CN112651556A - Airplane deviation characteristic prediction method with control system - Google Patents

Airplane deviation characteristic prediction method with control system Download PDF

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CN112651556A
CN112651556A CN202011566306.5A CN202011566306A CN112651556A CN 112651556 A CN112651556 A CN 112651556A CN 202011566306 A CN202011566306 A CN 202011566306A CN 112651556 A CN112651556 A CN 112651556A
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deviation
control
lateral
control system
criterion
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张秀林
曲晓雷
王业光
赵滨
张杨
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Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
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Abstract

The application provides an aircraft deviation characteristic prediction method with a control system, which comprises the following steps: establishing an airplane deviation prediction criterion according to a deviated motion mechanism, a system stability theory of an airplane dynamic equation and a flight control system principle, wherein the airplane deviation prediction criterion comprises a dynamic yaw divergence parameter criterion and a lateral operation deviation parameter criterion; coupling the control influence of lateral heading stability augmentation, lateral heading cross-linking coupling and multi-control-surface control distribution strategies in a flight control system into an airplane deviation prediction criterion; and carrying out deviation characteristic prediction evaluation by utilizing the coupled airplane deviation characteristic prediction criterion with the control system. The method provided by the application expands the course stability augmentation, the lateral course cross-linking coupling and the multi-control distribution strategy in the flight control law into the aircraft deviation characteristic criterion, provides a technical basis for the aircraft large-attack-angle control strategy by introducing the analytical relationship between the deviation criterion and the control system, effectively ensures the aircraft safety and reduces the risk.

