CN111003207B - Stability margin testing system and method for aircraft steering engine dynamic stiffness test bed - Google Patents
Stability margin testing system and method for aircraft steering engine dynamic stiffness test bed Download PDFInfo
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- CN111003207B CN111003207B CN201911245075.5A CN201911245075A CN111003207B CN 111003207 B CN111003207 B CN 111003207B CN 201911245075 A CN201911245075 A CN 201911245075A CN 111003207 B CN111003207 B CN 111003207B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- 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
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Abstract
The invention provides a stability margin test system and method for an aircraft steering engine dynamic stiffness test bed, wherein the test system consists of a flight simulation system (1), an optical fiber network system (2), an aircraft steering engine dynamic stiffness test bed control system (3) and a loading platform (4). The aircraft simulation system (1) writes a disturbed force scanning instruction A (omega) into the optical fiber network system (2), the aircraft steering engine dynamic stiffness test bed control system (3) integrates A (omega) with a self-generated loading force instruction B (omega), and the loading platform (4) feeds back a force signal c (omega) to the aircraft steering engine dynamic stiffness test bed control system (3) in real time; the control system (3) of the aircraft rudder maneuvering rigidity test bed stores (A (omega) + B (omega)) and c (omega)) in real time, and draws an amplitude-frequency characteristic curve and a phase-frequency characteristic curve of c (omega)/(A (omega) + B (omega)). The test system and the test method provide necessary quantitative data for the force frequency sweeping stability of the aircraft steering engine dynamic stiffness test bed.
Description
Technical Field
The invention belongs to the technical field of measurement and control, and particularly relates to a stability margin test system and method for an aircraft steering engine dynamic stiffness test bed.
Background
The airplane rudder maneuvering rigidity test bed is characterized in that a steering engine is fixed on one side of a loading platform and fixedly connected with a loading cylinder through a gap eliminating connecting mechanism, a rudder actuator cylinder is in a static state in the test process, a dynamic rigidity test bed control system receives a load spectrum instruction of a flight simulation system and controls the loading cylinder to execute force loading on the steering engine, and a force sensor feeds back force signals in real time to complete force closed-loop control of the control system. However, in the actual force loading process, the force feedback signal often has a larger degree of attenuation or divergence with increasing loading frequency and the presence of complex interference sources in the field, wherein one of the main reasons is the stability of the loading control system. Therefore, it is necessary to obtain accurate and reliable stability data of the load control system.
Disclosure of Invention
In order to solve the technical problem, the invention provides a system and a method for testing the stability margin of a dynamic stiffness test bed of an aircraft steering engine, which are used for testing the stability margin of a control system of the dynamic stiffness test bed of the aircraft steering engine in a low-frequency range force frequency sweeping process and providing necessary quantitative data for improving the stability of the control system in the frequency range.
The system for testing the stability margin of the aircraft rudder maneuvering rigidity test bed mainly comprises: the system comprises a flight simulation system, an optical fiber network system, a simulated airplane steering engine and a dynamic stiffness test bed of the airplane steering engine. The aircraft simulation system is connected to the optical fiber network system, and a disturbed force scanning instruction A (omega) is written into the optical fiber network system; the airplane steering engine dynamic stiffness test bed consists of an airplane steering engine dynamic stiffness test bed control system and a loading platform to form a closed-loop control system, and a force signal c (omega) is fed back to the airplane steering engine dynamic stiffness test bed control system by the loading platform in real time; the control system of the aircraft rudder maneuvering rigidity test bed reads a disturbed force scanning instruction A (omega) from a preset address of the optical fiber network system and synthesizes the disturbed force scanning instruction A and a loading force instruction B (omega) generated by the control system with the control system to form a force control instruction.
The loading platform consists of a loading cylinder and a force sensor, the loading cylinder is used for receiving and executing a force control command sent by the control system of the aircraft steering engine dynamic stiffness test bed, and the force sensor is used for feeding back a force signal c (omega) in real time.
Further, the force control command is formed by superposing a force sweep frequency command signal A (omega) (digital quantity) and a loading force command B (omega) (digital quantity) generated by a control system of a steering engine dynamic stiffness test bed of the airplane and then carrying out DA conversion.
Typically, simulated aircraft steering engines employ steel rods.
Furthermore, the aircraft steering engine of the steel bar simulation is arranged on the aircraft steering engine maneuvering rigidity test bed, and the connection mode is that the aircraft steering engine is fixedly connected through a gap eliminating connection mechanism.
And furthermore, two gap eliminating connecting mechanisms are fixedly connected with the steel bar and the aircraft steering engine dynamic stiffness test bed, wherein the first gap eliminating connecting mechanism is used for fixedly connecting the steel bar and the force sensor, and the second gap eliminating connecting mechanism is used for fixedly connecting the steel bar and one side of the loading bed.
