CN113252289A - Two-degree-of-freedom wind tunnel virtual flight test method - Google Patents
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- CN113252289A CN113252289A CN202110812883.6A CN202110812883A CN113252289A CN 113252289 A CN113252289 A CN 113252289A CN 202110812883 A CN202110812883 A CN 202110812883A CN 113252289 A CN113252289 A CN 113252289A
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- G—PHYSICS
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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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- G—PHYSICS
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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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Abstract
The invention discloses a two-degree-of-freedom wind tunnel virtual flight test method. The two-degree-of-freedom wind tunnel virtual flight test method comprises the following steps: the method comprises the following steps: preparing a wind tunnel virtual flight test; step two: releasing the pitching freedom degree and the rolling freedom degree of the test model; step three: pitch and roll maneuver flight control laws; step four: ending single blowing of the wind tunnel virtual flight test; step five: and executing the wind tunnel virtual flight test in the new parameter state. The two-degree-of-freedom wind tunnel virtual flight test method provided by the invention fully utilizes the advantages that a large wind tunnel can realize real simulation of flight physical environment, high efficiency, accuracy and low cost repeatable simulation, establishes a wind tunnel virtual flight test method suitable for integrated evaluation and verification of aerodynamic/motion/control performance of an aircraft, is an innovative method means besides the existing digital modeling simulation, semi-physical simulation and flight test methods, and has important technical support significance for aircraft flight control optimization design and performance evaluation.
Description
Technical Field
The invention belongs to the technical field of intersection of wind tunnel tests and flight tests, and particularly relates to a two-degree-of-freedom wind tunnel virtual flight test method.
Background
At present, the evaluation and verification of the aerodynamic performance and the flight control performance of an aircraft are mainly carried out in a serial mode, the flight/control performance verification is mainly based on modeling simulation, and finally the aerodynamic performance/control performance is evaluated and verified through a flight test. However, flight test verification can only be carried out in a small amount aiming at a typical state due to the large risk, high cost and long period of the flight test of the lifting body.
At present, a two-degree-of-freedom wind tunnel virtual flight test method for integrated evaluation and verification of aerodynamic/motion/control performance of an aircraft needs to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a two-degree-of-freedom wind tunnel virtual flight test method.
The invention discloses a two-degree-of-freedom wind tunnel virtual flight test method, which comprises the following steps of:
the method comprises the following steps: preparing a wind tunnel virtual flight test;
starting a flight control system; adjusting the pitch angle, the roll angle and the pneumatic control surface of the test model to 0 degrees, locking the pitch freedom degree and the roll freedom degree of the test model, and locking the pneumatic control surface of the test model; setting a pitch angle instruction and a roll angle instruction of the pitching and rolling maneuvering of the test model; starting wind tunnel video monitoring, and detecting the state of the test model in real time;
step two: releasing the pitching freedom degree and the rolling freedom degree of the test model;
setting a wind tunnel flow field control parameter according to the wind tunnel virtual flight test requirement, starting the wind tunnel, and releasing the pitching freedom degree and the rolling freedom degree of the test model after the flow field is stabilized to allow the test model to freely pitch and roll;
step three: pitch and roll maneuver flight control laws;
executing a flight control law according to the set pitch angle instruction and the set roll angle instruction, and measuring the pitch angle, the pitch angle speed, the roll angle and the roll angle speed of the test model by the motion parameter measuring equipment; the flight control system synchronously receives the motion parameter signals in real time and feeds the motion parameter signals back to a flight control law; the flight control law gives a control plane deflection instruction according to the deviation between the real angle of the test model and the target value; the test model starts pitching motion and rolling motion under the drive of aerodynamic force and torque generated by the control surface, and the pitch angle and the rolling angle approach to the target value until the real angle of the test model reaches the target value, so that the preset pitching and rolling maneuvering motion is completed. In the maneuvering process of the test model, processing and displaying the test result in real time, and monitoring the test state in real time;
step four: ending single blowing of the wind tunnel virtual flight test;
and after the pitch angle instruction and the roll angle instruction of the test model are completely executed, the flight control law gives a 0-degree pitch angle instruction and a 0-degree roll angle instruction. Repeating the process of the third step to return the pitch angle and the roll angle of the test model to the initial 0-degree position; locking the pitching freedom degree and the rolling freedom degree of the test model; closing the vehicle in the wind tunnel, and finishing single blowing in the wind tunnel virtual flight test;
step five: executing a wind tunnel virtual flight test in a new parameter state;
and resetting a pitch angle instruction and a roll angle instruction of the wind tunnel virtual flight test and related wind tunnel flow field control parameters, and repeatedly executing the processes of the first step to the fourth step to complete the wind tunnel virtual flight test in a new parameter state.
