CN109703780B - Method for realizing control surface jamming in fly test of telex transport type airplane - Google Patents
Method for realizing control surface jamming in fly test of telex transport type airplane Download PDFInfo
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Abstract
A method for realizing control surface jamming in a fly test of an electric transport type airplane belongs to the field of aviation application, and the technical scheme of the invention is as follows: and a negative feedback active control theoretical method is utilized to realize the negative feedback of the control surface initial control instruction signal, so that the instruction signal is counteracted, and the control surface jamming in the flight test process is realized. The method provides important technical support for developing the sticking test of the control surface of the telex transport plane and solves the problem of the technical shortage of the sticking of the control surface. The method does not need to change the fly-by-wire flight control system, only utilizes the signal of the flight control system to carry out negative feedback control, and realizes the jamming of the control surface in the flight test process.
Description
Technical Field
The invention discloses a control surface jamming implementation method for a fly test of an telex transport plane, and belongs to the field of aviation application.
Background
The control surface jamming flight test is a flight test provision verification test carried out by a transport aircraft to verify the provisions of the 25.671 general rule (c) of the 25 th part of China civil aviation regulations (CCAR 25-R4). So far, China only develops the control plane jamming flight test of a branch passenger plane ARJ 21-700. Normally, the control surfaces of an aircraft are controlled entirely by the aircraft's flight control system. In the process of carrying out the flight test of the control surface jamming, how to make the control surface jamming of the airplane in a fixed deflection is a difficult point for carrying out the flight test.
ARJ21-700 aircraft can add jamming signal via the circuit between the steering wheel and the actuator controller to jam the control surface of the aircraft, i.e. the jamming signal can be considered to replace the control signal input by the pilot via the steering wheel, once the jamming signal is added, the pilot can not control the jammed control surface via the steering wheel. But this presents a problem. According to the control principle of the fly-by-wire transport type airplane, the control command finally sent to the flight control surface by the actuator controller comprises two parts of commands, one part of commands are commands input by a pilot through a steering column, and the other part of commands are command signals calculated by the main flight control computer receiving atmosphere data system. The jamming signal described above replaces only the driver's command signal. The flight control system of the ARJ21-700 airplane is not a modern electric flight control system, and the authority of the main flight control computer for receiving the command signal calculated by the air data system is limited, so that the method of adding a jamming signal through a line between a steering wheel and an actuator controller meets the requirement of a control surface jamming flight test of the airplane.
For the full electric transport aircraft type airplane with modern significance, the control surface blocking method of the ARJ21-700 airplane obviously cannot block the control surface in the flight test process. The main flight control computer receives the command signal calculated by the atmospheric data system and can continuously drive the control surface to deflect, so that the test requirement is not met.
The invention provides an effective method for carrying out the sticking flight test of the control surface of the telex transport type airplane, which can simultaneously disable the command input by a pilot through a steering column and the command signal calculated by an atmosphere data system received by a main flight control computer, so that the sticking of the pilot flight is in the deviation degree required by the test.
Disclosure of Invention
The invention aims to: the method for realizing the jamming of the control surface in the flight test of the telex transport type airplane is provided, and solves the problem that the control surface of the telex transport type airplane is jammed at a fixed deflection degree according to the requirement of a tester in the process of carrying out the jamming flight test of the control surface, and is not influenced by an instruction input by a pilot rod and an instruction signal calculated by a main flight control computer receiving an atmospheric data system.
The technical scheme of the invention is as follows:
a method for realizing jamming of a control surface in a fly test of a telex transport plane comprises the following steps:
step 1: designing a high-speed signal receiving, processing and sending module, wherein the high-speed signal receiving, processing and sending module has the functions of receiving an analog quantity signal, calculating the analog quantity signal, sending the analog quantity signal and storing data;
step 2: receiving an initial control instruction signal A of the control surface of the airplane by using a high-speed signal receiving, processing and sending module;
and step 3: calculating an initial control instruction signal A of the airplane control surface by using a high-speed signal receiving, processing and sending module, and multiplying the initial control instruction signal A of the airplane control surface by-1 to obtain a-A signal;
and 4, step 4: adding a required airplane control plane deflection signal B stored in the high-speed signal receiving and processing sending module to the-A signal by using the high-speed signal receiving and processing sending module to obtain an airplane control plane jamming signal C, wherein C is-A + B;
and 5: sending the C signal to an adder of an aircraft actuator controller through an injection port of the aircraft actuator controller by using a high-speed signal receiving, processing and sending module, and realizing the addition operation of a jamming signal C and an aircraft control surface initial control instruction signal A in the adder of the aircraft actuator controller to obtain an aircraft control surface final control instruction signal D, namely D is A + C is A + (-A + B) is B; the aircraft control surface deflection signal B is just a required jamming signal; thereby realizing the jamming of the control surface of the airplane;
step 6: establishing an airplane control surface rudder loop model, establishing an airplane control surface jamming simulation model on the airplane control surface rudder loop model, and performing a control surface jamming simulation test to realize airplane control surface jamming, namely verifying the feasibility of the method; meanwhile, the effectiveness of the method is further verified through a fly-by-wire fly-control iron bird stand test.