Generally, the frequency range of the disturbance force scan command A (omega) written into the optical fiber network system by the flight simulation system is 0.1 to 20Hz.
The test method of the aircraft rudder maneuvering rigidity test bed stability margin test system comprises the following specific steps:
step1: completing the installation of the loading platform;
step2: the flight simulation system generates an A (omega) interference force frequency sweep instruction and writes the A (omega) interference force frequency sweep instruction into a reserved address of the optical fiber network system;
step3: a flight control steering engine dynamic stiffness test bed control system reads an A (omega) interference force frequency sweep instruction at a preset address of an optical fiber network system and superposes the A (omega) interference force frequency sweep instruction with a loading force instruction B (omega);
step4: generating a force control command by the superposed (A (omega) + (omega)), and loading the force by a loading platform;
step5: the loading table feeds back a force signal c (omega) in real time, the flight control steering engine dynamic stiffness test table control system stores c (omega), and simultaneously stores (A (omega) + B (omega)) in the test process in real time;
step6: and after the sweep frequency test is finished, drawing an amplitude-frequency characteristic curve and a phase-frequency characteristic curve of c (omega)/(A (omega) + B (omega)).
In the technical scheme, the system and the method for testing the stability margin of the control system of the aircraft steering engine dynamic stiffness test bed abandon the link of generating analog quantity by a traditional signal generator, directly convert a disturbed force frequency sweep instruction into digital quantity by means of an optical fiber network system and superpose the digital quantity and a loading force instruction, and provide necessary quantitative data for improving the force frequency sweep stability of the aircraft steering engine dynamic stiffness test bed in the frequency range of 0.1 Hz-20 Hz.
Drawings
FIG. 1 is a schematic block diagram of a system for testing stability margin of a control system of an aircraft rudder maneuvering stiffness test bed.
In fig. 1: 1. the device comprises a flight simulation system 2, an optical fiber network system 3, an aircraft steering engine dynamic stiffness test bed control system 4, a loading platform 41, a loading cylinder 42, a force sensor 43, a steel bar (simulating an aircraft steering engine), 44, gap eliminating connection mechanisms I and 45 and a gap eliminating connection mechanism II.
Detailed Description
The technical solution in the embodiment of the present invention will be clearly and completely described below with reference to fig. 1.
As shown in fig. 1, the system for testing the stability margin of the control system of the aircraft steering maneuvering stiffness test bed mainly comprises a flight simulation system 1, an optical fiber network system 2, a control system 3 of the aircraft steering maneuvering stiffness test bed and a loading platform 4, wherein a loading cylinder 41 and a force sensor 42 are configured on the loading platform 4, and a steel bar 43 (simulating an aircraft steering engine) is fixed on one side of the force sensor 42 and one side of the loading platform 4 through a gap eliminating connecting mechanism I44 and a gap eliminating connecting mechanism II 45.
The flight simulation system 1 generates a disturbed force sweep frequency instruction signal A (omega) (digital quantity) and writes the disturbed force sweep frequency instruction signal into a preset address of the optical fiber network system 2, the control system 3 of the aircraft steering engine dynamic stiffness test bed reads the force sweep frequency instruction signal from the preset address of the optical fiber network system 2 and superposes the force sweep frequency instruction signal with a loading force instruction B (omega) (digital quantity) sent by the control system 3, the superposed signal is converted into an analog quantity serving as a force control instruction through DA, the loading cylinder 41 executes the force instruction of the analog quantity and loads the steel bar 43, meanwhile, the force sensor 42 feeds back the force signal c (omega) (analog quantity) in real time, and the steering engine dynamic stiffness test bed control system 3 acquires c (omega) in real time, performs AD conversion and stores the acquired c (omega) and stores (A (omega) + B (omega)) (digital quantity). After the frequency sweeping is finished, drawing an amplitude-frequency characteristic curve and a phase-frequency characteristic curve of c (omega)/(A (omega) + B (omega)) to obtain the stability margin of the control system of the airplane steering engine dynamic stiffness test bed.
The specific test method comprises the following steps:
the first step is as follows: completing the installation of the steel bar 43 and the loading platform 4, wherein a first gap eliminating connecting mechanism 44 is used for fixedly connecting the steel bar 43 and the force sensor 42, and a second gap eliminating connecting mechanism 45 is used for fixedly connecting the steel bar 43 and one side of the loading platform 4;
the second step: the flight simulation system 1 generates an A (omega) (digital quantity) interference force frequency sweep instruction of 0.1 Hz-20 Hz, and writes the A (omega) (digital quantity) interference force frequency sweep instruction into a preset address of the optical fiber network system 2;
the third step: a flight control steering engine dynamic stiffness test bed control system 3 reads an A (omega) (digital quantity) interference force frequency sweep instruction of 0.1 Hz-20 Hz at a preset address of an optical fiber network system 2, and superposes the A (omega) (digital quantity) interference force frequency sweep instruction with a loading force instruction B (omega);
the fourth step: after DA conversion, the superposed (A (omega) + B (omega)) (digital quantity) generates a force control command, and the loading cylinder 41 executes an analog force command and loads the steel bar 43;
the fifth step: the force sensor 42 feeds back a force signal c (omega) (analog quantity) in real time, the flight control steering engine dynamic stiffness test bed control system 3 stores c (omega) (digital quantity) after AD conversion, and simultaneously stores (A (omega) + B (omega)) (digital quantity) in the test process in real time;
and a sixth step: after the sweep test is finished, an amplitude-frequency characteristic curve and a phase-frequency characteristic curve of c (omega)/(A (omega) + B (omega)) are drawn.
