Double-engine failure training method for three-engine configuration helicopter

Abstract

The invention belongs to the field of helicopter power system design, and discloses a three-engine configuration helicopter double-engine failure training method, which comprises the following steps that 1, a pilot controls a helicopter to enter a double-engine failure training mode; 2, setting an engine output power upper limit; step 3, the electromechanical management computer randomly selects two engines as failed engines, and sends failure marks to corresponding engine electronic controllers; the engine electronic controllers receiving the failure marks send true values and training values of corresponding failed engine parameters to the electromechanical management computer; the electromechanical parameter display and the multifunctional display display training values of parameters sent by the engine electronic controller; step 4, the electromechanical management computer controls a display to display a double-engine failure training identifier, and displays parameters sent by the electronic controllers of the three engines; and 5, the pilot controls the helicopter to exit the double-engine failure training mode.

Description

Technical Field

[0001] The invention belongs to the field of helicopter power system design, and in particular relates to a dual-engine failure training method for a three-engine helicopter. Background Art

[0002] my country has a vast territory and diverse landforms. Compared with other countries and regions in the world, China pays more attention to the performance of helicopters under plateau conditions during the development of helicopters. Due to the power attenuation of the engine's plateau performance, three-engine helicopters have become an option for the development of large-tonnage helicopters.

[0003] The two-engine failure (TEI) state of a helicopter is an important failure mode that a three-engine helicopter may encounter during use, and it has a great impact on the flight safety of the helicopter. When two engines of a three-engine helicopter fail, the remaining engine will automatically increase its power state to the emergency power state to meet the power requirements of the helicopter. In actual test flights, if the two engines are shut down for a TEI mode test flight, the emergency power usage time of the other engine will be consumed too quickly. During the engine repair interval, the emergency power state has strict restrictions on the usage time. Once it exceeds 2.5 minutes, the engine will need to be returned to the factory for repair, which will have a great impact on the test flight mission and the use of funds.

[0004] In the current helicopter training model, the focus is mainly on the failure mode under single engine failure (OEI), and less attention is paid to the failure mode under double engine failure. There is little research on the safety, economy, and authenticity of the TEI state.

[0005] Therefore, it is necessary to develop a helicopter TEI training function in order to train pilots in emergency response to TEI status during flight in daily test flight subjects. Summary of the invention

[0006] Purpose of the invention: A dual-engine failure training method for a three-engine helicopter is proposed. Compared with the OEI training function, the flight interface and setting logic of the simulated TEI fault mode are more complicated. The TEI training function enables the pilot to intuitively feel the display and warning information in the TEI fault mode, so as to train the pilot's emergency response capabilities in the TEI fault mode, replace the real TEI flight, further improve the safety, carry out relevant performance verification in the test flight, greatly reduce the flight risk, and at the same time, reduce the use time of the engine emergency power, and reduce the expenses and test flight time caused by the engine being returned to the factory for repair.

[0007] Technical Solution

[0008] A dual-engine failure training method for a three-engine helicopter, the steps are as follows:

[0009] Step 1: The pilot controls the helicopter to enter the dual-engine failure training mode;

[0010] Step 2: Set the upper limit of engine output power;

[0011] Step 3: The electromechanical management computer randomly selects two engines as failed engines and sends failure marks to the corresponding engine electronic controllers; the engine electronic controllers that receive the failure marks send the actual values ​​and training values ​​of the corresponding failed engine parameters to the electromechanical management computer, and the electromechanical parameter display and the multi-function display display the training values ​​of the parameters sent by the engine electronic controllers; Step 4: The electromechanical management computer controls the display to display the dual-engine failure training mark and the parameters sent by the three engine electronic controllers;

[0012] Step 5: The pilot controls the helicopter to exit the dual-engine failure training mode.

[0013] Further, in step 1, the pilot first switches the parking training switch from "normal" to "training", and then switches the parking training select switch from "normal" to "twin engine".

[0014] Further, in step 2, setting the upper limit of the engine output power includes: setting the maximum total power of the three engines to not exceed N;

[0015] The output power limit of each of the three engines is N / 3.

