CN110803297A - Airworthiness test method for single-shot performance of CCAR29 helicopters - Google Patents

Abstract

The invention belongs to the technical field of helicopter single-engine flight performance testing, and relates to an airworthiness verification method suitable for the flight performance of CCAR 29 helicopters. The engine parameter debugging equipment is used to adjust the output voltage and impedance to adjust the parameters of the engine's simulated single-engine performance. The airworthiness test of single-engine performance is carried out to improve the single-engine simulation accuracy of the engine instead of the real single-engine. By comparing the change of rotor speed with time in the process of real single engine and simulated single engine, the airworthiness verification of helicopter single engine flight performance is achieved by using simulated single engine instead of real single engine. Thereby, the attenuation of engine performance and the prolongation of the test period of the real single-engine test are effectively reduced. At the same time, the validity of the test flight data has been greatly improved, and it has been recognized by the airworthiness authorities.

Description

An airworthiness test method for single engine performance of CCAR29 helicopters

technical field

The invention belongs to the technical field of helicopter single-engine flight performance test, relates to an airworthiness verification method suitable for CCAR29 helicopter flight performance, and in particular relates to an airworthiness test method for CCAR29 twin-engine helicopter single-engine performance.

Background technique

In the process of airworthiness certification of twin-engine helicopters, how to prove that when one engine fails under any operating conditions, the performance of the helicopter can ensure safe flight has always been a complicated problem. Generally, applicants will use the method of shutting down one engine for typical performance test and then combining analysis, but this method is difficult to cover all operating conditions of the helicopter. Insufficient test points are often difficult to be recognized by the airworthiness authorities for the validity of the data. Too many test points will lead to premature deterioration of engine performance, resulting in additional test costs and increased test cycles. Therefore, an alternative method is needed for airworthiness verification. On the premise of reducing damage to the engine and improving the test efficiency, the performance of the engine when a single engine fails is simulated as realistically as possible, and then the verification of the single engine performance test of the helicopter is completed.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide an airworthiness verification method for the single-engine performance of CCAR29 helicopters, so as to solve the problem of high engine maintenance cost, excessively long test cycle, and high cost of engine maintenance caused by the need to actually shut down one engine during the current single-engine performance test process. Inefficient technical issues.

In order to solve this technical problem, the technical scheme of the present invention is:

An airworthiness test method for single-engine performance of CCAR29 helicopters, the airworthiness test method for single-engine performance of helicopters utilizes engine parameter debugging equipment to improve the simulation accuracy of single-engine engine instead of real single-engine to carry out airworthiness of single-engine performance test.

The engine parameter debugging equipment adopts the method of adjusting the output voltage and impedance to debug the parameters of the simulated single-engine performance of the engine.

The airworthiness test method of helicopter single engine performance includes the following steps:

The first step is to conduct a real single-shot test in the air, record the test data, and use it as a benchmark;

The second step is to use the engine parameter debugging equipment to set the initial engine parameters,

The third step is to conduct a simulated single-shot test in the air and record the test data;

The fourth step, since the torque and rotor speed directly reflect the change of the lift of the helicopter, it can effectively show the change of the power output of the helicopter when an engine fails. Therefore, the torque and rotor speed of the real single engine and the simulated single engine are compared with time. Based on the real single-engine curve, the simulated single-engine curve is obtained by adjusting the engine parameters and performing simulated single-engine tests until the variation curves of the simulated single-engine and real single-engine flight conditions tend to be consistent. ; Use this as the basis for the simulated single-engine to replace the real single-engine for the test; the fifth step is to use the simulated single-engine instead of the real single-engine to carry out the helicopter single-engine performance test;

Step 6. After the helicopter test environment changes, repeat steps 1 to 5 to complete the single-engine performance test verification.

The engine parameters include power difference, power difference depth, power difference response time and engine revolution threshold correction value parameters, wherein the above parameters can effectively adjust the response of the output power of the engine in the simulated single-engine state, so that the simulated single-engine is more accurate. close to the real state;

The first and third steps are recorded by the engine parameter acquisition equipment;

The test environment described in the sixth step includes temperature and altitude.

Preferably, the second step further includes a parameter display device connected to the engine parameter debugging device for real-time display.

Said helicopter is a twin-engine helicopter, using an engine with an electronic regulator.

The beneficial effects of the present invention are:

The method of the invention is used in the single-engine flight performance test of the CCAR29 helicopter, and solves the problems that the use of a real single-engine easily leads to engine performance damage, a long cycle, and insufficient test data. Utilize the method mentioned in the present invention, the following effects can be achieved:

1. Reduce the frequency of use of the real single engine, and reduce the repair and transportation costs caused by engine replacement and overhaul;

2. Reduce the single-engine flight performance test cycle and improve the flight test efficiency;

3. Improve the authenticity and validity of the flight test data and make the flight test verification more sufficient;

It can better verify the single-engine flight performance of the helicopter, determine the accuracy of the single-engine simulation of the helicopter, and provide a more accurate theoretical basis for the operation of the helicopter.

Description of drawings

In order to illustrate the technical solutions implemented by the present invention more clearly, the following will briefly explain the accompanying drawings that need to be used in the examples of the present invention. Obviously, the drawings described below are only some embodiments of the present invention, and for those skilled in the art, other drawings can also be obtained from these drawings without creative effort.

Fig. 1 is the test principle diagram of the present invention;

Figure 2 is a flow chart of an airworthiness test in an environmental state;

Figure 3 is a comparison diagram of the rotor speed change under the condition of real single engine and simulated single engine;

Among them, 1. Left engine, 2. Right engine, 3. Left engine EECU (engine electronic regulator), 4. Right engine EECU, 5. Simulated single engine debugging equipment, 6. Debugging parameter display equipment, 7. Engine parameter collection equipment.

