CN114383879A - Test method of second order differential loop in flight simulator identification test guidance system - Google Patents

Abstract

The invention belongs to the technical field of flight simulator identification and testing, and in particular relates to a test method for a second-order differential loop in a flight simulator identification test guide system. The simulation system controlled by the pilot in the QTG system loop; step 2, abstract the process of the pilot's manipulation action and dynamic adjustment manipulation action in the flight simulator into a second-order differential loop; step 3, adjust the parameters of each second-order differential loop to make The second-order differential loop is suitable for the corresponding flight simulator; in step 4, the second-order differential loop is tested in the QTG system, and the verification data is used as the input to control the state of each system, and the second-order differential loop is used to dynamically adjust each system according to the state of each system. . According to the second-order differential loop test in the QTG system, the invention realizes the test of each system of the flight simulator in the QTG system, and provides the test and verification capability of the D-level standard for the flight simulator.

Description

Test Method of Second Order Differential Loop in Flight Simulator Qualification Test Guide System

technical field

The invention belongs to the technical field of flight simulator identification and testing, in particular to a test method for a second-order differential loop in a flight simulator identification test guide system.

Background technique

At present, the domestic research and development of the Qualification Test Guide (QTG) system for full-motion flight simulators provides development space for the testing and verification capabilities of the D-level standards for flight simulators. However, there is no systematic description and implementation method for the use and realization process of test flight/verification data in the full-motion flight simulator qualification test guide system. The flight simulator R&D and manufacturing personnel need to design and develop independently to realize the flight simulator qualification test. Moreover, most of the existing QTG systems and researches only briefly describe the processing and conversion process of test flight/verification data, and how to use the verification data and test flight data to realize the verification to ensure that the flight simulator responds to the test flight/verification data in real time and dynamically , and did not propose the processing procedure and implementation method.

SUMMARY OF THE INVENTION

The main purpose of the present invention is to solve the problems existing in the prior art, and to provide a test method for a second-order differential loop in a flight simulator identification and test guide system. According to the state of each system of the flight simulator, the second-order differential loop is used to dynamically adjust each system of the flight simulator, so that the flight simulator can respond to the verification data in real time and dynamically, and realize the test of each system of the flight simulator in the QTG system.

The technical problem solved by the present invention is realized by the following technical solutions: a test method for a second-order differential loop to identify a test guide system in a flight simulator; The flight dynamics model of the aircraft responds to the manipulation actions, and outputs the system states of the flight simulator by manipulating the load system, instrument system, visual system, motion system, and sound system. The pilot dynamically adjusts the manipulation actions according to the states of the flight simulator systems to achieve A simulation system that pilots operate in the QTG system loop;

Step 2. The process of pilot manipulation and dynamic adjustment manipulation in the flight simulator is abstracted into a second-order differential loop. When debugging the QTG system according to the second-order differential loop, the input data of the second-order differential loop adopts QTG The verification data in the system is sent to the second-order differential circuit No. 1, the second-order differential circuit No. 2, the second-order differential circuit No. 3, the second-order differential circuit No. 4, the second-order differential circuit No. The process of the differential loop simulates the pilot's control action through the control system in the flight simulator; the process of sending the verification data to the second-order differential negative feedback loop simulates the pilot's dynamic adjustment of the control action according to the state of each system of the flight simulator;

Step 3. When debugging the QTG system, adjust No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, No. 6 second-order differential loop The parameters of the differential loop make the second-order differential loop suitable for the corresponding flight simulator;

Step 4, test in the QTG system according to the second-order differential loop, the input data of the second-order differential loop adopts the verification data in the QTG system, and send the verification data to the No. 1 second-order differential loop, the No. 2 second-order differential loop, The second-order differential loop No. 3, the second-order differential loop No. 4, the second-order differential loop No. 5, and the second-order differential loop No. 6 become control data, and the control data is input to the control load system, instrument system, visual system, and motion system. , sound system, each system of the flight simulator responds to the control data and outputs the state of each system; according to the state of each system of the flight simulator, the verification data is sent to the second-order differential negative feedback loop and becomes the dynamic control data, and the dynamic control data Input to each system of the flight simulator, each system of the flight simulator responds to the dynamic control data and adjusts each system dynamically, and realizes the second-order differential loop to test each system of the flight simulator in the QTG system.

