CN110803297B - Airworthiness test method for single-shot performance of CCAR29 helicopters - Google Patents
Airworthiness test method for single-shot performance of CCAR29 helicopters Download PDFInfo
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- CN110803297B CN110803297B CN201910987013.5A CN201910987013A CN110803297B CN 110803297 B CN110803297 B CN 110803297B CN 201910987013 A CN201910987013 A CN 201910987013A CN 110803297 B CN110803297 B CN 110803297B
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Abstract
The invention belongs to the technical field of helicopter single-shot flight performance tests, and relates to a airworthiness verification method suitable for flight performance of CCAR29 helicopters. By comparing the change of the rotating speed of the rotor wing along with the time in the process of real single-shot and simulation single-shot, the airworthiness verification that the single-shot flight performance of the helicopter is completed by replacing the real single-shot with the simulation single-shot is achieved. Therefore, the attenuation of the real single test to the performance of the engine and the extension of the test period are effectively reduced. Meanwhile, the validity of the test flight data is greatly improved, and the test flight data is approved by the airworthiness authority.
Description
Technical Field
The invention belongs to the technical field of helicopter single-engine flight performance tests, and relates to a seaworthiness verification method suitable for flight performance of CCAR29 helicopters, in particular to a seaworthiness test method for single-engine performance of CCAR29 double-engine helicopters.
Background
In the process of obtaining evidence of airworthiness of a double-engine helicopter, how to prove that the performance of the helicopter can ensure safe flight when one engine fails under any working condition is a more complex problem. The applicant can generally adopt a method of actually shutting down an engine to carry out a typical performance test and then combining the performance test with analysis, but the method hardly comprises all the operating conditions of the helicopter. Insufficient test of the test points is usually difficult to be approved by the airworthiness authorities for data validity, and excessive selection of the test points can lead to early decline of the performance of the engine, thereby causing additional test cost and increase of the test period. Therefore, an alternative method is needed in airworthiness verification, the performance of the engine during single-shot failure is simulated as truly as possible on the premise that damage to the engine is reduced and the test efficiency is improved, and verification of a helicopter single-shot performance test is completed.
Disclosure of Invention
The purpose of the invention is: the airworthiness verification method for the single-engine performance of the CCAR29 helicopters is provided, and the technical problems that in the existing single-engine performance test process, one engine needs to be really turned off, so that the maintenance cost of the engine is high, the test period is too long, and the efficiency is low are solved.
In order to solve the technical problem, the technical scheme of the invention is as follows:
a seaworthiness test method for single-shot performance of CCAR29 helicopters is characterized in that engine parameter debugging equipment is utilized to improve single-shot simulation precision of an engine to replace the real single-shot seaworthiness test for single-shot performance.
The engine parameter debugging equipment is used for debugging the parameters of the single-shot performance simulation of the engine in a mode of adjusting output voltage and impedance.
The airworthiness test method for the single-shot performance of the helicopter comprises the following steps of:
firstly, carrying out a real single-shot test in the air, recording test data and taking the test data as a reference;
secondly, setting initial engine parameters by using engine parameter debugging equipment,
thirdly, performing a simulation single-shot test in the air, and recording test data;
fourthly, because the torque and the rotating speed of the rotor wing directly reflect the change of the lifting force of the helicopter, the change condition of the power output of the helicopter when one engine fails can be effectively shown, so that a difference method for comparing the real single-shot torque and the simulated single-shot torque with the change curve of the rotating speed of the rotor wing along with time is adopted, the real single-shot curve is taken as a reference, and the simulated single-shot curve is obtained by adjusting the parameters of the engine and performing a simulated single-shot test until the change curves of the simulated single-shot and the real single-shot flight states tend to be consistent; the test result is used as a basis for carrying out a test by replacing a real single hair with a simulated single hair; fifthly, replacing a true single shot with a simulated single shot to carry out a helicopter single shot performance test;
and sixthly, repeating the first step to the fifth step after the helicopter test environment is changed, and completing single-shot performance test verification.
The engine parameters comprise power difference, power difference depth, power difference response time and engine revolution threshold correction value parameters, wherein the parameters can effectively adjust the response of the output power of the engine in a simulated single-shot state, so that the simulated single-shot state is closer to a real state;
recording through engine parameter acquisition equipment in the first step and the third step;
in the sixth step, the test environment comprises temperature and height.
Preferably, the second step further comprises a parameter display device connected with the engine parameter debugging device for real-time display.
The helicopter is a double-engine helicopter and adopts an engine with an electronic regulator.
The beneficial effects of the invention are:
the method is used for testing the single-shot flight performance of the CCAR29 helicopter, and solves the problems that the performance of an engine is damaged, the period is long, test data is insufficient and the like easily caused by using a real single shot. By utilizing the method provided by the invention, the following effects can be achieved:
1. the use frequency of real single shot is reduced, and the repair and transportation cost caused by engine replacement and overhaul is reduced;
2. the single-shot flight performance test period is shortened, and the flight test efficiency is improved;
3. the authenticity and the validity of flight test data are improved, so that the flight test verification is more sufficient;
the single-shot flight performance of the helicopter is better verified, the single-shot simulation precision of the helicopter is determined, and a more accurate theoretical basis is provided for helicopter operation.