[0016] Furthermore, step 1 also includes: the electromechanical management computer determines whether the dual-engine failure training mode can be entered, and prohibits entering the dual-engine failure training mode when any of the following conditions is met; the conditions are as follows:

[0017] Any engine is operating in manual mode;

[0018] Any engine has a critical fault or a non-critical fault;

[0019] Any engine is stopped;

[0020] Any engine control switch is not in the "flight" position;

[0021] The torque difference between the three engines is not within 5%;

[0022] Any engine Npt is less than 96%;

[0023] The "Parking Training" switch is in the "Normal" position;

[0024] The "Parking Training Selection" switch is in the "Normal" position;

[0025] The switching time of operating the "parking training selection" switch exceeds 0.2s;

[0026] The switching time of operating the “parking training” switch exceeds 0.2s.

[0027] Further, in step 4, the display simultaneously displays the real parameters and training parameters of the three engines;

[0028] The parameters include: Q: torque; Npt: free turbine speed; I TT: engine turbine inter-turbine temperature; T1: engine intake temperature; Ng: gas turbine speed, and the three engines are marked 1, 2, and 3 respectively.

[0029] Furthermore, Q1 training = 0, Q2 training = 0, Q3 training = Q3 actual + Q1 actual + Q2 actual.

[0030] Further, Npt1 training = 0, Npt2 training = 0, NPT3 training = Npt3 actual.

[0031] Further, I TT1 training = T1 actual, I TT2 training = T1 actual, I TT3 training = I TT3 + I TT INDTB3.

[0032] Further, Ng1 training = 0, Ng2 training = 0, Ng3 training = Ng3 + NG I NDTB3;

[0033] I TT I NDTB3: Inter-turbine temperature deviation; NG I NDTB3: Gas turbine speed deviation.

[0034] In summary, the beneficial effects of the present invention are as follows:

[0035] This patent proposes a TEI training function suitable for three-engine helicopters. This function sets the cockpit instruments and warnings in the TEI failure mode so that it can simulate the real warning information under the TEI failure. This function is used to train pilots' flight handling capabilities in the TEI failure mode. During the test flight, it reduces the cost and test flight cycle risks caused by the engine being returned to the factory for repair due to the use of the engine emergency power. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 This is a schematic diagram of the dual-engine failure training mode switch;

[0037] Figure 2 This is a control logic diagram for the double-engine failure training function. DETAILED DESCRIPTION

[0038] The present invention is related to the design field of helicopter power system and flight / engine control, and proposes a dual-engine failure training method suitable for three-engine helicopters. This function sets the instruments and warnings in the cockpit under the dual-engine failure mode so that it can simulate the real warning information under the dual-engine failure. This function is used to train the pilot's flight handling ability under the dual-engine failure mode. Compared with the single-engine failure training method, this function changes the safety requirements and has more stringent access and exit conditions. The setting of training parameters is simpler and more accurate, which reduces the cost and test flight cycle risks caused by the engine being returned to the factory for repair due to the use of the engine emergency power during the test flight.

[0039] A dual-engine failure training method for a three-engine helicopter comprises the following steps:

[0040] Step 1: The pilot switches the "parking training" switch in the cockpit from the "normal" position to the "training" position, and then switches the "parking training selection" switch from the "normal" position to the "dual engine" position; the parking training selection switch includes "single engine" and "dual engine", which can realize single engine training and dual engine training functions, and the parking training switch is the overall control to prevent the pilot from accidentally touching it. At the same time, the joint control of the two switches can effectively prevent the pilot from accidentally touching the operation during the flight, thereby putting the engine into training mode.

[0041] Step 2: The three engine electronic controllers receive the "parking training" signal and the "dual-engine training" signal. After the three engine electronic controllers receive the signals at the same time, they enter the dual-engine parking training mode. The maximum power of the helicopter cannot exceed 1300kW according to the transmission limitation. It is changed to: Compare the maximum power limit of a single engine and the maximum power limit of the transmission system, and use the smaller value of the two limits, 1300kW, as the maximum power limit of the helicopter. At this time, the three engine electronic controllers of the helicopter simultaneously set the upper limit of the output power of a single engine to 433kW according to the power limit of the transmission system of 1300kW, and the total power remains at 1300kW. If the collective pitch is increased again, the total power remains in the set state, and the rotor speed will be reduced accordingly.

[0042] Step 3: The electromechanical management computer immediately selects two engines as failed engines and sends the set failure mark (indicating the failed engine number) to the three engine electronic controllers; the engine electronic controllers continuously monitor the dual-engine parking training signal, and the engine electronic controllers calculate the training values ​​of the corresponding engine parameters according to the failure mark, and send the training values ​​to the electromechanical management computer, and the training value information of the failed engine is displayed on the electromechanical parameter display and the multi-function display.