The two-degree-of-freedom wind tunnel virtual flight test method provided by the invention fully utilizes the advantages that a large wind tunnel can realize real simulation of flight physical environment, high efficiency, accuracy and low cost repeatable simulation, establishes a wind tunnel virtual flight test method suitable for integrated evaluation and verification of aerodynamic/motion/control performance of an aircraft, is an innovative method means besides the existing digital modeling simulation, semi-physical simulation and flight test methods, and has important technical support significance for aircraft flight control optimization design and performance evaluation.
Compared with the traditional modeling simulation method, the two-degree-of-freedom wind tunnel virtual flight test method is more real and accurate, and the verification result is more reliable; compared with a flight test method, the method is lower in evaluation and verification cost and risk and more efficient.
Drawings
FIG. 1 is a flow chart of a two-degree-of-freedom wind tunnel virtual flight test method of the present invention;
FIG. 2 is a flow chart of control of pitch rudder deflection angle and roll rudder deflection angle of a test model using the two-degree-of-freedom wind tunnel virtual flight test method of the present invention.
FIG. 3a is a schematic view showing a pitch angle command of a test model obtained by using the two-degree-of-freedom wind tunnel virtual flight test method of the present inventionθ cmdAngle of true pitchθTime history curves of (d);
FIG. 3b is a diagram of a test model roll angle command obtained by using the two-degree-of-freedom wind tunnel virtual flight test method of the present inventionφ cmdAngle of true rollφTime history curves of (d);
FIG. 3c is a schematic view showing a pitch rudder deflection angle of a test model obtained by using the two-degree-of-freedom wind tunnel virtual flight test method of the present inventionδ zTime history curves of (d);
FIG. 3d is a diagram showing a roll rudder deflection angle of a test model obtained by using the two-degree-of-freedom wind tunnel virtual flight test method of the present inventionδ xTime history curves of (d);
FIG. 3e is a view showing a pitch angle velocity of a test model obtained by using the two-degree-of-freedom wind tunnel virtual flight test method of the present inventionqTime history curves of (d);
FIG. 3f is a diagram showing the roll angular velocity of a test model obtained by the two-degree-of-freedom wind tunnel virtual flight test method of the present inventionpTime history curves of (d);
FIG. 3g is a test model normal force system obtained by the two-degree-of-freedom wind tunnel virtual flight test method of the present inventionC N Time history curves of (d);
FIG. 3h is a side force system of a test model obtained by the two-degree-of-freedom wind tunnel virtual flight test method of the inventionC Z Time history curve of (d).
