CN112133156B

CN112133156B - Single-shot failure training method for three-shot helicopter

Info

Publication number: CN112133156B
Application number: CN202011028824.1A
Authority: CN
Inventors: 王智; 田野; 杜春雨; 文丽辉; 吴丽媛; 陈瑞; 徐朝梁; 刘文琦; 王辉; 谌昱; 陈天杰
Original assignee: China Helicopter Research and Development Institute
Current assignee: China Helicopter Research and Development Institute
Priority date: 2020-09-25
Filing date: 2020-09-25
Publication date: 2023-02-28
Anticipated expiration: 2040-09-25
Also published as: CN112133156A

Abstract

The invention belongs to the field of helicopter power system design and discloses a single-shot failure training method for a three-shot helicopter. Compared with the current helicopter single-shot failure OEI training function, the simulation method can realize more real simulation of the real OEI flight state on the premise of further improving the flight safety. Therefore, the pilot can be trained more accurately to deal with the OEI flight state, the training function can be used for replacing the real OEI flight subjects in the test flight process, the test flight evidence obtaining period and cost are greatly reduced, and the flight safety of the risk subjects is improved. The design logic of the helicopter can be applied to not only three-engine helicopters, but also double-engine or multi-engine helicopters.

Description

Single-shot failure training method for three-shot helicopter

Technical Field

The invention belongs to the field of helicopter power system design, and relates to a single-shot failure training method for a three-shot helicopter.

Background

The single-failure OEI state of the helicopter is an important failure mode which can be met by multiple helicopters in use, and has great influence on the flight safety of the helicopter. When one engine of the multiple helicopters fails, the rest engines are automatically lifted to be in an OEI emergency power state so as to improve the power output of the rest engines. This power state places a severe restriction on the time of use, typically a single restriction of 2.5 minutes, and a severe cumulative time limit over the entire engine overhaul interval, TBO. Once exceeded, the shortened engine life results in early return to service and maintenance of the engine, resulting in substantial economic costs.

There is therefore a need to develop helicopter OEI training functionality to train pilots to meet emergency treatment of OEI conditions in flight. There are three main aspects to the focus and design requirements of the OEI training function:

(1) Safety: i.e. training the pilot in relatively safe conditions;

(2) The economic efficiency is as follows: i.e. without consuming the real OEI lifetime of the engine;

(3) Authenticity: namely, the OEI training function needs to be as close as possible to the real OEI condition;

in the OEI training function design of various helicopters at present, the design mainly focuses on economy and safety, and the design in the aspect of authenticity is relatively poor.

Disclosure of Invention

The purpose of the invention is as follows: compared with the currently widely adopted OEI training function, the helicopter single-shot failure OEI training function further improves the safety on the basis of ensuring the use economy and realizes more real simulation of the OEI state. The flight test system can be used for training pilots, and can replace most of real OEI flight in the flight test process to carry out performance verification, so that the flight test risk, the flight test period and the economic cost are greatly reduced.

The technical scheme of the invention is as follows:

a single failure training method for a three-helicopter comprises the following steps: the method comprises the following steps:

the method comprises the following steps: the pilot enters a single failure training state through a training switch; the training switch sends training signals to three engine electronic controllers;

step two: after the three engine electronic controllers receive the training signals, the power upper limits of the three engines are all controlled to be reduced to 2/3 of the single failure power;

step three: the electromechanical management system sends the set failure marks to three engine electronic controllers; the engine electronic controller adjusts the corresponding engine parameter signal into a real single failure parameter according to the failure mark and feeds the real single failure parameter back to the electromechanical management system for display; the failure mark is used for representing a failed engine number;

step four: the electromechanical management system displays a single failure training mark and alarm information on a cockpit display according to the states of the three engines after the third step so as to provide pilot training;

step five: the pilot exits the single shot disabled training state through the training switch.

Further, before the step one, the method further includes: and the electromechanical management system sends the engine installation loss to an engine electronic controller to correct the engine power parameter.

Further, in the second step, the three engine electronic controllers perform consistency judgment after receiving the training signals, and if the consistency is met, the upper power limits of the three engines are all controlled to be reduced to 2/3 of the single failure power. The consistency of the emergency control signals comprises: time consistency and instruction consistency; the time consistency is that the time interval of the three engine electronic controllers receiving the emergency control signal is within a set threshold value; the command consistency is that the emergency control signals received by the three engine electronic controllers have consistent meanings

Further, in the second step, if the training signals received by the three engine electronic controllers do not meet the consistency, the single failure training is automatically exited.

Further, the method further comprises: and monitoring the state of the engine, and automatically exiting the single failure training state when the state of the engine is abnormal.

Further, the method further comprises: monitoring rotor rotational speed, when rotor rotational speed is less than the settlement threshold value, the automatic training state that singly breaks out of withdraws from.

Further, the method further comprises: and when the training switch automatically exits the single-shot failure training state, the training switch automatically returns.

Further, in the first step, a failure flag of the engine is set through the electromechanical management system.

Further, the electromechanical management system sends corresponding engine installation loss data to the engine electronic controller according to the set failed engine.

The invention has the beneficial technical effects that: compared with the current helicopter OEI training function, the flight safety can be further improved, and the simulation of the real OEI flight state can be realized more truly. Therefore, the pilot can be trained more accurately to deal with the OEI flight state, the training function can be used for replacing the real OEI flight subjects in the test flight process, the test flight evidence obtaining period and cost are greatly reduced, and the flight safety of the risk subjects is improved.

Drawings

FIG. 1 is a diagram of engine response characteristics in OEI training mode;

FIG. 2 is a schematic diagram of the control logic for the OEI training function.

