CN118817232B - An experimental method for obtaining dynamic derivatives of aircraft using large amplitude rotational motion - Google Patents
An experimental method for obtaining dynamic derivatives of aircraft using large amplitude rotational motion Download PDFInfo
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
本发明公开了一种大振幅旋转运动获取飞行器动导数的试验方法，涉及航空技术领域中风洞试验技术领域，包括：在模型上通过布置加速度计构建加速度阵列；通过标定获取加速度阵列输出与惯性力的映射关系；基于加速度阵列和应变天平计算扣除惯性力影响的动态气动力；基于加速度阵列，通过积分获取模型速度信息的交流量；除速度为零的角度附近外，基于运动过程中每个角度对应正向运动行程的点速度和动态气动力矩分量，以及负向运动行程的点速度和动态气动力矩分量计算得到俯仰动导数。本发明提供一种大振幅旋转运动获取飞行器动导数的试验方法，既可以适用于线性条件下获取动导数，也可以获取非线性条件下的动导数。
The present invention discloses an experimental method for obtaining aircraft dynamic derivatives by large-amplitude rotational motion, which relates to the field of wind tunnel test technology in the field of aviation technology, including: constructing an acceleration array by arranging accelerometers on a model; obtaining the mapping relationship between the acceleration array output and the inertial force by calibration; calculating the dynamic aerodynamic force deducted from the influence of the inertial force based on the acceleration array and the strain balance; obtaining the exchange quantity of the model velocity information by integration based on the acceleration array; and calculating the pitch dynamic derivative based on the point velocity and dynamic aerodynamic torque component corresponding to the positive motion stroke of each angle in the motion process, except near the angle where the velocity is zero, and the point velocity and dynamic aerodynamic torque component corresponding to the negative motion stroke. The present invention provides an experimental method for obtaining aircraft dynamic derivatives by large-amplitude rotational motion, which can be applied to obtaining dynamic derivatives under linear conditions and can also be applied to obtaining dynamic derivatives under nonlinear conditions.
Description
Technical Field
The invention relates to the technical field of wind tunnel tests in the technical field of aviation. More particularly, the invention relates to a test method for acquiring the dynamic derivative of an aircraft by using large-amplitude rotary motion.
Background
In the development of aircraft control systems, the dynamic derivative is an important design criterion. The current common method is to use small amplitude motion and obtain the dynamic derivative according to the relation between aerodynamic force and the amplitude and phase of the motion. The problems existing in the method at present mainly comprise two:
One is that the method is based on a linear assumption, i.e. aerodynamic forces equal to static aerodynamic forces plus derivatives times the movement (angular) velocity, and it is generally considered that the assumption is fulfilled when no separation of the aircraft flows occurs, and whether the assumption is fulfilled after the separation of the aircraft flows has occurred is not yet fully proven.
Secondly, in the process of maneuvering the aircraft at a large attack angle, the dynamic derivative may be related to the movement process, but the existing method cannot simulate the movement process. Strictly speaking, the dynamic derivative concept does not exist when aerodynamic forces do not meet the linear assumption or relate to the course of motion, but engineering is customary to approximate dynamic aerodynamic forces by multiplying the dynamic derivative by static aerodynamic forces and the motion (angular) velocity, where the dynamic derivative is the equivalent dynamic derivative. In view of engineering practices and brevity of expression, dynamic derivatives hereinafter refer to conventional dynamic derivatives and equivalent approximate dynamic derivatives.
Disclosure of Invention
It is an object of the present invention to address at least the above problems and/or disadvantages and to provide at least the advantages described below.
To achieve these objects and other advantages and in accordance with the purpose of the invention, a method for testing a large amplitude rotary motion to obtain a dynamic derivative of an aircraft is provided, comprising:
S1, constructing an acceleration array on a model by arranging accelerometers, wherein the accelerometer arrangement satisfies that accelerometer output vectors corresponding to any uncorrelated inertial force are uncorrelated;
s2, acquiring acceleration array output A and inertial force through calibration Mapping relation of (2)Wherein f () represents a mapping function of the acceleration array output to the inertial force;
s3, calculating dynamic aerodynamic force deducting the influence of the inertia force based on the acceleration array and the strain balance;
s4, acquiring a model speed through integration based on the acceleration array;
S5, except for the vicinity of the angle with zero speed, the point speed and dynamic aerodynamic moment component of the forward motion stroke corresponding to each angle in the motion process are recorded as AndThe point speed and dynamic aerodynamic moment component of each angle corresponding to the negative movement travel in the movement process are recorded asAndTo obtain the pitching derivative based on the following formula:
S6, repeating the steps S3-S5 for calculating corresponding dynamic derivatives for different test states.