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
As shown in FIG. 1, the two-degree-of-freedom wind tunnel virtual flight test method of the invention comprises the following steps:
the method comprises the following steps: preparing a wind tunnel virtual flight test;
starting a flight control system; adjusting the pitch angle, the roll angle and the pneumatic control surface of the test model to 0 degrees, locking the pitch freedom degree and the roll freedom degree of the test model, and locking the pneumatic control surface of the test model; setting a pitch angle instruction and a roll angle instruction of the pitching and rolling maneuvering of the test model; starting wind tunnel video monitoring, and detecting the state of the test model in real time;
step two: releasing the pitching freedom degree and the rolling freedom degree of the test model;
setting a wind tunnel flow field control parameter according to the wind tunnel virtual flight test requirement, starting the wind tunnel, and releasing the pitching freedom degree and the rolling freedom degree of the test model after the flow field is stabilized to allow the test model to freely pitch and roll;
step three: pitch and roll maneuver flight control laws;
executing a flight control law according to the set pitch angle instruction and the set roll angle instruction, and measuring the pitch angle, the pitch angle speed, the roll angle and the roll angle speed of the test model by the motion parameter measuring equipment; the flight control system synchronously receives the motion parameter signals in real time and feeds the motion parameter signals back to a flight control law; the flight control law gives a control plane deflection instruction according to the deviation between the real angle of the test model and the target value; the test model starts pitching motion and rolling motion under the drive of aerodynamic force and torque generated by the control surface, and the pitch angle and the rolling angle approach to the target value until the real angle of the test model reaches the target value, so that the preset pitching and rolling maneuvering motion is completed. In the maneuvering process of the test model, processing and displaying the test result in real time, and monitoring the test state in real time;
step four: ending single blowing of the wind tunnel virtual flight test;
and after the pitch angle instruction and the roll angle instruction of the test model are completely executed, the flight control law gives a 0-degree pitch angle instruction and a 0-degree roll angle instruction. Repeating the process of the third step to return the pitch angle and the roll angle of the test model to the initial 0-degree position; locking the pitching freedom degree and the rolling freedom degree of the test model; closing the vehicle in the wind tunnel, and finishing single blowing in the wind tunnel virtual flight test;
step five: executing a wind tunnel virtual flight test in a new parameter state;
and resetting a pitch angle instruction and a roll angle instruction of the wind tunnel virtual flight test and related wind tunnel flow field control parameters, and repeatedly executing the processes of the first step to the fourth step to complete the wind tunnel virtual flight test in a new parameter state.
Example 1
As shown in fig. 2, in the real airflow environment of a large wind tunnel, the pitch angle instruction and the roll angle instruction of the test model are given by the flight control law of the flight control system in this embodiment. Meanwhile, the motion parameter measuring equipment measures the pitch angle, the pitch angle speed, the roll angle and the roll angle speed of the test model, and synchronously transmits the measured values to the flight control system in real time to serve as feedback signals of the flight control law. And the flight control law further provides a control surface deflection instruction according to the deviation between the real pitch angle instruction and the pitch angle instruction of the test model and the deviation between the real roll angle instruction and the roll angle instruction, generates proper pitch moment on the test model, and drives the test model to perform pitch and roll motions so that the pitch angle instruction and the roll angle instruction of the test model tend to the pitch angle instruction and the roll angle instruction. The process is continuously circulated until the real pitch angle and the real roll angle of the test model reach the pitch angle target value and the roll angle target value given by the flight control law, the expected pitching maneuvering motion and the expected rolling maneuvering motion are completed, and in the test process, the pneumatic parameter measuring equipment synchronously measures the pneumatic power and the torque of the test model, so that the integrated evaluation and verification of the pneumatic/movement/control performance of the aircraft are realized.
Formula (1) gives a pitch angle instruction of a two-degree-of-freedom wind tunnel virtual flight testθ cmdRoll angle commandφ cmdTypical state parameter conditions of (2):
the pneumatic parameter measuring equipment in the embodiment can synchronously measure and record time history curves of physical quantities such as a pitch angle, a roll angle, pneumatic force, moment and the like in real time, and the obtained typical physical quantity time history curves are shown in figures 3 a-3 h. As can be seen from the figures 3 a-3 h, the two-degree-of-freedom wind tunnel virtual flight test method can realize the flight control of the pitching and rolling motion of the aircraft in the wind tunnel, and has the integrated evaluation and verification capability of the aerodynamic/motion/control performance of the aircraft.
Although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, but it can be applied to various fields suitable for the present invention. Additional modifications and refinements of the present invention will readily occur to those skilled in the art without departing from the principles of the present invention, and therefore the present invention is not limited to the specific details and illustrations shown and described herein without departing from the general concept defined by the claims and their equivalents.
