ISO 1151-8:2022

INTERNATIONAL ISO
STANDARD 1151-8
Second edition
2022-11
Flight dynamics — Vocabulary —
Part 8:
Dynamic behaviour of aircraft
Reference number
© ISO 2022
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Contents Page
Foreword .iv
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
3.1 General . 1
3.2 Types of aircraft motion . 2
3.3 Types of aircraft motion and natural modes of aircraft motion . 4
3.4 Characteristic parameters of individual modes of motion . 5
3.5 Standard input signals . 7
3.6 Response of aircraft to a step . 11
Bibliography .15
Index .16
iii
Foreword
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This document was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles,
Subcommittee SC 8, Aerospace terminology.
This second edition cancels and replaces the first edition (ISO 1151-8:1992), which has been technically
revised.
The main changes are as follows:
— new terms related to types of aircraft motion have been added.
A list of all parts in the ISO 1151 series can be found on the ISO website.
Any feedback or questions on this document should be directed to the user’s national standards body. A
complete listing of these bodies can be found at www.iso.org/members.html.
iv
INTERNATIONAL STANDARD ISO 1151-8:2022(E)
Flight dynamics — Vocabulary —
Part 8:
Dynamic behaviour of aircraft
1 Scope
This document defines terms related to the concepts and quantities characterizing some classes of
aircraft motion and their fundamental dynamic characteristics.
The aircraft is assumed to be rigid, of constant mass and of constant inertia. It is not equipped with
systems modifying its natural dynamic behaviour. However, most of the definitions can be applied to
the case of a flexible aircraft, of variable mass and of variable inertia.
The general concepts defined in this document are applicable to the atmospheric flight phase.
2 Normative references
There are no normative references in this document.
3 Terms and definitions
ISO and IEC maintain terminology databases for use in standardization at the following addresses:
— ISO Online browsing platform: available at https:// www .iso .org/ obp
— IEC Electropedia: available at https:// www .electropedia .org/
3.1 General
3.1.1
flight variable
physical quantity, the value of which as a function of time characterizes aircraft motion
3.1.2
flight state
set of values of the flight variables (3.1.1)
Note 1 to entry: This concept should not be confused with that of flight point (ISO 1151-7:1985, 7.5.5).
3.1.3
steady flight state
flight state (3.1.2) in which the flight variables (3.1.1) considered remain constant with time
3.1.4
quasi-steady flight state
flight state (3.1.2) in which the flight variables (3.1.1) considered vary so slowly with time that their
variations can be disregarded in the study
3.1.5
unsteady flight state
flight state (3.1.2) in which at least one of the flight variables (3.1.1) considered varies so rapidly with
time that its variations cannot be disregarded in the study
3.1.6
reference flight state
flight state (3.1.2) chosen as reference in a given study
Note 1 to entry: In most cases, a steady flight state (3.1.3) or a quasi-steady flight state (3.1.4) is chosen as
reference.
Note 2 to entry: In a study covering a certain period of time, it is normal to choose the flight state immediately
prior to this period as a reference.
3.1.7
control input
action on aircraft intended to alter or to maintain the flight state (3.1.2)
3.1.8
disturbance
involuntary action which results in a modification in the flight state (3.1.2)
Note 1 to entry: The nature of this action can be, for example:
— human;
— atmospheric;
— mechanical.
3.1.9
input variable
element of the set of quantities characterizing the control input (3.1.7) or disturbance (3.1.8)
3.1.10
output variable
element of the set of flight variables (3.1.1), the developments of which over time characterize the
response of aircraft to the control input (3.1.7) or disturbance (3.1.8) considered
3.2 Types of aircraft motion
3.2.1
flight-path
trajectory
three-dimensional locus of origin of the flight-path axis system, usually the centre of mass, relative to
the Earth
3.2.2
aircraft plane motion
motion of aircraft characterized by a flight-path (3.2.1) contained within a plane
3.2.3
straight flight
aircraft plane motion (3.2.2) characterized by a straight flight-path (3.2.1)
3.2.4
horizontal flight
aircraft plane motion (3.2.2) characterized by a flight-path (3.2.1) contained within a horizontal plane
3.2.5
symmetrical flight
flight state (3.1.2) of aircraft with zero angle of sideslip
