS
Government documents
Specifications, standards, and handbooks
Other Government documents, drawings, and publications
Non–Government publications
Order of precedence
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1
1
1
1
1
1
DEFINITIONS
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Aircraft classification and operational missions
Flight Phase Categories
Levels and qualitative suitability of flying qualities
Parameters
General terms
Speeds
Thrust and power
Control parameters
Longitudinal parameters
Lateral–directional parameters
Atmospheric disturbance parameters
Terms used in high angle of attack requirements
2
2
2
2
2
2
3
5
6
6
8
16
18
REQUIREMENTS
General requirements
Loadings
Moments and products of inertia
Internal and external stores
Flight Envelopes
Operational Flight Envelopes
Service Flight Envelopes
Permissible Flight Envelopes
Configurations and States of the aircraft
Aircraft Normal States
Allowable Levels for Aircraft Normal States
Flight outside the Service Flight Envelopes
Ground operation
Aircraft Failure States
Allowable Levels for Aircraft Failure States
Aircraft Special Failure States
Probability calculation
Generic failure analysis
When Levels are not specified
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iv
MIL–STD–1797A
CONTENTS – Continued
Paragraph
Page
4.1.7.6
4.1.8
4.1.8.1
4.1.8.2
4.1.9
4.1.10
4.1.11
4.1.11.1
4.1.11.2
4.1.11.3
4.1.11.4
4.1.11.5
4.1.11.6
4.1.11.7
4.1.11.8
4.1.12
4.1.12.1
4.1.12.2
4.1.12.3
4.1.12.4
4.1.12.5
4.1.12.6
4.1.12.7
4.1.12.8
4.1.12.9
4.1.12.10
4.1.12.11
4.1.13
4.1.13.1
4.1.13.2
4.1.13.3
4.1.13.4
4.1.13.5
4.1.13.6
4.2
4.2.1
4.2.1.1
4.2.1.2
4.2.2
4.2.3
4.2.4
4.2.5
4.2.6
4.2.6.1
4.2.6.2
Failures outside the Service Flight Envelopes
Dangerous flight conditions
Warning and indication
Devices for indication, warning, prevention, and recovery
Interpretation of subjective requirements
Interpretation of quantitative requirements
General flying qualities requirements
Buffet
Release of stores
Effects of armament delivery and special equipment
Failures
Control margin
Pilot–induced oscillations (PIO)
Residual oscillations
Control cross–coupling
General flight control system characteristics
Control centering and breakout forces
Cockpit control free play
Adjustable controls
Rate of control displacement
Dynamic characteristics
Damping
Transfer to alternate control modes
Flight control system failures
Augmentation systems
Auxiliary dive recovery devices
Direct force controllers
General trim requirements
Trim system irreversibility
Rate of trim operation
Stalling of trim systems
Transients and trim changes
Trim for asymmetric thrust
Automatic trim systems
Flying qualities requirements for the pitch axis
Pitch attitude dynamic response to pitch controller
Long–term pitch response
Short–term pitch response
Pilot–induced oscillations
Residual pitch oscillations
Normal acceleration at pilot station
Pitch trim changes
Pitch axis response to other inputs
Pitch axis response to failures, controls free
Pitch axis response to configuration or control mode change
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v
MIL–STD–1797A
CONTENTS – Continued
Paragraph
Page
4.2.7
4.2.7.1
4.2.7.2
4.2.7.2.1
4.2.7.3
4.2.7.4
4.2.8
4.2.8.1
4.2.8.2
4.2.8.3
4.2.8.4
4.2.8.5
4.2.8.6
4.2.8.6.1
4.2.8.6.2
4.2.8.6.3
4.2.8.6.4
4.2.8.6.5
4.2.8.6.6
4.2.8.7
4.2.9
4.2.9.1
4.2.9.2
4.3
4.3.1
4.3.1.1
4.3.1.2
4.3.2
4.3.3
4.3.3.1
4.3.3.2
4.3.4
4.4
4.4.1
4.4.1.1
4.5
4.5.1
4.5.1.1
4.5.1.2
4.5.1.3
4.5.1.4
4.5.1.5
4.5.2
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Pitch axis control power
Pitch axis control power in unaccelerated flight
Pitch axis control power in maneuvering flight
Load factor response
Pitch axis control power in takeoff
Pitch axis control power in landing
Pitch axis control forces
Pitch axis control forces––steady–state control force per g
Pitch axis control forces––transient control force per g
Pitch axis control forces––control force variations during
rapid speed changes
Pitch axis control forces––control force vs. control deflection
Pitch axis control breakout forces
Pitch axis control force limits
Pitch axis control force limits––takeoff
Pitch axis control force limits––landing
Pitch axis control force limits––dives
Pitch axis control force limits––sideslips
Pitch axis control force limits––failures
Pitch axis control force limits––control mode change
Pitch axis trim systems
Pitch axis control displacements
Pitch axis control displacement––takeoff
Pitch axis control displacement––maneuvering
Flying qualities requirements for the normal (flight path) axis
Flight path response to attitude change
Transient flight path response to attitude change
Steady–state flight path response to attitude change
Flight path response to designated flight path controller
Flight path control power
Control power for designated primary flight path controller
Control power for designated secondary flight path controller
Flight path controller characteristics
Flying qualities requirements for the longitudinal (speed) axis
Speed response to attitude changes
Speed response to attitude changes–relaxation in transonic flight
Flying qualities requirements for the roll axis