Claims (7)
1. The utility model provides an aircraft steering wheel dynamic stiffness test bench stability margin test system which characterized in that: the stability margin test system of the aircraft steering engine dynamic stiffness test bed consists of a flight simulation system (1), an optical fiber network system (2), a simulated aircraft steering engine and the aircraft steering engine dynamic stiffness test bed; the flight simulation system (1) is connected to the optical fiber network system (2), and a disturbed force scanning instruction A (omega) is written into the optical fiber network system (2); the airplane rudder maneuvering rigidity test bed consists of an airplane rudder maneuvering rigidity test bed control system (3) and a loading platform (4) to form a closed-loop control system, and a force signal c (omega) is fed back to the airplane rudder maneuvering rigidity test bed control system (3) in real time by the loading platform (4); the control system (3) of the aircraft rudder maneuvering rigidity test bed reads a disturbed force scanning instruction A (omega) from a preset address of the optical fiber network system (2), and the disturbed force scanning instruction A and a loading force instruction B (omega) generated by the control system are integrated to form a force control instruction;
the test method comprises the following test steps:
step1: completing the installation of the loading platform (4);
step2: the flight simulation system (1) generates an A (omega) interference force frequency sweep instruction and writes the A (omega) interference force frequency sweep instruction into a reserved address of the optical fiber network system (2);
step3: the airplane rudder maneuvering rigidity test bed control system (3) reads an A (omega) interference force frequency sweep instruction at a preset address of the optical fiber network system (2), and superposes the A (omega) interference force frequency sweep instruction with a loading force instruction B (omega);
step4: the superimposed (A (omega) + (omega)) generates a force control command, and the loading table (4) executes the loading of the force;
step5: the loading table (4) feeds back a force signal c (omega) in real time, the aircraft steering engine dynamic stiffness test table control system (3) stores c (omega), and simultaneously stores (A (omega) + B (omega)) in the test process in real time;
step6: after the sweep test is finished, an amplitude-frequency characteristic curve and a phase-frequency characteristic curve of c (omega)/(A (omega) + B (omega)) are drawn.
2. The stability margin test system for the aircraft steering engine dynamic stiffness test bed according to claim 1, characterized in that: the loading platform (4) is composed of a loading cylinder (41) and a force sensor (42), the loading cylinder (41) is used for receiving and executing a force control command sent by the control system (3) of the airplane steering engine dynamic stiffness test platform, and the force sensor (42) is used for feeding back a force signal c (omega) in real time.
3. The stability margin test system for the aircraft steering engine dynamic stiffness test bed according to claim 2, characterized in that: the force control instruction is formed by superposing a force sweep instruction signal A (omega) (digital quantity) and a loading force instruction B (omega) (digital quantity) generated by a dynamic stiffness test bed control system (3) of the airplane steering engine and then performing DA conversion.
4. The aircraft steering engine dynamic stiffness test bed stability margin test system according to claim 1, characterized in that: the simulated airplane steering engine adopts a steel bar (43).
5. The aircraft steering engine dynamic stiffness test bed stability margin test system according to claim 4, characterized in that: the airplane steering engine simulated by the steel bar (43) is arranged on the airplane steering engine maneuvering rigidity test bed, and the connection mode is that the airplane steering engine is fixedly connected through a gap eliminating connection mechanism.
6. The stability margin test system for the aircraft steering engine dynamic stiffness test bed according to claim 5, wherein the stability margin test system comprises: the device is characterized in that the number of gap eliminating connecting mechanisms fixedly connected with the steering engine dynamic stiffness test bed of the airplane is two, wherein a first gap eliminating connecting mechanism (44) is used for fixedly connecting the steel bar (43) and the force sensor (42), and a second gap eliminating connecting mechanism (45) is used for fixedly connecting the steel bar (43) and one side of the loading platform (4).
7. The stability margin test system for the aircraft steering engine dynamic stiffness test bed according to claim 1, characterized in that: the frequency range of a force scanning instruction A (omega) for writing disturbance into the optical fiber network system (2) by the flight simulation system (1) is 0.1-20 Hz.
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