Claims (1)
1. A two-degree-of-freedom wind tunnel virtual flight test method is characterized by comprising the following steps:
the method comprises the following steps: preparing a wind tunnel virtual flight test;
starting a flight control system; adjusting the pitch angle, the roll angle and the pneumatic control surface of the test model to 0 degrees, locking the pitch freedom degree and the roll freedom degree of the test model, and locking the pneumatic control surface of the test model; setting a pitch angle instruction and a roll angle instruction of the pitching and rolling maneuvering of the test model; starting wind tunnel video monitoring, and detecting the state of the test model in real time;
step two: releasing the pitching freedom degree and the rolling freedom degree of the test model;
setting a wind tunnel flow field control parameter according to the wind tunnel virtual flight test requirement, starting the wind tunnel, and releasing the pitching freedom degree and the rolling freedom degree of the test model after the flow field is stabilized to allow the test model to freely pitch and roll;
step three: pitch and roll maneuver flight control laws;
executing a flight control law according to the set pitch angle instruction and the set roll angle instruction, and measuring the pitch angle, the pitch angle speed, the roll angle and the roll angle speed of the test model by the motion parameter measuring equipment; the flight control system synchronously receives the motion parameter signals in real time and feeds the motion parameter signals back to a flight control law; the flight control law gives a control plane deflection instruction according to the deviation between the real angle of the test model and the target value; the test model starts pitching motion and rolling motion under the drive of aerodynamic force and torque generated by the control surface, and the pitch angle and the rolling angle approach to the target value until the real angle of the test model reaches the target value, so that the preset pitching and rolling maneuvering motion is completed; in the maneuvering process of the test model, processing and displaying the test result in real time, and monitoring the test state in real time;
step four: ending single blowing of the wind tunnel virtual flight test;
after the pitch angle instruction and the roll angle instruction of the test model are completely executed, the flight control law gives a 0-degree pitch angle instruction and a 0-degree roll angle instruction; repeating the process of the third step to return the pitch angle and the roll angle of the test model to the initial 0-degree position; locking the pitching freedom degree and the rolling freedom degree of the test model; closing the vehicle in the wind tunnel, and finishing single blowing in the wind tunnel virtual flight test;
step five: executing a wind tunnel virtual flight test in a new parameter state;
and resetting a pitch angle instruction and a roll angle instruction of the wind tunnel virtual flight test and related wind tunnel flow field control parameters, and repeatedly executing the processes of the first step to the fourth step to complete the wind tunnel virtual flight test in a new parameter state.
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| CN113899526A (en) * | 2021-10-11 | 2022-01-07 | 中国航空工业集团公司哈尔滨空气动力研究所 | Self-compensating heave control system |
| CN114577433A (en) * | 2022-02-15 | 2022-06-03 | 中国航空工业集团公司哈尔滨空气动力研究所 | Wind tunnel virtual flight test balance aerodynamic force acquisition and processing system |
| CN114608794A (en) * | 2022-05-11 | 2022-06-10 | 中国航空工业集团公司哈尔滨空气动力研究所 | Method for measuring aerodynamic coefficient of model wind tunnel virtual flight test |
| CN115307861A (en) * | 2022-10-10 | 2022-11-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Flight verification method and flight verification model for torque control performance of jet control surface |
| CN115436003A (en) * | 2022-11-07 | 2022-12-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel hanging test method and device |
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| CN114608794A (en) * | 2022-05-11 | 2022-06-10 | 中国航空工业集团公司哈尔滨空气动力研究所 | Method for measuring aerodynamic coefficient of model wind tunnel virtual flight test |
| CN114608794B (en) * | 2022-05-11 | 2022-07-19 | 中国航空工业集团公司哈尔滨空气动力研究所 | Method for measuring aerodynamic coefficient of model wind tunnel virtual flight test |
| CN115307861A (en) * | 2022-10-10 | 2022-11-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Flight verification method and flight verification model for torque control performance of jet control surface |
| CN115307861B (en) * | 2022-10-10 | 2023-01-03 | 中国空气动力研究与发展中心低速空气动力研究所 | Flight verification method and flight verification model for torque control performance of jet control surface |
| CN115436003A (en) * | 2022-11-07 | 2022-12-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel hanging test method and device |
| CN115436003B (en) * | 2022-11-07 | 2023-03-24 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel hanging test method and device |
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