Roll response to roll controller
Roll mode
Spiral stability
Coupled roll–spiral oscillation
Roll oscillations
Roll time delay
Pilot–induced roll oscillations
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30
31
31
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32
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vi
MIL–STD–1797A
CONTENTS – Continued
Paragraph
Page
4.5.3
4.5.4
4.5.5
4.5.6
4.5.7
4.5.7.1
4.5.7.2
4.5.8
4.5.8.1
4.5.8.2
4.5.8.3
4.5.8.4
4.5.8.5
4.5.8.6
4.5.9
4.5.9.1
4.5.9.2
4.5.9.3
4.5.9.4
4.5.9.5
4.5.9.5.1
4.5.9.5.2
4.5.9.5.3
4.5.9.5.4
4.5.9.5.5
4.5.9.5.6
4.5.9.5.7
4.6
4.6.1
4.6.1.1
4.6.1.2
4.6.1.3
4.6.2
4.6.3
4.6.4
4.6.5
4.6.5.1
4.6.5.2
4.6.5.3
4.6.6
4.6.6.1
4.6.6.2
4.6.6.3
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34
34
34
34
34
34
34
34
35
35
35
35
35
35
35
35
36
36
36
36
36
36
36
36
36
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Linearity of roll response to roll controller
Lateral acceleration at the pilot stations
Roll characteristics in steady sideslip
Roll axis control for takeoff and landing in crosswinds
Roll axis response to other inputs
Roll axis response to augmentation failures
Roll axis response to configuration or control mode change
Roll axis control power
Roll axis response to roll control inputs
Roll axis control power in steady sideslips
Roll axis control power in crosswinds
Roll axis control power for asymmetric thrust
Roll axis control power in dives and pullouts
Roll axis control power for asymmetric loading
Roll axis control forces and displacements
Roll control displacements
Roll axis control forces to achieve required roll performance
Roll axis control sensitivity
Roll axis control centering and breakout forces
Roll axis control force limits
Roll axis control force limits in steady turns
Roll axis control force limits in dives and pullouts
Roll axis control force limits in crosswinds
Roll axis control force limits in steady sideslips
Roll axis control force limits for asymmetric thrust
Roll axis control force limits for failures
Roll axis control force limits for configuration or control
mode change
Flying qualities requirements for the yaw axis
Yaw axis response to yaw and side–force controllers
Dynamic lateral–directional response
Steady sideslips
Wings–level turn
Yaw axis response to roll controller
Pilot–induced yaw oscillations
Yaw axis control for takeoff and landing in crosswinds
Yaw axis response to other inputs
Yaw axis response to asymmetric thrust
Yaw axis response to failures
Yaw axis response to configuration or control mode change
Yaw axis control power
Yaw axis control power for takeoff, landing, and taxi
Yaw axis control power for asymmetric thrust
Yaw axis control power with asymmetric loading
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vii
MIL–STD–1797A
CONTENTS – Continued
Paragraph
Page
4.6.7
4.6.7.1
4.6.7.2
4.6.7.3
4.6.7.4
4.6.7.5
4.6.7.6
4.6.7.7
4.6.7.8
4.6.7.9
4.6.7.10
4.6.7.11
4.7
4.7.1
4.8
4.8.1
4.8.2
4.8.3
4.8.4
4.8.4.1
4.8.4.2
4.8.4.2.1
4.8.4.2.2
4.8.4.2.3
4.8.4.2.4
4.8.4.3
4.8.4.3.1
4.8.4.3.2
4.9
4.9.1
4.9.2
4.9.3
5.
5.1
5.1.1
5.1.2
5.1.3
5.1.4
5.1.4.1
5.1.4.2
5.1.4.3
5.1.5
5.1.6
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39
Yaw axis control forces
39
Yaw axis control force limits in rolling maneuvers
39
Yaw axis control force limits in steady turns
39
Yaw axis control force limits during speed changes
39
Yaw axis control force limits in crosswinds
39
Yaw axis control force limits with asymmetric loading
40
Yaw axis control force limits in dives and pullouts
40
Yaw axis control force limits for waveoff (go–around)
40
Yaw axis control force limits for asymmetric thrust during takeoff
40
Yaw axis control force limits with flight control failures
40
Yaw axis control force limits––control mode change
40
Yaw axis breakout forces
40
Flying qualities requirements for the lateral flight path axis
40
Dynamic response for lateral translation
41
Flying qualities requirements for combined axes
41
Cross–axis coupling in roll maneuvers
41
Crosstalk between pitch and roll controllers
41
Control harmony
41
Flight at high angle of attack
41
Warning cues
41
Stalls
41
Stall approach
41
Stall characteristics
42
Stall prevention and recovery
42
One–engine–out stalls
42
Post–stall gyrations and spins
42
Departure from controlled flight
42
Recovery from post–stall gyrations and spins
Flying qualities requirements in atmospheric disturbances
43
Allowable flying qualities degradations in atmospheric disturbances 43.
44
Definition of atmospheric disturbance model form
Application of disturbance models in analyses
44
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VERIFICATION
General requirements—verification
Loadings—verification
Moments and products of inertia—verification
Internal and external stores—verification
Flight Envelopes—verification
Operational Flight Envelopes—verification
Service Flight Envelopes—verification
Permissible Flight Envelopes—verification
Configurations and States of the aircraft—verification
Aircraft Normal States—verification
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viii
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