Preferably, in S1, the dynamic aerodynamic force obtaining manner includes:
S10, acquiring moment of inertia about moment reference points in a plane corresponding to a dynamic derivative of the model through three-dimensional design software or theoretical calculation ;
S11, under the condition of stable wind tunnel flow field, the control model performs large-amplitude motion on a plane corresponding to the dynamic derivative, so that balance and acceleration array data are synchronously acquired through synchronous acquisition equipment, and a balance measured value is calculated,;
S12, calculating dynamic aerodynamic force for deducting influence of inertia force based on the following formula:
。
Preferably, in S4, the speed obtaining manner includes:
S20, calculating and obtaining rotation angular acceleration based on the following formula :
In the above-mentioned method, the step of,For the moment of inertia component of the dynamic derivative corresponding to the plane rotation,Moment of inertia about a moment reference point in a plane corresponding to the dynamic derivative;
S21, pair Integrating to obtain angular velocity;
S22, respectively matching high-pass filters with the same parametersAerodynamic moment component of rotation of plane corresponding to dynamic derivativeHigh pass filtering is performed and the filter cutoff frequency should be lower than the model motion frequency.
The invention at least comprises the following beneficial effects:
Firstly, the invention does not require linear assumption, and can be suitable for acquiring the dynamic derivative under the linear condition or acquiring the dynamic derivative under the nonlinear condition;
secondly, the invention can simulate the maneuvering process of the aircraft and acquire the dynamic derivative related to the movement process;
thirdly, the invention does not need to deduct the ground dynamic derivative, and does not have systematic errors caused by corresponding operation.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Drawings
FIG. 1 is a flow chart of a test method for obtaining the dynamic derivative of an aircraft by large amplitude rotary motion according to the present invention.
Detailed Description
The present invention is described in further detail below with reference to the drawings to enable those skilled in the art to practice the invention by referring to the description.
The invention discloses a test method for acquiring a dynamic derivative of an aircraft by large-amplitude rotary motion, which does not require linear assumption, and can be suitable for acquiring the dynamic derivative under a linear condition and acquiring an equivalent dynamic derivative under a nonlinear condition. For engineering purposes, the dynamic derivative under nonlinear conditions may be expressed in the form of a dynamic derivative, but not in the strict sense. Under nonlinear conditions, the maneuvering process of the aircraft can be simulated, and the dynamic derivative which is as close to the flight condition as possible is obtained, so that a reference is provided for the design of an aircraft control system.
Specifically, for ease of description, it is assumed that there is a pilot in the model, and left-right, front-back, up-down, and up-down are determined with the direction of the pilot in the assumed model, unless explicitly stated otherwise. For pitching movement, the positive direction of pitching movement is defined when the test model moves to the head, for yawing movement, the positive direction of yawing movement is defined when the test model nose moves to the left, and for rolling movement, the positive direction of rolling movement is defined when the wing on the right side of the test model moves downwards, and the positive direction of moment is defined as the same as the positive direction of movement. When force or moment is involved, it is assumed that it has the same coordinate system and moment reference point. In the test, the model is moved in only one plane, e.g., translated and rotated in the pitch plane.
