CN113377027A - Aircraft propulsion system test system - Google Patents
Aircraft propulsion system test system Download PDFInfo
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- CN113377027A CN113377027A CN202110579994.7A CN202110579994A CN113377027A CN 113377027 A CN113377027 A CN 113377027A CN 202110579994 A CN202110579994 A CN 202110579994A CN 113377027 A CN113377027 A CN 113377027A
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- 238000012360 testing method Methods 0.000 title claims abstract description 47
- 238000004088 simulation Methods 0.000 claims abstract description 39
- 230000000875 corresponding effect Effects 0.000 claims abstract description 28
- 230000005540 biological transmission Effects 0.000 claims description 11
- 230000001276 controlling effect Effects 0.000 abstract description 4
- 230000015572 biosynthetic process Effects 0.000 description 8
- 238000003786 synthesis reaction Methods 0.000 description 8
- 238000013461 design Methods 0.000 description 7
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- 238000004891 communication Methods 0.000 description 3
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- 239000010687 lubricating oil Substances 0.000 description 3
- 230000002238 attenuated effect Effects 0.000 description 2
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- 238000012986 modification Methods 0.000 description 2
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- 238000006467 substitution reaction Methods 0.000 description 2
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B17/00—Systems involving the use of models or simulators of said systems
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Abstract
The application belongs to the technical field of aircraft propulsion system tests, concretely relates to aircraft propulsion system test system, include: the airplane state monitor can output airplane throttle control commands and airplane engine control commands; an aircraft accelerator mechanical connecting rod and an engine main pump simulation device; the aircraft throttle control assembly, the aircraft state monitor, the aircraft throttle mechanical connecting rod and the engine main pump simulation device are used for controlling the aircraft throttle mechanical connecting rod and the engine main pump simulation device to perform corresponding actions according to the aircraft throttle control instruction; an aircraft engine simulator; the aircraft engine information comprehensive computer is connected with the aircraft state monitor and the aircraft engine simulator so as to control the operation of the engine simulator according to the aircraft engine control instruction and receive a feedback signal of the operation of the aircraft engine simulator, and the aircraft state monitor outputs corresponding aircraft state parameters based on the feedback signal.
Description
Technical Field
The application belongs to the technical field of aircraft propulsion system tests, and particularly relates to an aircraft propulsion system test system.
Background
The aircraft propulsion system mainly comprises an aircraft engine automatic starting device, an engine information comprehensive computer, an accelerator control assembly and an engine, the reasonability of the design of the aircraft propulsion system is directly related to the flight safety of the aircraft, a ground test is carried out on the aircraft engine, the realization of the function and the static/dynamic performance index of the aircraft engine are verified, corresponding parameters are obtained, data support can be provided for the improvement design of the aircraft propulsion system, and the aircraft propulsion system is particularly significant for the improvement design of the unmanned aerial vehicle aircraft propulsion system.
Currently, an effective technical scheme capable of performing an aircraft propulsion system test, verifying the realization of the functions and the static/dynamic performance indexes thereof, and acquiring corresponding parameters is lacking.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft propulsion system test system to overcome or mitigate at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
an aircraft propulsion system test system comprising:
the airplane state monitor can output airplane throttle control commands and airplane engine control commands;
an aircraft accelerator mechanical connecting rod and an engine main pump simulation device;
the aircraft throttle control assembly, the aircraft state monitor, the aircraft throttle mechanical connecting rod and the engine main pump simulation device are used for controlling the aircraft throttle mechanical connecting rod and the engine main pump simulation device to perform corresponding actions according to the aircraft throttle control instruction;
an aircraft engine simulator;
the aircraft engine information comprehensive computer is connected with the aircraft state monitor and the aircraft engine simulator so as to control the operation of the engine simulator according to the aircraft engine control instruction and receive a feedback signal of the operation of the aircraft engine simulator, and the aircraft state monitor outputs corresponding aircraft state parameters based on the feedback signal.