According to the implementation method for the control surface jamming in the flight test of the telex transport type airplane, the high-speed signal receiving, processing and sending module in the first step calculates the capacity for 1000 times per second, so that the initial control instruction signal A of the control surface of the airplane is completely offset.
According to the implementation method for the control plane jamming of the fly test of the telex transport type airplane, the high-speed signal receiving, processing and sending module in the fourth step can send the jamming signal C of the control plane of the airplane to the airplane test system, and the airplane test system records the jamming signal C.
According to the implementation method for the control surface jamming of the fly test of the telex transport type airplane, the high-speed signal receiving, processing and sending module in the step two can send the initial control instruction signal A of the control surface of the airplane to the airplane test system, and the airplane test system records the initial control instruction signal A.
The invention has the advantages that:
a) a method for realizing the jamming of a control surface of a telex transport type airplane does not need to change a telex flight control system, and only utilizes various control command signals and hardware of the telex flight control system to form a system;
b) the implementation method for the control surface jamming of the telex transport type airplane can quickly realize that the airplane is recovered to a normal airplane control state from the control surface jamming state;
c) the implementation approach of the implementation method of the control surface jamming of the telex transport plane is convenient and easy to implement on the plane.
Description of the drawings:
FIG. 1 is a schematic diagram of a fly-by-wire flight control system of a fly-by-wire transport type aircraft;
FIG. 2 is a schematic diagram of the actuator controller;
FIG. 3 is a schematic diagram of a method for realizing jamming of a control surface of a telex transport-type airplane;
FIG. 4 is a diagram of a control surface jamming simulation model;
FIG. 5 is a plot of aileron sticking simulation results;
FIG. 6 is a plot of an elevator sticking simulation result;
FIG. 7 is a diagram of rudder sticking simulation results;
FIG. 8 is a graph of the results of an aileron jammer test;
fig. 9 is a graph of the results of an elevator stuck iron bird bench test.
The specific implementation mode is as follows:
the present invention will be described in further detail with reference to the accompanying drawings.
The method comprises the following steps: and (5) analyzing the control principle of the fly-by-wire flight control system.
Under the normal control condition of the telex transport type airplane, a pilot controls control input equipment such as a steering wheel and the like, a displacement sensor measures deflection signals of the steering wheel and the like, the deflection signals are transmitted to an actuator for control through a line, and the actuator controller sends the signals to a main flight computer; the main flight computer receives a pilot operation instruction from the actuator controller on one hand, and also receives data from the atmospheric data system on the other hand, calculates an airplane control instruction in real time according to the data, and transmits the calculated instruction and the pilot operation instruction to the actuator controller after being superposed; the actuator controller transmits the command signal received from the main flight control computer to the flight control surface, so that the control surface deflects according to the command, and the airplane is controlled. The operation principle of the fly-by-wire operation system of the fly-by-wire transport type airplane is shown in the attached figure 1.
The actuator controller is an important hardware component of the electric flight control system, and the basic operation principle of the actuator controller is shown in fig. 2. The actuator controller receives an analog quantity signal from a steering input terminal such as a steering wheel, converts the signal into a digital quantity by a/D conversion, and then sends it to the main flight control computer. The main flight control computer sends the control surface initial control instruction to the actuator controller, and the control surface initial control instruction is finally sent to the control surface by the adder after D/A conversion. The actuator controller has a signal injection port for signal injection superposition.
Step two: the implementation process of the fly test control surface jamming implementation method of the telex transport type airplane.
a) Designing a high-speed signal receiving, processing and sending module, wherein the high-speed signal receiving, processing and sending module has the functions of receiving an analog quantity signal, calculating the analog quantity signal, sending the analog quantity signal and storing data; the computing power of the high-speed signal receiving, processing and sending module is at least 1000 times per second, so that the initial control instruction signal A of the control surface of the airplane is completely counteracted;
b) receiving an initial control instruction signal A of the control surface of the airplane by using a high-speed signal receiving, processing and sending module; the high-speed signal receiving, processing and sending module can send the initial control instruction signal A of the airplane control surface to an airplane test system, and the airplane test system records the initial control instruction signal A;
c) calculating an initial control instruction signal A of the airplane control surface by using a high-speed signal receiving, processing and sending module, and multiplying the initial control instruction signal A of the airplane control surface by-1 to obtain a-A signal;
d) adding a required airplane control plane deflection signal B stored in the high-speed signal receiving and processing sending module to the-A signal by using the high-speed signal receiving and processing sending module to obtain an airplane control plane jamming signal C, wherein C is-A + B; the high-speed signal receiving, processing and sending module can send the aircraft control surface jamming signal C to the aircraft testing system, and the aircraft testing system records the jamming signal C.
e) Sending the C signal to an adder of an aircraft actuator controller through an injection port of the aircraft actuator controller by using a high-speed signal receiving, processing and sending module, and realizing the addition operation of a jamming signal C and an aircraft control surface initial control instruction signal A in the adder of the aircraft actuator controller to obtain an aircraft control surface final control instruction signal D, namely D is A + C is A + (-A + B) is B; the aircraft control surface deflection signal B is just a required jamming signal; thereby realizing the jamming of the control surface of the airplane;
the above process realizes negative feedback of the control surface initial control instruction through the signal receiving, processing and sending module. The signal A of the 'control surface initial control instruction signal' is the sum of an instruction input by a driver through a steering column and an instruction signal calculated by an atmosphere data system received by a main flight control computer, so that the signal A is invalid, and the control surface jamming is realized. The principle of the implementation method of the control surface jamming of the fly-by-wire transport type airplane is shown in the attached figure 3.