Detailed Description

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, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.

The real OEI training system for the helicopter engine with the three-engine/multiple-engine configuration, which is provided by the patent, is composed of a cockpit power check control switch, a multifunctional display, an electromechanical management system, an electronic controller of three engines and other sensors providing relevant functional parameters, which are mutually linked, as shown in fig. 2. Correspondingly, engine development is required to achieve the corresponding functional capabilities.

1) The pilot enters and exits an OEI training state through an OEI training control switch with a false touch prevention protective cover;

2) When all three engines receive the training signal, the three engines enter an OEI training state. After a brief power down, the three engines each deliver 2/3 of the OEI power, so that in the event that the three engines are operating and do not exceed normal operating limits,

the upper limit of the output power is defined as the OEI emergency power state of 2 engines to simulate the power output characteristics in a single-shot failure state.

3) The electromechanical management system sends the label of the engine with failure to three engine electronic controllers, and the engine adjusts the engine parameter signal sent to the electromechanical management system to be consistent with the real failure according to the electromechanical management system signal so as to simulate the parameter display of the cockpit when the real failure occurs.

4) The electromechanical management system displays OEI training identification and alarm information on the cockpit multifunctional display according to the state of the engine so as to distinguish the OEI training identification from the real situation.

5) When the received instructions of all the engines are inconsistent, a fault exists, or the rotating speed of the rotor wing of the helicopter is lower than a threshold value, the helicopter automatically exits from the training mode, and meanwhile, the control switch can automatically rebound to a normal position so as to keep the instructions consistent with the instructions.

Designing key control logic: and (3) simulating the control logic design of the real OEI power output:

the key to simulating the real OEI power output state using the OEI training function is to truly simulate the power characteristics of the engine after installation. Under other models of helicopters OEI training modes, only the power characteristics of the engine are generally considered, but the influence of the installed characteristics of the engine is not considered. The output power of the engine can be larger than the installed power, and the situation is particularly obvious in high installation loss and altitude flight. Thereby affecting the realism of the training and the ability to replace real OEI flights in trial flight subjects.

According to the helicopter platform, the influence of the installation loss of the engine on NG and T45 is sent to the engine electronic controller by using the electromechanical management system, and the helicopter platform corrects the power output characteristic of the engine, so that the influence of different platforms on the output characteristic of the engine can be truly simulated under the condition that the setting of the engine is not changed. The relevant control logic is shown in figure 1.

Wherein

a) The method is based on a complete functional design scheme designed for safety and authenticity.

b) The electromechanical management system is used for the selection and display management of the simulated 'failed' engine. By adopting the method, while the complex multi-position switch is prevented from being arranged on the three-engine helicopter, the 'failure' engine can be independently selected by a pilot or set according to preset logic, and the selection diversity is increased.

c) And an electromechanical management system is used for sending mounting loss correction data of the NG and T45 engines for correcting response characteristics of the engines after the engines are installed, so that the influence on the output characteristics of the engines under different platforms and different external conditions is truly simulated. So that the simulation is more realistic.

d) Under the real OEI state, the rotating speed of the rotor is a key factor which greatly influences the safety. In order to ensure the flight safety in the OEI training state. Besides automatic exit logics such as inconsistent instructions and engine faults, the invention also introduces the monitoring of the rotating speed of the rotor, and the monitoring is realized by monitoring the rotating speed of the engine Np, so that the training state is automatically exited under the condition that the rotating speed of the rotor is abnormal.

The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A single failure training method for a three-helicopter comprises the following steps: the method is characterized in that: the method comprises the following steps:

step zero: the electromechanical management system sends the engine installation loss to an engine electronic controller to correct the engine power parameter; the response characteristic after the engine is installed is corrected, so that the influence on the output characteristic of the engine under different platforms and different external conditions is truly simulated;

the method comprises the following steps: the pilot enters a single failure training state through a training switch; the training switch sends training signals to three engine electronic controllers; the switch is a switch with a magnetic retaining function;

2. The single-shot failure training method of a three-shot helicopter of claim 1: the method is characterized in that: in the second step, the three engine electronic controllers receive the training signals and then carry out consistency judgment, and if the consistency is met, the upper power limits of the three engines are controlled to be reduced to 2/3 of the single failure power;

the consistency of the training signal comprises: time consistency and instruction consistency;

the time consistency is that the time interval of the three engine electronic controllers receiving the training signals is within a set threshold value;

the command consistency is that the training signals received by the three engine electronic controllers have consistent meanings.

3. The single-shot failure training method of a three-shot helicopter of claim 2: the method is characterized in that: in the second step, if the training signals received by the three engine electronic controllers do not meet the consistency, the single failure training is automatically exited.

4. The single-shot failure training method of a three-shot helicopter of claim 1: the method is characterized in that: the method further comprises the following steps: and monitoring the state of the engine, and automatically exiting the single failure training state when the state of the engine is abnormal.

5. The single-shot failure training method of a three-shot helicopter of claim 1: the method is characterized in that: the method further comprises the following steps: monitoring rotor rotational speed, when rotor rotational speed is less than the settlement threshold value, the automatic training state that singly breaks out of withdraws from.

6. A three-helicopter single shot failure training method according to any of claims 3-5 and comprising: the method is characterized in that: the method further comprises the following steps: and when the training switch automatically exits the single-shot failure training state, the training switch automatically returns.

7. The single-shot failure training method of a three-shot helicopter of claim 1: the method is characterized in that: and in the third step, setting a failure mark of the engine through an electromechanical management system.