[0043] Step 4: The electromechanical management computer enters the training mode screen according to the failure status of Engines 1 and 2, and displays the dual-engine failure training logo, engine parameter display under dual-engine failure, and corresponding warning information on the electromechanical parameter display and the avionics system multi-function display for pilot training.

[0044] Step 5: The pilot can exit the dual-engine failure training state by placing the "Parking Training" switch in the "Normal" position and the "Parking Training Select" switch in the "Normal" position.

[0045] Furthermore, in step 2, since the dual-engine failure training conditions are more stringent and require better safety, it is defined that if any of the following conditions occurs, the training mode cannot be entered:

[0046] Any engine is in manual mode;

[0047] Any engine has a critical fault or a non-critical fault;

[0048] Any engine is stopped;

[0049] Any engine control switch is not in the "flight" position;

[0050] The torque difference between the three engines is not within 5%;

[0051] Any engine Npt is less than 96%;

[0052] The "Parking Training" switch is in the "Normal" position;

[0053] The "Parking Training Selection" switch is in the "Normal" position;

[0054] The switching time of operating the “parking training selection” switch exceeds 0.2s;

[0055] The switching time of operating the “Parking Training” switch exceeds 0.2s.

[0056] Furthermore, in step 2, during the dual-engine parking training, the three engines evenly share the "larger" power that should be generated by one engine.

[0057] Furthermore, in step 4, the instruments and warnings in the cockpit all show that two engines have failed and stopped;

[0058] When entering the dual-engine parking training mode, the three engine parameters in the training screen of the electromechanical parameter display are displayed according to the following setting parameters: (Q: torque; Npt: free turbine speed; I TT: engine turbine inter-turbine temperature; T1: engine intake temperature; Ng: gas turbine speed; I TT I NDTB3: turbine inter-turbine temperature deviation value (the engine electronic controller calculates and corrects the I TT value in the engine training mode, which will be calculated according to the engine real-time power state); NG I NDTB3: gas turbine speed deviation value (the engine electronic controller calculates and corrects the Ng value in the engine training mode, which will be calculated according to the engine real-time power state); take the failure of 1 and 2 engines as an example.)

[0059] Q1 training = 0

[0060] Q2 training = 0

[0061] Q3 training = Q3 actual + Q1 actual + Q2 actual

[0062] Npt1 training = 0

[0063] Npt2 training = 0

[0064] NPT3 training = NPT3 practice

[0065] I TT1 training = T1 practice

[0066] I TT2 training = T1 practice

[0067] ·I TT3 training=I TT3+I TT I NDTB3

[0068] Ng1 training = 0

[0069] Ng2 training = 0

[0070] Ng3 training = Ng3 + NG I NDTB3

[0071] Furthermore, in step five, if any of the following conditions occurs, the engine automatically exits the training mode to ensure flight safety.

[0072] ·Continuously monitor the automatic and manual mode signals. When any engine is in manual mode, the engine automatically exits the training mode;

[0073] ·Continuously monitor the engine status. If any engine has a critical or non-critical fault, the engine will automatically exit the training mode;

[0074] ·Continuously monitor engine status signals. If any engine stops, the engine will automatically exit the training mode;

[0075] ·Continuously monitor the engine control switch signal. When the state of any engine control switch changes, the engine automatically exits the training mode;

[0076] ·Continuously monitor the Npt sensor signal. If the Npt of any engine is lower than 96% (due to the increase in required power and engine power limitation, resulting in a decrease in rotor speed), the engine automatically exits the training mode;

[0077] ·Continuously monitor the engine parking training switch signal. When the "parking training" switch is in the "normal" position, the engine automatically exits the training mode;

[0078] ·Continuously monitor the engine parking training selection switch signal. When the "parking training selection" switch is in the "normal" position, the engine automatically exits the training mode.

[0079] The beneficial technical effects of the present invention include: a dual-engine failure training method suitable for three-engine helicopters. Compared with the single-engine failure training method for helicopters, the dual-engine failure failure mode has higher safety requirements and more stringent entry and exit conditions. Under the premise of ensuring flight safety, the dual-engine failure failure mode that may occur during flight is simulated to train pilots to deal with the dual-engine failure failure mode and enhance the pilots' ability to cope with dual-engine failure. At the same time, the dual-engine failure training function is used in the test flight to reduce the time it takes for the engine to enter emergency power, reduce the number of times the engine is returned to the factory, and reduce the test flight cycle and cost.