The key points of the invention are that one of the two points is to deduct the influence of inertia force by using an acceleration array (an array consisting of accelerometers) to obtain high-precision dynamic aerodynamic force with the bandwidth of 10-30 times that of an independent strain balance force measuring system, and the other is to obtain the alternating flow of model speed or angular speed (hereinafter referred to as speed uniformly) information by using the same acceleration array through integration. The reason for the need of subtracting the inertial force by using the acceleration array is that the traditional method for subtracting the influence of the inertial force by using the windy subtracting windless method has lower precision. The reason for using the same acceleration array to measure the speed is that the speed measurement needs high enough bandwidth and phase precision, and the effect of the two conventional methods is not ideal. Two methods are commonly used, the first is mechanical measurement, using encoders or strain gauges on the mechanism, and the second is measurement using gyroscopes. The first method is affected by the elasticity of the support structure, the phase and the accuracy are difficult to meet the requirements of the invention, the second method is affected by the state of the art, and the gyroscope measurement bandwidth and phase are generally not capable of meeting the requirements of the invention.
The method for deducting the influence of inertia force by using the acceleration array is disclosed in the patent of the invention named as a measuring method and a measuring system (ZL 201710206338.6) of multi-component force and moment, and the patent of the invention is published by the team of the inventor of the invention. For convenience of description, a formula for subtracting the influence of inertial force by using the acceleration array is defined as follows:
wherein, In order to subtract the dynamic aerodynamic force after the influence of the inertial force,Force vector applied to the model for the balance (thenEqual to the balance measurement),In the form of an inertial force,Derived from the acceleration array. Gravity, which is an easily deducted disturbance, is omitted here for simplicity of description.
Angular acceleration can be obtained from the inertial force and moment of inertia, and the angular velocity can be obtained by integration.
At vectorSelecting moment components corresponding to the rotation of the motion planeThe calculation formula of the model angular acceleration is:
wherein, The moment of inertia of the model about a moment reference point is represented by a subscript i in a formula, i=x, y and z respectively represent yz, xz and xy planes, namely the values of i are different for different dynamic derivatives, and the values are the same.
For a pair ofIntegrating to obtain the rotation angular velocity of the model. Dynamic aerodynamic force vector after subtracting inertial force influenceSelecting moment components corresponding to the rotation of the motion plane. For a pair ofAndThe filtering is performed using a high pass filter of the same parameters, the high pass filter cut-off frequency should be lower than the model motion frequency. For each angle in the movement process, the data point speed and dynamic aerodynamic moment corresponding to the forward movement travel are recorded asAndThe data point speed and dynamic aerodynamic moment corresponding to the negative movement travel are recorded asAndThe calculation formula of the dynamic derivative of the corresponding in-plane rotation is:
the dimensionless dynamic derivative can be obtained after dimensionless. The dynamic derivative of most angles in the range of motion can be obtained except near the region on the track where the speed is 0.
As shown in fig. 1, for large amplitude motion in a certain motion plane, the acquisition of the corresponding motion derivative may be performed as follows:
arranging an acceleration array on the model, calculating by using single-axis acceleration components, and arranging at least 6 accelerometers, wherein the accelerometer output vectors corresponding to any uncorrelated inertial force are uncorrelated.
Step two, obtaining the output A of the acceleration array to the inertial force through calibrationMapping relation of (2). Acquiring moment of inertia about moment reference points in a motion plane corresponding to a model through three-dimensional design software or theoretical calculation。
And thirdly, enabling the model to move in a large amplitude on a corresponding dynamic derivative plane under the condition of stable flow field of the wind tunnel, and synchronously collecting balance and acceleration array data through synchronous collecting equipment.
Step four, calculating the balance measured valueCalculating inertial force from acceleration array dataInertial forceThe moment of inertia component of the rotation of the corresponding motion plane is。
Step five, calculating dynamic aerodynamic force except inertia force influenceDynamic aerodynamic forceThe aerodynamic moment component of the rotation of the corresponding motion plane is. Moment of inertia component rotating according to corresponding plane of motionAnd calculating rotational angular acceleration corresponding to moment of inertia about the moment reference point in the motion plane。
Step six, corresponding to the rotation angle acceleration in the motion planeIntegrating to obtain angular velocity。
Step seven, adopting high-pass filters with the same parameters to respectively count the inner angular speeds of corresponding motion planesAnd the dynamic derivative corresponds to the amount of aerodynamic moment rotating in the plane of motionAnd (3) high-pass filtering, wherein the filter cutoff frequency is lower than the model motion frequency.