Description

Airplane deviation characteristic prediction method with control system
Technical Field
The application belongs to the technical field of flight control, and particularly relates to an aircraft deviation characteristic prediction method with a control system.
Background
The flight dynamics of the airplane with the flight control system in the deviation area have important significance for ensuring the flight safety of the airplane under a large attack angle. Currently, the study of multiple flight dynamics equations based on the linearization of a conventional aircraft on the basis of the deviation characteristic of an aircraft (deviation characteristic means that when the aircraft is flying at a large angle of attack, it has an action or tendency to fly off sideways, which is undesirable) is proposed to be insufficiently suitable for multi-control surface modern aircraft employing flight control systems.
Disclosure of Invention
It is an object of the present application to provide a method of predicting deviation characteristics of an aircraft with a control system to address or mitigate at least one of the problems of the background art.
The technical scheme of the application is as follows: a method of predicting deviation characteristics of an aircraft having a control system, the method comprising:
establishing an airplane deviation prediction criterion according to a deviated motion mechanism, a system stability theory of an airplane dynamic equation and a flight control system principle, wherein the airplane deviation prediction criterion comprises a dynamic yaw divergence parameter criterion and a lateral operation deviation parameter criterion;
coupling the control influence of lateral heading stability augmentation, lateral heading cross-linking coupling and multi-control-surface control distribution strategies in a flight control system into an airplane deviation prediction criterion;
and carrying out deviation characteristic prediction evaluation by utilizing the coupled airplane deviation characteristic prediction criterion with the control system.
Further, in the coupling of the control influence including lateral direction stability augmentation, lateral direction cross-linking coupling and/or multi-control surface control distribution strategy and lateral side control deviation parameter criterion, the dynamic yaw divergence parameter criterion is as follows:
Figure BDA0002860774020000021
in the formula, Cnβ、C1βRespectively representing the heading static stability derivative, alpha is an angle of attack, IZFor aircraft to body axis ztMoment of inertia, IXFor aircraft to body axis xtMoment of inertia.
Further, the prediction formula of the coupling of the control influence comprising the lateral stability augmentation, the lateral cross-linking coupling and/or the multi-control surface control distribution strategy and the lateral deviation control parameter criterion is as follows:
Figure BDA0002860774020000022
of formula (II) to C'nβ、C’1βRespectively, the extended heading static stability derivatives.
Further, a heading static stability derivative C 'of expansion'nβ、C’1βRespectively as follows:
Figure BDA0002860774020000023
Figure BDA0002860774020000024
in the formula, Cn(β)、Cl(beta) yaw and roll moment coefficients due to the control of control plane deflection by the flight control system; beta is a generalized control plane containing differential ailerons, differential horizontal tails and rudder skewness.
Further, the prediction formula of the coupling of the control influence comprising the lateral stability augmentation, the lateral cross-linking coupling and/or the multi-control surface control distribution strategy and the lateral deviation control parameter criterion is as follows:
Figure BDA0002860774020000025
the aircraft deviation characteristic prediction method with the control system can be used for predicting the large-attack-angle deviation characteristic and the tail-spin sensitivity of a modern aircraft, the course stability augmentation, the lateral course cross-linking coupling and the multi-control distribution strategy in the flight control law are expanded into the aircraft deviation characteristic criterion, the analytical relation between the deviation criterion and the control system characteristic is introduced, a technical basis is provided for the aircraft large-attack-angle control strategy, the aircraft safety is effectively guaranteed, and the risk is reduced.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a flowchart of a method for predicting deviation characteristics of an aircraft with a control system according to the present application.
FIG. 2 is a graph of dynamic yaw divergence parameters versus angle of attack for a controlled system and an uncontrolled system in an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
As shown in fig. 1, the present application provides a method for predicting deviation characteristics of an aircraft with a control system, the method comprising:
s1, establishing an airplane deviation prediction criterion according to a deviation motion mechanism, a system stability theory of an airplane dynamic equation and a flight control system principle, wherein the airplane deviation prediction criterion comprises a dynamic yaw divergence parameter criterion and a lateral operation deviation parameter criterion;
s2, coupling the control influence of lateral heading stability augmentation, lateral heading cross-linking coupling and multi-control-surface control distribution strategies in the flight control system into an airplane deviation prediction criterion;
and S3, utilizing the coupled airplane deviation characteristic prediction criterion with the control system to carry out deviation characteristic prediction evaluation.
In the coupled embodiment of the dynamic yaw divergence parameter criterion of the application combined with a flight control system comprising lateral course stability augmentation, lateral course cross-linking coupling and multi-control surface control distribution strategies, firstly, the aircraft dynamic yaw divergence parameter criterion is established:
Figure BDA0002860774020000031
in the formula, Cnβ、ClβRespectively representing heading static stability derivatives;
then, considering the aircraft lateral course control input and control law stability augmentation design, C is expandednβdynThe parameters define the final prediction formula:
Figure BDA0002860774020000041
Figure BDA0002860774020000042
Figure BDA0002860774020000043
in the formula, Cn(δ)、Cl(δ) is the yaw and roll moment coefficients due to the flight control system controlling the control plane deflections. The generalized control plane δ here includes differential ailerons, differential horizontal tails, rudder skewness, etc.
For example: the course adopts the lateral overload feedback stability-increasing control condition, and the feedback gain from the lateral overload to the rudder is assumed to be
Figure BDA0002860774020000044
(negative), the governing law equation is:
Figure BDA0002860774020000045
considering the equivalent conversion relationship between lateral overload and lateral slip angle:
Figure BDA0002860774020000046
generalized yaw static stability derivative C'nβIs calculated as follows
Figure BDA0002860774020000047
Similarly, there are:
Figure BDA0002860774020000051
and finally, carrying out evaluation by using the corrected airplane deviation characteristic prediction method with the control system.
The evaluation result of this embodiment is shown in fig. 2, and it can be seen from fig. 2 that the deviation characteristic of the aircraft with the control system is more stable.
In another cross-side maneuver biasing parameter (LCDP) criterion in conjunction with flight control system coupled embodiments including lateral stability augmentation, lateral cross-coupling, multi-control surface control distribution strategies of the present application,
according to the steps in the first embodiment, functions of navigation stability augmentation, lateral cross-linking coupling, multi-control distribution strategy and the like in modern advanced aircraft control are considered for lateral deviation control parameter criteria, for example, modern fighters are generally configured with multiple groups of rolling control surfaces, such as differential ailerons, differential horizontal tails and the like. Carrying out formula expansion on the LCDP criterion, wherein the final prediction formula is as follows:
Figure BDA0002860774020000052
KARIto introduce aileron-rudder crosslinking gain, KDHRepresenting the ratio of differential horizontal tail deflection to aileron deflection for the same beam input command, Δ δdh＝KDHΔδa。
TABLE 1 dimension-derivative
Figure BDA0002860774020000053
Figure BDA0002860774020000061
TABLE 2 legends
Symbol Definition of
Iz Aircraft to body axis ztMoment of inertia
Ix Aircraft body axis xtMoment of inertia
α Angle of attack
δr Steering angle
ny Lateral overload
Cl Coefficient of roll moment
Cn Yaw moment coefficient
Cy Coefficient of lateral force
qD Quick press
S Wing area
m Mass of aircraft
g Acceleration of gravity
β Sideslip angle
δa Aileron deflection angle
The advanced aircraft deviation characteristic prediction method with the flight control system is used for predicting the large-attack-angle deviation characteristic and the tail-spin sensitivity of a modern aircraft, course stability augmentation, lateral course cross-linking coupling and multi-control distribution strategies in the flight control law are expanded into aircraft deviation characteristic criteria, and by introducing the analytical relation between the deviation criteria and the characteristics of the control system, a technical basis is provided for the aircraft large-attack-angle control strategy, the safety of the aircraft is effectively guaranteed, and the risk is reduced. 4 combined criteria are applied to predict the deviation characteristic of the airplane, so that the limitation of a single criterion is avoided; establishing a specific analytical relationship between the airplane deviation criterion and the characteristics of the control system, so that the theoretical guiding significance of the criterion is more definite, and the design of a deviation-preventing control law of a modern airplane control system is facilitated; the method couples control influences such as lateral course stability augmentation, lateral course cross-linking coupling and multi-control-surface control distribution strategies in the flight control law into the prediction criterion, is suitable for deviation characteristic prediction of the multi-control-surface modern aircraft adopting the flight control system, and has wide application range.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (5)