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In order to more clearly illustrate the technical solution of the present invention, the drawings used in the embodiment of the present invention will be briefly explained. It is obvious that the drawings described below are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is a schematic diagram of the test of the present invention;
FIG. 2 is a flowchart of an airworthiness test under an environmental condition;
FIG. 3 is a plot comparing rotor speed variation for real single shot versus simulated single shot;
the system comprises a left engine 1, a right engine 2, a left engine EECU (engine electronic regulator) 3, a right engine EECU 4, a right engine EECU 5, a simulation single debugging device 6, a debugging parameter display device 7 and an engine parameter acquisition device 7.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features of various aspects of embodiments of the invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to one of ordinary skill in the art that the present invention may be practiced without these specific details. The following description of the embodiments is merely intended to better understand the present invention by illustrating examples thereof. The present invention is not limited to any particular arrangement or method provided below, but rather covers all product structures, any modifications, alterations, etc. of the method covered without departing from the spirit of the invention.
In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
A seaworthiness test method for single-shot performance of CCAR29 helicopters is mainly suitable for being provided with two electrically-controlled turboshaft engines with a simulation single-shot function, and the simulation single-shot function is used for replacing a real single-shot to carry out a seaworthiness test for single-shot flight performance of the helicopters.
In the first step of the test, the helicopter performs a real single-shot flight test, and the engine parameter acquisition equipment 7 is used for acquiring the curves of the engine torque and the rotor rotation speed along with the time change and taking the curves as the reference under the test condition.
And in the second step of the test, the engine parameters (including but not limited to power difference, power difference depth, power difference response time and the like) are debugged by using the simulation single-shot debugging device 5, and the display value of the adjusted parameters can be observed in real time through the debugging parameter display device 6.
And the third step of the test is to perform a flight test for simulating a single shot, and record parameters by using the engine parameter acquisition equipment 7.
And a fourth test step, judging the accuracy of debugging parameters by comparing the change conditions of the engine torque and the rotor wing rotating speed along with time in the real single-shot test data and the simulated single-shot test data, further finely adjusting to obtain the optimal adjustment coefficient of the simulated single-shot helicopter, and repeating the third step to obtain data again according to the situation.
And a fifth test step, regulating the engine to a final state in a simulation single-shot mode according to the final debugging result, and replacing the real single-shot mode to carry out the airworthiness test of the single-shot flight performance of the helicopter.
And in the sixth test step, because the power output of the engine is greatly influenced by the ambient temperature and the height, in order to ensure that the most accurate test data can be obtained under various flight working conditions, after the test environment is changed, the first step to the fourth step are repeated to obtain the final debugging data.
The first embodiment is as follows: on the AC312E helicopter which is being proved, the applicant utilizes the method to develop the airworthiness verification test of the single-shot flight performance of the AC312E helicopter. Flight verification tests on plains, sub-plateaus, plateaus and high plateaus are respectively carried out at different temperatures. Figure 3 shows the variation of the rotor speed with time for simulated and real single-shot conditions. As shown in the figure 3, through debugging of the test equipment, the change conditions of the rotating speed of the rotor under the two conditions are basically equivalent, the accuracy of replacing a true single shot with a simulated single shot is effectively shown, and sufficient comparison is provided for developing subsequent tests.
The test result shows that the single-shot flight test carried out by the method reduces the real single-shot flight time by more than 70 percent, shortens the whole test period by more than 50 percent, and reduces the test cost by tens of millions of yuan RMB. The precision of the test data is approved by the China Civil Aviation Administration (CAAC), and the conformity verification of relevant airworthiness terms is completed. The method is approved by China civil aviation administration, and can be popularized in single-shot flight performance airworthiness verification work of other CCAR29 helicopters in the future.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (4)
1. A airworthiness test method for single-shot performance of CCAR29 helicopters is characterized by comprising the following steps: the airworthiness test method for the single-shot performance of the helicopter utilizes the engine parameter debugging equipment to improve the single-shot simulation precision of the engine to replace the real single-shot airworthiness test for the single-shot performance;
the engine parameter debugging equipment is used for debugging the parameters of the engine simulation single-shot performance in a mode of adjusting output voltage and impedance;
the airworthiness test method comprises the following steps:
firstly, carrying out a real single-shot test in the air, recording test data and taking the test data as a reference;
secondly, setting initial engine parameters by using engine parameter debugging equipment; the engine parameters include: power difference, power difference depth, power difference response time and engine revolution threshold correction value parameters;
thirdly, performing a simulation single-shot test in the air, and recording test data;
comparing the difference between the torque of the real single shot and the torque of the simulated single shot and the change curve of the rotating speed of the rotor wing along with time, and obtaining a simulated single shot curve by adjusting the engine parameters and performing a simulated single shot test by taking the real single shot curve as a reference until the change curves of the simulated single shot and the real single shot in two flight states tend to be consistent;
fifthly, replacing a true single shot with a simulated single shot to carry out a helicopter single shot performance test;
sixthly, after the test environment of the helicopter is changed, repeating the first step to the fourth step to complete single-shot performance test verification; the test environment includes temperature, altitude.
2. The airworthiness test method for the single-shot performance of the CCAR29 helicopters according to claim 1, characterized in that: and recording in the first step and the third step through engine parameter acquisition equipment.
3. The airworthiness test method for the single-shot performance of the CCAR29 helicopters according to claim 1, characterized in that: and the second step also comprises a parameter display device which is connected with the engine parameter debugging device for real-time display.
4. The airworthiness test method for the single-shot performance of CCAR29 helicopters according to claim 1, characterized in that: the helicopter is a double-engine helicopter and adopts an engine with an electronic regulator.
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| CN112373721B (en) * | 2020-11-03 | 2023-02-10 | 哈尔滨飞机工业集团有限责任公司 | Method for adjusting reference of main-rotor steering engine of helicopter in ground state |
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