According to at least one embodiment of the application, in the aircraft propulsion system test system, the aircraft state monitor can output an aircraft engine automatic start control command;
the aircraft propulsion system test system further comprises:
the automatic starting device of the aircraft engine is connected with the information comprehensive computer of the aircraft engine; the aircraft engine information comprehensive computer can control the aircraft engine automatic starting device to perform corresponding actions according to the aircraft engine automatic starting control instruction.
According to at least one embodiment of the present application, in the above-mentioned aircraft propulsion system test system, the aircraft throttle mechanical link and engine main pump simulation apparatus includes:
an airplane accelerator load simulation torque motor;
the torque sensor is connected with an output shaft of the airplane throttle load simulation torque motor and the airplane state monitor; the airplane state monitor can control the torque output of the airplane throttle load simulation torque motor according to the feedback signal of the torque sensor;
the transmission shaft is connected with the torque sensor at one end;
one end of the aircraft throttle mechanical connecting rod is connected with the aircraft throttle control component so as to carry out corresponding action under the control of the aircraft throttle control component;
and the encoder is connected with the other end of the transmission shaft, the other end of the aircraft throttle mechanical connecting rod and the aircraft state monitor so as to transmit the rotation angle of the aircraft throttle mechanical connecting rod to the aircraft state monitor.
According to at least one embodiment of the present application, in the above-mentioned aircraft propulsion system test system, the aircraft throttle mechanical link and engine main pump simulation apparatus further includes:
and one end of the coupler is connected with the torque sensor, and the other end of the coupler is connected with one end of the transmission shaft, which faces away from the encoder.
According to at least one embodiment of the present application, in the above-mentioned aircraft propulsion system test system, the aircraft throttle mechanical link and engine main pump simulation apparatus further includes:
the first bracket is connected with the aircraft throttle load simulation torque motor to support the aircraft throttle load simulation torque motor;
and the second bracket is connected with the encoder to support the encoder.
According to at least one embodiment of the present application, in the aircraft propulsion system test system described above, engine fault information can be configured in the engine simulator.
According to at least one embodiment of the present application, the aircraft propulsion system test system further includes:
the interface simulator is connected with the aircraft engine simulator and the aircraft engine information comprehensive computer, converts control signals of the aircraft engine information comprehensive computer to the engine into corresponding digital signals and transmits the digital signals to the aircraft engine simulator so as to control the operation of the engine simulator, and converts feedback signals of the operation of the aircraft engine simulator into corresponding sensor signals and transmits the sensor signals to the aircraft engine information comprehensive computer.
Drawings
FIG. 1 is a schematic diagram of an aircraft propulsion system test system provided by an embodiment of the present application;
FIG. 2 is a schematic diagram of an aircraft throttle mechanical link and an engine main pump simulation device provided by an embodiment of the application;
FIG. 3 is a schematic diagram of an interface simulator and an aircraft engine simulator thereof, and an aircraft engine information synthesis computer provided in an embodiment of the application;
wherein:
1-an aircraft state monitor; 2, an aircraft accelerator mechanical connecting rod and an engine main pump simulation device; 3-aircraft throttle control assembly; 4-an aircraft engine simulator; 5-an aircraft engine information comprehensive computer; 6-simulating a moment motor for the throttle load of the airplane; 7-a torque sensor; 8-a transmission shaft; 9-mechanical connecting rod of airplane throttle; 10-an encoder; 11-interface emulator; 12-automatic starting means of the aircraft engine; 13-a coupler; 14-a first scaffold; 15-second support.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1 to 3.
An aircraft propulsion system test system comprising:
the airplane state monitor 1 can output airplane throttle control commands and airplane engine control commands;
an aircraft accelerator mechanical connecting rod and an engine main pump simulation device 2;
the aircraft throttle control assembly 3, the aircraft state monitor 1, the aircraft throttle mechanical connecting rod and the engine main pump simulation device 2 are used for controlling the aircraft throttle mechanical connecting rod and the engine main pump simulation device 2 to perform corresponding actions according to an aircraft throttle control command;
the aircraft engine simulator 4 is embedded with an aircraft simulation model;
and the aircraft engine information comprehensive computer 5 is connected with the aircraft state monitor 1 and the aircraft engine simulator 4 so as to be capable of controlling the operation of the engine simulator 4 according to the aircraft engine control instruction and receiving a feedback signal of the operation of the aircraft engine simulator 4, and the aircraft state monitor 1 outputs corresponding aircraft state parameters based on the feedback signal.