Note 1 to entry: The angle of sideslip is defined in ISO 1151-1:1988, 1.2.1.1.
Note 2 to entry: The geometry of aircraft and the flow are not necessarily symmetrical.
3.2.6
turn
motion of aircraft resulting in a change of flight-path (3.2.1) azimuth angle
Note 1 to entry: The flight-path azimuth angle is defined in ISO 1151-2:1985, 2.3.1.
3.2.7
horizontal turn
turn (3.2.6) in horizontal flight (3.2.4)
3.2.8
steady turn
horizontal turn (3.2.7) for which the airspeed and the load factor are held constant
Note 1 to entry: If the wind speed, V (ISO 1151-2:1985, 2.2.3), is zero, the flight-path (3.2.1) is circular.
w
3.2.9
longitudinal motion
isolated longitudinal motion
motion characterized by variations of flight variables (3.1.1), related to the three degrees of freedom in
the aircraft plane of symmetry
Note 1 to entry: Longitudinal motion is characterized by variations in relation to a reference flight state (3.1.6) of
— angle of attack, α (ISO 1151-1:1988, 1.2.1.2),
— inclination angle, Θ (ISO 1151-1:1988, 1.2.2.2),
— airspeed, V (ISO 1151-1:1988, 1.3.1),
— flight-path (3.2.1) inclination angle, γ (ISO 1151-2:1985, 2.3.2), and
— rate of pitch, q (ISO 1151-1:1988, 1.3.6),
while the variations of
— angle of sideslip, β (ISO 1151-1:1988, 1.2.1.1),
— rate of roll, p (ISO 1151-1:1988, 1.3.6), and
— rate of yaw, r (ISO 1151-1:1988, 1.3.6)
are zero or negligible.
3.2.10
lateral motion
isolated lateral motion
motion characterized by variations of flight variables (3.1.1), related to the three degrees of freedom
outside of the aircraft plane of symmetry
Note 1 to entry: Lateral motion is characterized by variations in relation to a reference flight state (3.1.6) of
— angle of sideslip, β (ISO 1151-1:1988, 1.2.1.1),
— bank angle, Φ (ISO 1151-1:1988, 1.2.2.3),
— azimuth angle, Ψ (ISO 1151-1:1988, 1.2.2.1),
— rate of roll, p (ISO 1151-1:1988, 1.3.6), and
— rate of yaw, r (ISO 1151-1:1988, 1.3.6),
while the variations of
— angle of attack, α (ISO 1151-1:1988, 1.2.1.2),
— airspeed, V (ISO 1151-1:1988, 1.3.1),
— flight-path (3.2.1) inclination angle, γ (ISO 1151-2:1985, 2.3.2), and
— rate of pitch, q (ISO 1151-1:1988, 1.3.6)
are zero or negligible.
3.2.11
aerodynamic stall
aerodynamic loss of lift caused by the angle of attack, α, exceeding its critical value
Note 1 to entry: The angle of attack, α, is defined in ISO 1151-1:1988, 1.2.1.2.
3.2.12
aeroplane upset
flight state (3.1.2) characterized by aircraft flight variables (3.1.1) unintentionally exceeding their limits
normally experienced in line operations or training
Note 1 to entry: Aeroplane upset is normally defined by the existence of at least one of the following parameters:
a) inclination angle, Θ (ISO 1151-1:1988, 1.2.2.2) (pitch attitude), greater than 25°, nose up;
b) inclination angle, Θ (ISO 1151-1:1988, 1.2.2.2) (pitch attitude), less than −10°, nose down;
c) absolute value of bank angle, Φ (ISO 1151-1:1988, 1.2.2.3), greater than 45°;
d) within the above parameters, but flying at airspeed, V (ISO 1151-1:1988, 1.3.1), inappropriate for the
conditions.
3.3 Types of aircraft motion and natural modes of aircraft motion
3.3.1
short period oscillation
oscillatory longitudinal motion characterized by variations in the angle of attack, α, and the rate of
pitch, q, at a nearly constant airspeed, V, with a frequency, f, higher than that of the phugoid (3.3.2) mode
Note 1 to entry: The angle of attack, α, is defined in ISO 1151-1:1988, 1.2.1.2. The rate of pitch, q, is defined in
ISO 1151-1:1988, 1.3.6. The airspeed, V, is defined in ISO 1151-1:1988, 1.3.1.
Note 2 to entry: The damping coefficient, δ (3.4.2), of short period oscillation is generally large.
Note 3 to entry: The modes considered correspond to small motions superimposed on a steady or quasi-steady
reference flight state. These are motions of aircraft following a control input or disturbance.
3.3.2
phugoid
phugoid oscillation
oscillatory longitudinal motion (3.2.9) characterized by variations in the horizontal and vertical

components of the aircraft velocity, V , and the inclination angle, Θ, of the aircraft, at a nearly constant
angle of attack, α

Note 1 to entry: The aircraft velocity, V , is defined in ISO 1151-1:1988, 1.3.1. The inclination angle, Θ, is defined
in ISO 1151-1:1988, 1.2.2.2. The angle of attack, α, is defined in ISO 1151-1:1988, 1.2.1.2.
Note 2 to entry: The frequency, f, and the damping coefficient, δ (3.4.2), are generally low.
Note 3 to entry: The modes considered correspond to small motions superimposed on a steady or quasi-steady
reference flight state. These are motions of aircraft
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