Further, in step 2, the process of pilot manipulation action and dynamic adjustment manipulation action in the flight simulator is abstracted into a second-order differential loop, which further includes,

Since the output voltage and current value of the motor in the flight simulator have hysteresis after closed-loop adjustment, the motor speed changes greatly in unit time, and the differential part in the PID control is introduced as the lead adjustment variable to ensure the speed stability when the motor load changes, then The process of pilot manipulation and dynamic adjustment manipulation in the flight simulator is abstracted into a second-order differential loop.

Further, the verification data in the QTG system includes a manipulation amount and an output amount, and the manipulation amount includes the forward and backward movement position of the steering wheel, the steering wheel rotation angle, the pedal position, the flaps and slat positions, and the landing gear position; the output amount includes the height , Speed, Pitch Angle, Pitch Angle Velocity, Pitch Angle Acceleration, Yaw Angle, Spoiler Angle, Elevator Angle, Slat Angle, Landing Gear, Time Information.

Further, in step 4, the QTG system is tested according to the second-order differential loop, and the input data of the second-order differential loop adopts the verification data in the QTG system, further comprising,

The QTG system is tested according to the second-order differential loop, and the input data of the second-order differential loop adopts the verification data in the QTG system and the verification data is the converted standard format data.

Further, in step 3, when debugging the QTG system, adjust No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, No. 6 The parameters of the second-order differential loop to make the second-order differential loop fit the corresponding flight simulator, further comprising,

During the debugging of the QTG system, due to the differences in the systems, hardware equipment and software responses of different types of flight simulators, adjust the No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. The parameters of the first-order differential loop, No. 5 second-order differential loop, and No. 6 second-order differential loop make the second-order differential loop suitable for the corresponding flight simulator.

Further, in step 4, each system of the flight simulator responds to the dynamic control data and adjusts each system dynamically, so as to realize the second-order differential loop to test each system of the flight simulator in the QTG system, further comprising,

Each system of the flight simulator responds to the dynamic control data and adjusts each system dynamically, and also plots the input data of the second-order differential loop and the response changes of the flight simulator system to display the test results of the QTG system, so that the second-order differential loop is Test flight simulator systems in the QTG system.

The beneficial effects of the present invention are:

The present invention tests the QTG system according to the second-order differential loop, the input data of the second-order differential loop adopts the verification data in the QTG system, and sends the verification data to the No. 1 second-order differential loop, the No. 2 second-order differential loop, and the No. The first-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, and No. 6 second-order differential loop become control data, and the control data is input to the control load system, instrument system, visual system, motion system, and sound system. , each system of the flight simulator responds to the control data and outputs the state of each system; according to the state of each system of the flight simulator, the verification data is sent to the second-order differential negative feedback loop to become the dynamic control data, and the dynamic control data is input to the flight simulator Each system, each system of the flight simulator responds to the dynamic control data and adjusts each system dynamically. It can be seen that the present invention uses the verification data as input to control the states of each system of the flight simulator, and then uses the second-order differential loop to dynamically adjust each system of the flight simulator according to the system states of the flight simulator, so that the flight simulator can respond to the verification data in real time and dynamically. The corresponding relationship between the verification data and the pilot's manipulation input is found, and the method of dynamically debugging the states of each system is provided, and the test of each system of the flight simulator in the QTG system is realized, and the test and verification capability of the D-level standard is provided for the flight simulator.

Description of drawings

FIG. 1 is a flow chart of the test method of the second-order differential loop in the flight simulator qualification test guide system of the present invention.

FIG. 2 is a block diagram of a simulation system operated by a pilot in the QTG system loop of the present invention.

3 is a block diagram of a second order differential loop of the present invention.

FIG. 4 is a structural diagram of a second-order differential loop for debugging the QTG system using the verification data of the present invention.

Figures 5(a)-5(f) are comparison diagrams of input data and system response changes in the second-order differential loop of the present invention.

Detailed ways

The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the accompanying drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the indicated device or element must have a specific orientation or a specific orientation. construction and operation, and therefore should not be construed as limiting the invention. Furthermore, the terms "first", "second", and "third" are used for descriptive purposes only and should not be construed to indicate or imply relative importance.

In the description of the present invention, it should be noted that the terms "installed", "connected" and "connected" should be understood in a broad sense, unless otherwise expressly specified and limited, for example, it may be a fixed connection or a detachable connection Connection, or integral connection; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through an intermediate medium, can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood in specific situations.