Step three: simulation verification of the method for realizing the jamming of the control surface of the telex transport plane.
And carrying out simulation verification aiming at the implementation method of the jamming of the control surface of the telex transport plane. Firstly, a rudder loop mathematical model of a control surface of an fly-by-wire transport type airplane is established, wherein the rudder loop mathematical model comprises airplane ailerons, elevators and rudders.
Secondly, a simulation model of the jamming of the control surface of the telex transport plane is established, and the simulation model of the jamming of the control surface is shown in figure 4. And (3) respectively carrying out sticking simulation tests on the ailerons, the elevators and the rudders, and theoretically verifying the feasibility of the method. Fig. 5 shows the aileron sticking simulation result, fig. 6 shows the elevator sticking simulation result, and fig. 7 shows the rudder sticking simulation result. It can be seen from the figure that the control surface is deflected before the jamming signal is not added, and after the jamming signal is added, the control surface can be stably kept at a fixed deflection, namely, jamming is formed.
Step four: the method for realizing the jamming of the control surface of the fly-by-wire transport type airplane is used for carrying out test verification on the fly-by-wire flight control iron bird stand.
Further test verification of the fly-by-wire flight control iron bird stand is carried out by aiming at the method for realizing the jamming of the control surface of the fly-by-wire transport type airplane. Fig. 8 shows the aileron blocking bird table test results and fig. 9 shows the elevator blocking bird table test results. It can be seen from the figure that after the jamming signal is added, the control surface can basically jam in the skewness required by the tester without being influenced by the command input by the steering column and the command signal calculated by the air data system received by the main flight control computer.
Claims (4)
1. A control surface jamming implementation method for a fly test of an electric transport type airplane is characterized by comprising the following steps:
step 1: designing a high-speed signal receiving, processing and sending module, wherein the high-speed signal receiving, processing and sending module has the functions of receiving an analog quantity signal, calculating the analog quantity signal, sending the analog quantity signal and storing data;
step 2: receiving an initial control instruction A of the control surface of the airplane by using a high-speed signal receiving, processing and sending module;
and step 3: calculating an initial control instruction signal A of the airplane control surface by using a high-speed signal receiving, processing and sending module, and multiplying the initial control instruction signal A of the airplane control surface by-1 to obtain a-A signal;
and 4, step 4: adding a required airplane control plane deflection signal B stored in the high-speed signal receiving and processing sending module to the-A signal by using the high-speed signal receiving and processing sending module to obtain an airplane control plane jamming signal C, wherein C is-A + B;
and 5: sending the aircraft control surface jamming signal C to an adder of an aircraft actuator controller through an injection port of the aircraft actuator controller by using a high-speed signal receiving, processing and sending module, and realizing the addition operation of the aircraft control surface jamming signal C and an aircraft control surface initial control instruction signal A in the adder of the aircraft actuator controller to obtain an aircraft control surface final control instruction signal D, namely D is A + C is A + (-A + B) is B; the aircraft control surface deflection signal B is just a required jamming signal; thereby realizing the jamming of the control surface of the airplane;
step 6: establishing an airplane control surface rudder loop model, establishing an airplane control surface jamming simulation model on the airplane control surface rudder loop model, and performing a control surface jamming simulation test to realize airplane control surface jamming, namely verifying the feasibility of the method; meanwhile, the effectiveness of the method is further verified through a fly-by-wire fly-control iron bird stand test.
2. The method for realizing the jamming of the control surface in the flight test of the fly-by-wire transport type airplane according to claim 1, wherein the high-speed signal receiving, processing and sending module calculates the capacity to 1000 times per second, so that the initial control command signal A of the control surface of the airplane is completely counteracted.
3. The method for realizing the control surface jamming in the fly test of the fly-by-wire transport type airplane according to claim 1, wherein the high-speed signal receiving, processing and sending module can send the jamming signal C of the control surface of the airplane to an airplane test system, and the airplane test system records the jamming signal C.
4. The method for realizing the control surface jamming in the fly test of the fly-by-wire transport type airplane according to claim 1, wherein the high-speed signal receiving, processing and sending module can send the initial control instruction signal A of the control surface of the airplane to an airplane test system, and the airplane test system records the initial control instruction signal A.
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| CN112255476A (en) * | 2020-09-22 | 2021-01-22 | 兰州万里航空机电有限责任公司 | Automatic control circuit applied to aircraft rudder surface lock |
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