1. A method for predicting deviation characteristics of an aircraft having a control system, the method comprising:
establishing an airplane deviation prediction criterion according to a deviated motion mechanism, a system stability theory of an airplane dynamic equation and a flight control system principle, wherein the airplane deviation prediction criterion comprises a dynamic yaw divergence parameter criterion and a lateral operation deviation parameter criterion;
coupling the control influence of lateral heading stability augmentation, lateral heading cross-linking coupling and multi-control-surface control distribution strategies in a flight control system into an airplane deviation prediction criterion;
and carrying out deviation characteristic prediction evaluation by utilizing the coupled airplane deviation characteristic prediction criterion with the control system.
2. The method of predicting aircraft departure characteristics with a control system as claimed in claim 1 wherein the control impacts comprising lateral stability augmentation, lateral cross-linking coupling and/or multi-control surface control allocation strategy are coupled to lateral deviation from maneuver parameter criteria, said dynamic yaw divergence parameter criteria being:
Figure FDA0002860774010000011
in the formula, Cnβ、C1βRespectively representing the heading static stability derivative, alpha is an angle of attack, IZFor aircraft to body axis ztMoment of inertia, IXFor aircraft to body axis xtMoment of inertia.
3. The method of predicting aircraft deviation characteristics with a control system of claim 2, wherein the predictive formula coupling the control impact comprising lateral stability augmentation, lateral cross-linking coupling and/or multi-control surface control allocation strategy to the lateral deviation maneuver parameter criteria is:
Figure FDA0002860774010000012
of formula (II) to C'nβ、C’1βRespectively, the extended heading static stability derivatives.
4. An aircraft departure characteristic prediction method according to claim 3 and wherein the developed heading static stability derivative C'nβ、C’1βRespectively as follows:
Figure FDA0002860774010000021
Figure FDA0002860774010000022
in the formula, Cn(β)、Cl(beta) yaw and roll moment coefficients due to the control of control plane deflection by the flight control system; beta is a generalized control plane containing differential ailerons, differential horizontal tails and rudder skewness.
5. The method of predicting aircraft deviation characteristics with a control system of claim 4, wherein the predictive formula coupling the control impact comprising lateral stability augmentation, lateral cross-linking coupling and/or multi-control surface control allocation strategy to the lateral deviation maneuver parameter criteria is:
Figure FDA0002860774010000023
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