As shown in Figures 1 to 4, the present invention provides a test method for a second-order differential loop in a flight simulator identification test guide system. Step 1. The pilot performs a control action through the control system in the flight simulator, and the flight simulator The dynamic model responds to the manipulation action, and outputs the system status of the flight simulator by manipulating the load system, instrument system, visual system, motion system, and sound system. The pilot dynamically adjusts the manipulation action according to the status of each system of the flight simulator, so as to realize the pilot's performance in the QTG A simulated system that operates in a system loop.

Among them, according to the classification of continuous system simulation in the field of engineering application, the flight simulation equipment belongs to the simulation of human in the loop, that is, the simulation system in which the pilot operates in the system loop. The system must run in real time, and has strict technical index requirements for the confidence and accuracy of dynamic characteristics, static characteristics and time delay.

Step 2. The process of pilot manipulation and dynamic adjustment manipulation in the flight simulator is abstracted into a second-order differential loop. When debugging the QTG system according to the second-order differential loop, the input data of the second-order differential loop is adopted in the QTG system. Verifying data, verifying the process of sending data to No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, and No. 6 second-order differential loop , simulating the pilot's control action through the control system in the flight simulator; the process of sending the verification data to the second-order differential negative feedback loop, simulating the pilot's dynamic adjustment of the control action according to the state of each system of the flight simulator;

Step 3. When debugging the QTG system, adjust No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, No. 6 second-order differential loop , so that the second-order differential loop is suitable for the corresponding flight simulator;

Step 4. Test in the QTG system according to the second-order differential loop. The input data of the second-order differential loop adopts the verification data in the QTG system, and send the verification data to the No. 1 second-order differential loop, No. 2 second-order differential loop, and No. 3 The second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, and No. 6 second-order differential loop become control data, and the control data is input to the control load system, instrument system, visual system, motion system, sound system, each system of the flight simulator responds to the control data and outputs the state of each system; according to the state of each system of the flight simulator, the verification data is sent to the second-order differential negative feedback loop to become the dynamic control data, and the dynamic control data is input to the flight simulation Each system of the flight simulator and each system of the flight simulator respond to the dynamic control data and adjust each system dynamically, realizing the second-order differential loop to test each system of the flight simulator in the QTG system.

Further, in step 2, the process of pilot manipulation action and dynamic adjustment manipulation action in the flight simulator is abstracted into a second-order differential loop, which further includes,

Since the output voltage and current value of the motor in the flight simulator have hysteresis after closed-loop adjustment, the motor speed changes greatly in unit time, and the differential part in the PID control is introduced as the lead adjustment variable to ensure the speed stability when the motor load changes, then The process of pilot manipulation and dynamic adjustment manipulation in the flight simulator is abstracted into a second-order differential loop.

Among them, in the flight simulation system, some rotational speeds change greatly in unit time, such as the pitch angle and the moment of inertia. Because the motor is a partial inductive load, its output voltage and current have hysteresis after closed-loop regulation. In order to meet the requirements of the real-time performance of the flight simulator and the positional accuracy of the control surface and the control surface, the lead adjustment amount is introduced to meet the stability of the rotational speed when the motor load changes. Therefore, the differential part in the PID (Proportional (proportional), Integral (integral), Differential (differential)) control is introduced to play the role of advanced adjustment.

Further, the verification data in the QTG system includes the manipulation quantity and the output quantity. The manipulation quantity includes the forward and backward movement position of the joystick, the steering wheel rotation angle, the pedal position, the flaps and slat positions, and the landing gear position; the output quantity includes the altitude, speed, pitch angle, Pitch velocity, pitch acceleration, yaw angle, spoiler angle, elevator angle, flap and slat angle, landing gear, time information.

Further, in step 4, the QTG system is tested according to the second-order differential loop, and the input data of the second-order differential loop adopts the verification data in the QTG system, further comprising,

The QTG system is tested according to the second-order differential loop. The input data of the second-order differential loop adopts the verification data in the QTG system and the verification data is the converted standard format data.

Further, in step 3, when debugging the QTG system, adjust the No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. 4 second-order differential loop, No. The parameters of the differential loop to make the second-order differential loop fit the corresponding flight simulator, further including,

During the debugging of the QTG system, due to the differences in the systems, hardware equipment and software responses of different types of flight simulators, adjust the No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, and No. The parameters of the loop, No. 5 second-order differential loop, and No. 6 second-order differential loop make the second-order differential loop suitable for the corresponding flight simulator.

Among them, each flight simulator has different natural frequencies and response characteristics due to differences in systems, hardware equipment, and software responses. Therefore, in the QTG debugging process, the parameters of each second-order differential loop are adjusted to adapt to each flight simulator, that is, a generalized method for the application of the second-order differential loop in the full-motion flight simulator qualification test system.