Detailed ways

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be described clearly and completely below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present invention.

The features of various aspects of the embodiments of the present 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 only for a better understanding of the present invention by illustrating examples of the invention. The present invention is not limited to any specific arrangements and methods provided below, but covers all product structures, any improvements, substitutions, and the like of methods covered without departing from the spirit of the present invention.

In the various drawings and the following description, well-known structures and techniques have not been shown in order to avoid unnecessarily obscuring the present invention.

An airworthiness test method for the single-engine performance of CCAR29 helicopters, which is mainly applicable to the installation of two electrically-controlled turboshaft engines with simulated single-engine function, and the use of simulated single-engine function to replace real single-engine to develop helicopter single-engine flight performance. Airworthiness test.

In the first step of the test, the helicopter conducts a real single-engine flight test, and uses the engine parameter acquisition device 7 to collect the curves of engine torque and rotor speed with time, and use this as the benchmark under this test condition.

In the second step of the test, use the simulated single-engine debugging equipment 5 to debug the engine parameters (including but not limited to: power difference, power difference depth, power difference response time, etc.), and the adjusted parameters can be observed in real time through the debugging parameter display device 6 display value.

In the third step of the test, a flight test simulating a single engine is performed, and the parameters are recorded by the engine parameter acquisition device 7 .

The fourth step of the test is to judge the accuracy of the debugging parameters by comparing the changes of engine torque and rotor speed with time in the real single-engine and simulated single-engine test data, and through further fine-tuning, obtain the best adjustment of the helicopter simulated single-engine coefficient, repeat the third step to obtain the data again if necessary.

In the fifth step of the test, according to the final debugging results, the simulated single engine of the engine is adjusted to the final state, and the single engine flight performance airworthiness test of the helicopter is carried out instead of the real single engine.

In the sixth step of the test, since the power output of the engine is greatly affected by the ambient temperature and altitude, in order to ensure that the most accurate test data can be obtained under various flight conditions, after changing the test environment, it is necessary to repeat the first step to the first step. Four steps to get the final debug data.

Embodiment 1: On the AC312E helicopter that is being certified, the applicant uses this method to carry out the airworthiness verification test of the single-engine flight performance of the AC312E helicopter. The plain, sub-altitude, high-altitude and high-altitude flight verification tests were carried out at different temperatures. Figure 3 shows the variation of rotor speed with time under simulated single-engine and real single-engine conditions. As shown in Figure 3, through the debugging of the test equipment, the changes of the rotor speed under the two conditions are basically the same, which effectively demonstrates the accuracy of using a simulated single engine instead of a real single engine, and provides sufficient information for subsequent experiments. Compared.

The test results show that the single-engine flight test using this method reduces the actual single-engine flight time by more than 70%, the overall test period is shortened by more than 50%, and the test cost can be reduced by tens of millions of yuan. The accuracy of the test data has been recognized by the Civil Aviation Administration of China (CAAC), and the compliance verification of the relevant airworthiness provisions has been completed. Approved by the Civil Aviation Administration of China, this method will also be promoted in the airworthiness verification work of other CCAR29 helicopters in the future.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited to this. Various equivalent modifications or substitutions should be included within the protection scope of the present invention.

Claims (8)

1. an airworthiness test method for single-engine performance of CCAR29 helicopters, it is characterized in that: the airworthiness test method of described helicopter single-engine performance utilizes engine parameter debugging equipment to improve engine single-engine simulation accuracy instead of real single-engine development Airworthiness test of single engine performance. 2. the airworthiness test method for single-engine performance of CCAR29 helicopters according to claim 1, is characterized in that: described engine parameter debugging equipment adopts the mode of regulating output voltage and impedance to simulate the parameters of single-engine performance of engine to debug. 3. The airworthiness test method for single-engine performance of CCAR29 helicopters according to claim 1, wherein the airworthiness test method comprises the following steps: The first step is to conduct a real single-shot test in the air, record the test data, and use it as a benchmark; The second step is to use the engine parameter debugging equipment to set the initial engine parameters; The third step is to conduct a simulated single-shot test in the air and record the test data; The fourth step is to compare the difference between the torque and rotor speed curves of the real single engine and the simulated single engine. Based on the real single engine curve, the simulated single engine curve is obtained by adjusting the engine parameters and performing the simulated single engine test. The change curves of simulated single-engine and real single-engine flight tend to be consistent; The fifth step is to use the simulated single engine instead of the real single engine to carry out the helicopter single engine performance test; Step 6: After the helicopter test environment changes, repeat steps 1 to 4 to complete the single-engine performance test verification. 4. The airworthiness test method for single-engine performance of CCAR29 helicopters according to claim 3, wherein the engine parameters include: power difference, power difference depth, power difference response time and engine revolution threshold correction value parameter. 5. The airworthiness test method for single-engine performance of CCAR29 helicopters according to claim 3, characterized in that: in the first step and the third step, it is recorded by an engine parameter collection device. 6 . The airworthiness test method for single-engine performance of a CCAR29 helicopter according to claim 3 , wherein the test environment in the sixth step includes temperature and altitude. 7 . 7. The airworthiness test method for the single-engine performance of CCAR29 helicopters according to any one of claims 3 to 6, characterized in that: in the second step, it also includes connecting with the engine parameter debugging equipment for real-time display Parameter display device. 8. The airworthiness test method for the single-engine performance of CCAR29 helicopters according to any one of claims 1 to 6, wherein the helicopter is a twin-engine helicopter and adopts an engine with an electronic regulator.

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