Step eight, except for the vicinity of the angle with zero speed, for each angle in the motion process, the point speed and dynamic aerodynamic moment component corresponding to the forward motion travel are recorded asAndThe point velocity and dynamic aerodynamic moment component corresponding to the negative motion travel are recorded asAndAccording to the formulaThe dynamic derivative of the corresponding in-plane rotation is calculated.
For each Mach number, motion frequency, etc., test state, the dynamic derivative calculation repeats steps three through eight.
Examples:
for large amplitude motions of pitch, the acquisition of the pitch derivative may be performed as follows.
Arranging an acceleration array on the model, calculating by using single-axis acceleration components, and arranging at least 6 accelerometers, wherein the accelerometer output vectors corresponding to any uncorrelated inertial force are uncorrelated.
Step two, obtaining the output A of the acceleration array to the inertial force through calibrationMapping relation of (2). Acquiring moment of inertia about moment reference point in pitching plane of model through three-dimensional design software or theoretical calculation。
Step three, under the condition of stable wind tunnel flow field, the model moves in large amplitude on the pitching plane, and synchronously acquires the model through synchronous acquisition equipmentBalance, acceleration array data.
Step four, calculating the balance measured valueCalculating inertial force from acceleration array dataInertial forceThe moment of inertia of the middle pitch is a component。
Step five, calculating dynamic aerodynamic force except inertia force influenceDynamic aerodynamic forceThe medium pitch aerodynamic moment component is. Based on the pitch moment of inertia component and the moment of inertia about the moment reference pointCalculating pitch acceleration。
Step six, for pitch angle accelerationIntegrating to obtain angular velocity。
And seventhly, respectively carrying out high-pass filtering on the pitch angle speed and the pitch moment component by adopting the high-pass filter with the same parameter, wherein the filtering cut-off frequency is lower than the model motion frequency.
Step eight, except for the vicinity of the angle with zero speed, for each angle in the motion process, the point speed and dynamic aerodynamic moment component corresponding to the forward motion travel are recorded asAndThe point velocity and dynamic aerodynamic moment component corresponding to the negative motion travel are recorded asAndAccording to the formulaThe pitch derivative is calculated.
And (3) repeating the third step to the eighth step for each Mach number, motion frequency and other test states by pitch motion derivative calculation. The yaw and roll derivatives calculation method is similar to the pitch derivatives and will not be described again.
The above is merely illustrative of a preferred embodiment, but is not limited thereto. In practicing the present invention, appropriate substitutions and/or modifications may be made according to the needs of the user.
Although embodiments of the invention have been disclosed above, they are not limited to the use listed in the specification and embodiments. It can be applied to various fields suitable for the present invention. Additional modifications will readily occur to those skilled in the art. Therefore, the invention is not to be limited to the specific details and illustrations shown and described herein, without departing from the general concepts defined in the claims and their equivalents.
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| CN109063391A (en) * | 2018-09-30 | 2018-12-21 | 上海机电工程研究所 | Dynamic derivative under rotating condition calculates detection method and dynamic derivative wind tunnel test methods |
| CN110132527A (en) * | 2019-06-24 | 2019-08-16 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of model vibration monitoring method in the wind tunnel test based on balance signal |
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| DE10001813C2 (en) * | 2000-01-18 | 2003-10-30 | Eads Deutschland Gmbh | Measuring system for determining air data of an aircraft and a method for determining the air data |
| CN104850759B (en) * | 2015-06-16 | 2017-08-25 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of wind-tunnel forced vibration dynamic stability derivative Data Processing Method |
| CN114088330B (en) * | 2021-11-19 | 2023-03-17 | 中国航空工业集团公司哈尔滨空气动力研究所 | Longitudinal dynamic derivative low-speed wind tunnel continuous measurement test method |
| CN114838905B (en) * | 2022-03-23 | 2023-05-12 | 厦门大学 | Novel dynamic aerodynamic force measurement method for model of tethered parallel support aircraft |
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| CN109063391A (en) * | 2018-09-30 | 2018-12-21 | 上海机电工程研究所 | Dynamic derivative under rotating condition calculates detection method and dynamic derivative wind tunnel test methods |
| CN110132527A (en) * | 2019-06-24 | 2019-08-16 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of model vibration monitoring method in the wind tunnel test based on balance signal |
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