Further, in step 4, each system of the flight simulator responds to the dynamic control data and adjusts each system dynamically, so as to realize the second-order differential loop to test each system of the flight simulator in the QTG system, further comprising,

Each system of the flight simulator responds to the dynamic control data and adjusts each system dynamically, and also plots the input data of the second-order differential loop and the response changes of the flight simulator system to display the test results of the QTG system, and realizes the second-order differential loop in the QTG system. Test flight simulator systems.

Example

As shown in Figure 1-4, the test process in the QTG system according to the second-order differential loop is as follows:

Step 1. The pilot performs the control action through the control system in the flight simulator. The flight dynamics model of the flight simulator responds to the control action, and outputs the various functions of the flight simulator by manipulating the load system, instrument system, visual system, motion system, and sound system. System state, the pilot dynamically adjusts the control action according to the system state of the flight simulator, as shown in Figure 2, to realize the simulation system that the pilot controls in the QTG system loop.

Step 2. The process of pilot manipulation and dynamic adjustment manipulation in the flight simulator is abstracted into a second-order differential loop. When debugging the QTG system according to the second-order differential loop, the input data of the second-order differential loop is adopted in the QTG system. Verifying data, verifying the process of sending data to No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, and No. 6 second-order differential loop , simulating the pilot's control action through the control system in the flight simulator; the process of sending the verification data to the second-order differential negative feedback loop, simulating the pilot's dynamic adjustment of the control action according to the state of each system of the flight simulator.

As shown in Figure 3, No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, No. The input of the differential negative feedback loop can be obtained from the verification data of the QTG system, and then acted on the flight simulator after loop control, so as to realize the second-order differential loop control process.

Step 3. When debugging the QTG system, adjust No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, No. 6 second-order differential loop The parameters of the second order differential loop are suitable for the corresponding flight simulator.

The following takes the pitch angle as an example to describe the QTG debugging process shown in Figure 4 (which can be adjusted by the pitch angle). Through the data conversion software, the verification data in the standard format is extracted. The verification data includes: time, joystick, pitch angle, pitch Angular change rate, pitch angle change acceleration, etc.

The input acting on the flight simulator is:

u ₁ (t)=a*x(t)+b*h(t)+c*g(t)+d*k(t)

=a*x(t)+b*h(t)+c*k1*h'(t)+d*k2*h"(t)

Among them, u ₁ (t) is the synthetic control variable 1 acting on the control surface 1; x(t) is the verification data (input of the joystick); h(t) is the control surface angle of the aircraft simulation equipment, that is, the pitch angle; g(t) is the rate of change of the control surface, that is, the rate of change of the pitch angle; k(t) is the acceleration of the change of the control surface, that is, the rate of change of the pitch angle. a, b, c, d are the adjustment coefficients of each input quantity in the second-order differential loop in the QTG debugging process. The relationship among h(t), g(t) and k(t) is as follows: g(t)=h'(t), k(t)=g'(t)=h"(t).

As shown in Figure 5(a)-5(f), the pitch angle is taken as an example to illustrate the dynamic adjustment of the input coefficient and system response change in the second-order differential loop. The input is the displacement of the joystick, and the output is the pitch angle. The first-order adjustment amount is the pitch angle change rate, and the second-order adjustment amount is the pitch angle acceleration. Adjust the parameters of the second-order differential loop to (here is only an application example, the specific value is adjusted according to the system): parameter a is 1, parameter b is 0.0001, first-order differential coefficient c*k1 is 0.02, second-order differential coefficient d*k2 is 0.00005. At this time, the change of the steering stick displacement is shown in Figure 5(a), the solid line represents the change of the steering stick displacement, and the dashed line represents the change of the system response; the change of the pitch angle is shown in Figure 5(c), the solid line represents the change of the pitch angle, and the dashed line represents the system response change; the pitch angle change rate is shown in Figure 5(e), the solid line represents the pitch angle change rate change, and the dashed line represents the system response change.