With respect to the aircraft propulsion system test system disclosed in the above embodiments, it will be appreciated by those skilled in the art that, the airplane throttle control component 3 is designed to control an airplane throttle mechanical connecting rod and an engine main pump simulation device 2 to perform corresponding actions according to an airplane throttle control command output by an airplane state monitor 1, an airplane engine information comprehensive computer 5 controls an engine simulator 4 to operate according to the airplane engine control command output by the airplane state monitor 1, the airplane state monitor 1 receives a feedback signal of the operation of the airplane engine simulator 4 based on the airplane engine information comprehensive computer 5 and outputs corresponding airplane state parameters, therefore, the ground test can be efficiently carried out on the aircraft propulsion system, the realization of the function of the aircraft propulsion system and the static/dynamic performance index of the aircraft propulsion system are verified, corresponding parameters are obtained, and data support is provided for the improved design of the aircraft propulsion system.
In some optional embodiments, in the above-mentioned aircraft propulsion system test system, the aircraft state parameters include aircraft flight altitude, aircraft flight speed, aircraft engine throttle PLA, aircraft engine speed, aircraft engine thrust, aircraft engine exhaust temperature
In some optional embodiments, in the above-mentioned aircraft propulsion system test system, the aircraft state monitor 1 can output an aircraft engine automatic start control command;
the aircraft propulsion system testing system further comprises:
the automatic starting device 12 of the aircraft engine is connected with the information comprehensive computer 5 of the aircraft engine; the aircraft engine information comprehensive computer 5 can control the aircraft engine automatic starting device 12 to perform corresponding actions according to the aircraft engine automatic starting control instruction.
In some optional embodiments, in the above-mentioned aircraft propulsion system test system, the aircraft engine state monitor 1 may be designed to communicate with the aircraft engine information synthesis computer 5 through two GJB289A buses, communicate with the aircraft throttle control component 3 through three RS-422 buses, connect with the aircraft throttle mechanical link and the engine main pump simulation device 2 through hard wires, test communication between the aircraft engine information synthesis computer 5 and the aircraft throttle control component 3 through two RS-422 buses, test communication between the aircraft engine information synthesis computer 5 and the aircraft engine simulator 4 through four RS-422 buses, and test an output signal from the aircraft engine information synthesis computer 5 to the aircraft engine automatic starting device 12 through hard wires. In addition, the aircraft engine state monitor 1 and the aircraft engine simulator 4 can be connected through the ethernet and used for file transfer during development, maintenance and update of a system and transmission of relevant data during testing.
In some optional embodiments, in the above aircraft propulsion system test system, the aircraft throttle mechanical link and engine main pump simulation apparatus 2 includes:
the aircraft accelerator load simulation torque motor 6 simulates the load generated by the action of the aircraft accelerator according to the output torque;
the torque sensor 7 is connected with an output shaft of the airplane throttle load simulation torque motor 6 and the airplane state monitor 1; the airplane state monitor 1 can control the torque output of the airplane accelerator load simulation torque motor 6 according to the feedback signal of the torque sensor 7;
a transmission shaft 8, one end of which is connected with a torque sensor 7;
one end of the aircraft throttle mechanical connecting rod 9 is connected with the aircraft throttle control component 3 so as to perform corresponding actions under the control of the aircraft throttle control component 3;
and the encoder 10 is connected with the other end of the transmission shaft 8, the other end of the aircraft throttle mechanical connecting rod 9 and the aircraft state monitor 1 so as to transmit the rotation angle of the aircraft throttle mechanical connecting rod 9, namely the rotation angle of the aircraft throttle to the aircraft state monitor 1.
In some optional embodiments, in the above aircraft propulsion system test system, the aircraft throttle mechanical link and engine main pump simulation apparatus 2 further includes:
and one end of the coupler 13 is connected with the torque sensor 7, and the other end of the coupler is connected with one end of the transmission shaft 8, which is back to the encoder 10.