In order to highlight the influence of adjusting the parameters of the second-order loop, adjust the parameters of the second-order differential loop to: the parameter a is 1, the parameter b is 0.0001, the first-order differential coefficient c*k1 is 0.022, and the second-order differential coefficient d*k2 is 0.0005, After adjustment, the system convergence and response characteristics change compared with the previous situation. At this time, the change of the steering rod displacement is shown in Figure 5(b). The solid line represents the change of the steering rod displacement, and the dashed line (the solid line in the dashed line represents the curve of the affected segment) represents the change of the system response; the change of the pitch angle is shown in Figure 5(d), the solid line represents the change of the pitch angle, and the dashed line (the solid line in the dashed line represents the curve of the affected segment) represents the change of the system response; the rate of change of the pitch angle is shown in Figure 5(f). ), the solid line represents the change in the rate of change of the pitch angle, and the dashed line (the solid line in the dashed line represents the curve of the affected segment) represents the system response change.

Figure 5(a) and Figure 5(b) show the characteristics of two different response curves before and after the adjustment of the steering stick displacement parameters, and Figure 5(c) and Figure 5(d) show the two different response curves before and after the adjustment of the pitch angle parameters Figure 5(e) and Figure 5(f) show the two different response curve characteristics before and after the adjustment of the pitch angle change rate parameter, which can reflect the influence of the second-order differential loop parameters on the QTG test, that is, reflect The impact of pilots' dynamic adjustment and control actions on aircraft systems is analyzed.

Step 4. Test in the QTG system according to the second-order differential loop. The input data of the second-order differential loop adopts the verification data in the QTG system, and send the verification data to the No. 1 second-order differential loop, No. 2 second-order differential loop, and No. 3 The second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, and No. 6 second-order differential loop become control data, and the control data is input to the control load system, instrument system, visual system, motion system, sound system, each system of the flight simulator responds to the control data and outputs the state of each system; according to the state of each system of the flight simulator, the verification data is sent to the second-order differential negative feedback loop to become the dynamic control data, and the dynamic control data is input to the flight simulation Each system of the flight simulator and each system of the flight simulator respond to the dynamic control data and adjust each system dynamically, and also plot the input data of the second-order differential loop and the response changes of the flight simulator system to display the test results of the QTG system, and realize the second-order differential loop. Road in the QTG system to test the various systems of the flight simulator.

As shown in Figure 4, the feedback mechanism is pitch angle, yaw angle, and roll angle, the controlled object is a flight simulator, r(t) is the verification data, and y(t) is the output angle (pitch angle, yaw angle) , roll angle), x(t) is the manipulation amount (steering stick, pedals, etc.), h(t) is the control surface angle, g(t) is the rate of change of the control surface, k(t) is the acceleration, u ₁ ( t) is the synthetic manipulation amount 1 acting on the controlled surface 1, u _n (t) is the synthetic manipulation amount n (n=1, 2, 3, ...) acting on the controlled surface n, u (t ) is the synthetic manipulation amount acting on the control object.

In the QTG system test, the verification data in the standard format is extracted through the data conversion software, the verification data is used as the input data of the second-order differential loop, and the verification data is sent to the No. 1 second-order differential loop, No. 2 second-order differential loop, No. The first-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, and No. 6 second-order differential loop become control data, and the control data is input to the control load system, instrument system, visual system, motion system, and sound system. , this process simulates the pilot's control action, the control data is u ₁ (t) to u _n-1 (t) in Figure 4, and each system of the flight simulator responds to the control data and outputs the state of each system; After sending the verification data to the second-order differential negative feedback loop, it becomes the dynamic control data, and the dynamic control data is input to each system of the flight simulator. This process simulates the pilot's dynamic adjustment and control actions. The dynamic control data is u _n in Figure 4. (t), each system of the flight simulator responds to the dynamic control data and adjusts each system dynamically, and also plots the input data of the second-order differential loop and the response changes of the flight simulator system to display the test results of the QTG system, and realizes the second-order differential loop. Road in the QTG system to test the various systems of the flight simulator. As shown in Figures 5(a)-5(f), the pitch angle is taken as an example to illustrate the input data of the second-order differential loop and the response changes of the flight simulator system to display the test results of the QTG system.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: The technical solutions described in the foregoing embodiments can still be modified, or some or all of the technical features thereof can be equivalently replaced; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the technical solutions of the embodiments of the present invention. scope.