In some optional embodiments, in the above aircraft propulsion system test system, the aircraft throttle mechanical link and engine main pump simulation apparatus 2 further includes:
the first bracket 14 is connected with the aircraft throttle load simulation torque motor 6 to support the aircraft throttle load simulation torque motor 6;
and a second support 15 coupled to the encoder 10 to support the encoder 10.
In some optional embodiments, in the above-mentioned aircraft propulsion system test system, the engine simulator 4 can be configured with engine fault information, so as to simulate the operation state of the aircraft engine under fault.
In some optional embodiments, the above aircraft propulsion system test system further includes:
and the interface simulator 11 is connected with the aircraft engine simulator 4 and the aircraft engine information comprehensive computer 5, converts the control signals of the aircraft engine information comprehensive computer 5 to the engine into corresponding digital signals and transmits the digital signals to the aircraft engine simulator 4 so as to control the operation of the engine simulator 4, and converts the feedback signals of the operation of the aircraft engine simulator 4 into corresponding sensor signals and transmits the sensor signals to the aircraft engine information comprehensive computer 5.
With respect to the aircraft propulsion system test system disclosed in the above embodiments, it will be understood by those skilled in the art that the aircraft engine simulator 4 simulates the actual aircraft engine operation, outputs the aircraft engine operation feedback signal in the form of digital quantity, and inputs the aircraft engine control signal in the form of digital quantity, which is not in accordance with the input and output signal form of the actual engine, and cannot be directly connected to the aircraft engine information synthesis computer 5, the interface simulator 11 is designed to convert the control signal of the aircraft engine information synthesis computer 5 to the engine into the corresponding digital signal to be transmitted to the aircraft engine simulator 4, to control the operation of the engine simulator 4, and convert the feedback signal of the operation of the aircraft engine simulator 4 into the corresponding sensor signal to be transmitted to the aircraft engine information synthesis computer 5, therefore, the matching conversion of the signals between the aircraft engine simulator 4 and the aircraft engine information comprehensive computer 5 can be realized.
The sensor signals to be simulated by the interface simulator 11 mainly include an engine inlet temperature sensor signal, a turbine rear gas temperature sensor signal, an engine vibration sensor signal, an engine inlet static pressure sensor signal, an engine lubricating oil pressure sensor signal, a low-pressure rotor rotating speed sensor signal, a high-pressure rotor rotating speed sensor signal, a lubricating oil normal and anti-surge power supply switching value signal and the like, and the control signals to be simulated mainly include 2 paths of AD signals.
The interface simulator 11CPU may adopt TMS320F2808 core board, ± 12V analog electric, and +5V digital electric, and communicate with the aircraft engine simulator 4 in RS232 communication mode, the analog mode adopted is as follows:
signals of an engine lubricating oil pressure sensor and signals of an engine inlet static pressure sensor are output by a DAC through a reverse amplifier;
the signal of the engine vibration sensor is reversely attenuated by the DAC and the operational amplifier 1/5;
after the turbine, the signal of the gas temperature sensor is attenuated by a DAC and then by an operational amplifier 1/100, and is added with the output of a subtracter;
the signals of the engine inlet temperature sensor are electronically synthesized into R0/1-K, wherein R0 is 30 ohms, and K is 0-1;
signals of the low-voltage rotor speed sensor and the high-voltage rotor speed sensor are output by PWM, the duty ratio is 50%, and the amplitude is controlled by DA;
AD input is 0-5V;
the oil is normal and the surge-proof power switch value signal is converted into 5VTTL level output through 245.
For the aircraft propulsion system test system disclosed in the above embodiment, those skilled in the art can understand that the ground test of the aircraft propulsion system is realized in a semi-physical simulation manner, the implementation of the aircraft propulsion system function and the static/dynamic performance index thereof are verified, corresponding parameters are obtained, data support is provided for the improved design of the aircraft propulsion system, and the aircraft propulsion system test system has higher efficiency and accuracy.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Furthermore, those skilled in the art will appreciate that the various components of the aircraft propulsion system test system disclosed in the embodiments of the present application can be implemented as electronic hardware, computer software, or combinations of both, and that, to clearly illustrate this interchangeability of hardware and software, functions described herein are generally implemented as hardware or software, and that, depending on the particular application and design constraints imposed on the solution, those skilled in the art will be able to select different approaches to implement the described functions for each particular application and its practical constraints, but such implementation should not be considered as beyond the scope of the present application.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (7)
1. An aircraft propulsion system test system, comprising:
the airplane state monitor (1) can output airplane throttle control commands and airplane engine control commands;
an aircraft accelerator mechanical connecting rod and an engine main pump simulation device (2);
the aircraft throttle control assembly (3) is connected with the aircraft state monitor (1), the aircraft throttle mechanical connecting rod and the engine main pump simulation device (2) so as to control the aircraft throttle mechanical connecting rod and the engine main pump simulation device (2) to perform corresponding actions according to an aircraft throttle control command;
an aircraft engine simulator (4);
the aircraft engine information comprehensive computer (5) is connected with the aircraft state monitor (1) and the aircraft engine simulator (4) so as to control the operation of the engine simulator (4) according to an aircraft engine control instruction and receive a feedback signal of the operation of the aircraft engine simulator (4), and the aircraft state monitor (1) outputs corresponding aircraft state parameters based on the feedback signal.
2. An aircraft propulsion system test system according to claim 1,
the airplane state monitor (1) can output an automatic starting control instruction of an airplane engine;
the aircraft propulsion system testing system further comprises:
the automatic starting device (12) of the aircraft engine is connected with the information comprehensive computer (5) of the aircraft engine; the aircraft engine information comprehensive computer (5) can control an aircraft engine automatic starting device (12) to perform corresponding actions according to the aircraft engine automatic starting control instruction.
3. An aircraft propulsion system test system according to claim 1,
aircraft throttle mechanical connecting rod and engine main pump analogue means (2) include:
an airplane throttle load simulation torque motor (6);
the torque sensor (7) is connected with an output shaft of the aircraft accelerator load simulation torque motor (6) and the aircraft state monitor (1); the airplane state monitor (1) can control the torque output of the airplane throttle load simulation torque motor (6) according to the feedback signal of the torque sensor (7);
the transmission shaft (8) is connected with the torque sensor (7) at one end;
one end of the aircraft throttle mechanical connecting rod (9) is connected with the aircraft throttle control component (3) so as to perform corresponding actions under the control of the aircraft throttle control component (3);
and the encoder (10) is connected with the other end of the transmission shaft (8), the other end of the aircraft throttle mechanical connecting rod (9) and the aircraft state monitor (1) so as to transmit the rotation angle of the aircraft throttle mechanical connecting rod (9) to the aircraft state monitor (1).
4. An aircraft propulsion system test system according to claim 3,
aircraft throttle mechanical connecting rod and engine main pump analogue means (2) still include:
and one end of the coupler (13) is connected with the torque sensor (7), and the other end of the coupler is connected with one end of the transmission shaft (8) back to the encoder (10).
5. An aircraft propulsion system test system according to claim 3,
aircraft throttle mechanical connecting rod and engine main pump analogue means (2) still include:
the first bracket (14) is connected with the aircraft throttle load simulation torque motor (6) to support the aircraft throttle load simulation torque motor (6);
and a second support (15) connected with the encoder (10) to support the encoder (10).
6. An aircraft propulsion system test system according to claim 1,
engine fault information can be configured in the engine simulator (4).
7. An aircraft propulsion system test system according to claim 1,
further comprising:
the interface simulator (11) is connected with the aircraft engine simulator (4) and the aircraft engine information comprehensive computer (5), converts control signals of the aircraft engine information comprehensive computer (5) to the engine into corresponding digital signals and transmits the digital signals to the aircraft engine simulator (4) so as to control the operation of the engine simulator (4), and converts feedback signals of the operation of the aircraft engine simulator (4) into corresponding sensor signals and transmits the sensor signals to the aircraft engine information comprehensive computer (5).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110579994.7A CN113377027A (en) | 2021-05-26 | 2021-05-26 | Aircraft propulsion system test system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110579994.7A CN113377027A (en) | 2021-05-26 | 2021-05-26 | Aircraft propulsion system test system |
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