Claims (6)

1. the test method of the second-order differential loop in the flight simulator identification test guide system, is characterized in that: Step 1. The pilot performs the control action through the control system in the flight simulator, the flight dynamics model of the flight simulator responds to the control action, and outputs the flight simulation by manipulating the load system, the instrument system, the visual system, the motion system, and the sound system According to the state of each system of the flight simulator, the pilot dynamically adjusts the control actions to realize the simulation system that the pilot controls in the QTG system loop; Step 2. The process of pilot manipulation and dynamic adjustment manipulation in the flight simulator is abstracted into a second-order differential loop. When debugging the QTG system according to the second-order differential loop, the input data of the second-order differential loop adopts QTG The verification data in the system is sent to the second-order differential circuit No. 1, the second-order differential circuit No. 2, the second-order differential circuit No. 3, the second-order differential circuit No. 4, the second-order differential circuit No. The process of the differential loop simulates the pilot's control action through the control system in the flight simulator; the process of sending the verification data to the second-order differential negative feedback loop simulates the pilot's dynamic adjustment of the control action according to the state of each system of the flight simulator; Step 3. When debugging the QTG system, adjust No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, No. 6 second-order differential loop The parameters of the differential loop make the second-order differential loop suitable for the corresponding flight simulator; Step 4, test in the QTG system according to the second-order differential loop, the input data of the second-order differential loop adopts the verification data in the QTG system, and send the verification data to the No. 1 second-order differential loop, the No. 2 second-order differential loop, The second-order differential loop No. 3, the second-order differential loop No. 4, the second-order differential loop No. 5, and the second-order differential loop No. 6 become control data, and the control data is input to the control load system, instrument system, visual system, and motion system. , sound system, each system of the flight simulator responds to the control data and outputs the state of each system; according to the state of each system of the flight simulator, the verification data is sent to the second-order differential negative feedback loop and becomes the dynamic control data, and the dynamic control data Input to each system of the flight simulator, each system of the flight simulator responds to the dynamic control data and adjusts each system dynamically, and realizes the second-order differential loop to test each system of the flight simulator in the QTG system. 2. second-order differential loop according to claim 1 is in the test method of flight simulator identification test guide system, it is characterized in that: in step 2, the process abstraction of pilot control action and dynamic adjustment control action in flight simulator is a second-order differential loop, which further includes, Since the output voltage and current value of the motor in the flight simulator have hysteresis after closed-loop adjustment, the motor speed changes greatly in unit time, and the differential part in the PID control is introduced as the lead adjustment variable to ensure the speed stability when the motor load changes, then The process of pilot manipulation and dynamic adjustment manipulation in the flight simulator is abstracted into a second-order differential loop. 3. the test method of the second-order differential loop according to claim 1 in the flight simulator identification test guide system, it is characterized in that: in the described QTG system, the verification data comprises manipulation quantity and output quantity, and described manipulation quantity comprises driving Rod forward and backward movement position, steering wheel rotation angle, pedal position, slat position, landing gear position; the output includes altitude, speed, pitch angle, pitch angle velocity, pitch angle acceleration, yaw angle, spoiler angle, Elevator angle, flap and slat angle, landing gear, time information. 4. second-order differential loop according to claim 1 is in the test method of flight simulator identification test guide system, it is characterized in that: in step 4, according to second-order differential loop to QTG system test, described second-order differential The input data of the loop adopts the verification data in the QTG system, which further includes, The QTG system is tested according to the second-order differential loop, and the input data of the second-order differential loop adopts the verification data in the QTG system and the verification data is the converted standard format data. 5. second-order differential loop according to claim 1 is in the test method of flight simulator identification test guide system, it is characterized in that: during step 3, described QTG system debugging, adjust No. 1 second-order differential loop, No. 2 The parameters of the second-order differential loop, No. 3 second-order differential loop, No. 4 second-order differential loop, No. 5 second-order differential loop, and No. 6 second-order differential loop make the second-order differential loop suitable for the corresponding flight simulator, and further include, During the debugging of the QTG system, due to the differences in the systems, hardware equipment and software responses of different types of flight simulators, adjust the No. 1 second-order differential loop, No. 2 second-order differential loop, No. 3 second-order differential loop, No. The parameters of the first-order differential loop, No. 5 second-order differential loop, and No. 6 second-order differential loop make the second-order differential loop suitable for the corresponding flight simulator. 6. the test method of second-order differential loop according to claim 1 and 3 in flight simulator identification test guide system, it is characterized in that: in step 4, each system of described flight simulator responds to dynamic manipulation data respectively and dynamically Adjust each system to realize the second-order differential loop to test each system of the flight simulator in the QTG system, further including, Each system of the flight simulator responds to the dynamic control data and adjusts each system dynamically, and also plots the input data of the second-order differential loop and the response changes of the flight simulator system to display the test results of the QTG system, so that the second-order differential loop is Test flight simulator systems in the QTG system.

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