[0080] The technical solution of the present invention includes three parts: system composition, function design and display design.

[0081] System composition:

[0082] The patent proposes a real double-engine failure training function for three-engine helicopter engines, which consists of a parking training selection switch on the engine control box panel in the cockpit, a parking training switch, an electromechanical parameter display, a multi-function display, a warning light box, an engine electronic controller, and sensors for corresponding parameters. Correspondingly, the engine needs to develop corresponding functional capabilities.

[0083] Display Design:

[0084] Normal mode: In normal mode, the electromechanical parameter display shows the status of the three engines and the corresponding Q, NPT, I TT, and NG parameters through bar graphs;

[0085] Dual-engine failure training mode: In dual-engine failure training mode, the electromechanical parameter display shows that the No. 1 and No. 2 engines have a fault and are stopped. The Q, NPT, I TT, and NG parameter values ​​of the two engines are 0. The bar display of the No. 3 engine parameters shows the parameter values ​​under the current power state according to the helicopter power demand.

[0086] Compared with the OE I training function of other helicopters, the main innovation of this patent is

[0087] a) This method proposes a double-engine failure training function.

[0088] b) This method proposes a method of randomly selecting two failed engines, so that the pilot can experience the dual-engine failure state more realistically.

[0089] c) The electromechanical management computer sends the engine identification to the electronic controller, and the engine electronic controller outputs the training value of the parameter.

[0090] d) The training values ​​output by the engine electronic controller are calculated in a simpler and more accurate way, and the engine I TT and Ng parameter training values ​​are corrected in real time according to the helicopter power status, so as to achieve the purpose of truly simulating the dual-engine failure state.

Claims

1. A dual-engine failure training method for a three-engine helicopter, characterized by: Here are the steps: Step 1: The pilot controls the helicopter to enter the dual-engine failure training mode; Step 2: Set the upper limit of engine output power; Step 3: The electromechanical management computer randomly selects two engines as failed engines and sends failure marks to the corresponding engine electronic controllers; The engine electronic controller that receives the failure mark sends the real value and the training value of the corresponding failed engine parameter to the electromechanical management computer, and the electromechanical parameter display and the multi-function display display the training value of the parameter sent by the engine electronic controller; Step 4: The electromechanical management computer controls the display to display the dual-engine failure training logo and the parameters sent by the electronic controllers of the three engines; Step 5: The pilot controls the helicopter to exit the dual-engine failure training mode.

2. The method according to claim 1, characterized in that: In step one, the pilot first switches the parking training switch from "Normal" to "Training" and then switches the parking training select switch from "Normal" to "Twin Engine".

3. The method according to claim 2, characterized in that: In step 2, setting the upper limit of the engine output power includes: setting the maximum total power of the three engines to not exceed N; The output power limit of each of the three engines is N / 3.

4. The method according to claim 3, characterized in that: Step 1 also includes: the electromechanical management computer determines whether the dual-engine failure training mode can be entered, and prohibits entering the dual-engine failure training mode when any of the following conditions is met; the conditions are as follows: Any engine is operating in manual mode; Any engine has a critical fault or a non-critical fault; Any engine is stopped; Any engine control switch is not in the "flight" position; The torque difference between the three engines is not within 5%; Any engine Npt is less than 96%; The "Parking Training" switch is in the "Normal" position; The "Parking Training Selection" switch is in the "Normal" position; The switching time of operating the "parking training selection" switch exceeds 0.2s; The switching time of operating the "parking training" switch exceeds 0.2s.

5. The method according to claim 4, characterized in that: In step 4, the display simultaneously displays the real parameters and training parameters of the three engines; The parameters include: Q: torque; Npt: free turbine speed; ITT: engine inter-turbine temperature; T1: engine intake temperature; Ng: gas turbine speed, and the three engines are marked 1, 2, and 3 respectively.

6. The method according to claim 5, characterized in that: Q1 training = 0, Q2 training = 0, Q3 training = Q3 actual + Q1 actual + Q2 actual.

7. The method according to claim 5, characterized in that: Npt1 training = 0, Npt2 training = 0, NPT3 training = Npt3 actual.

8. The method according to claim 5, characterized in that: ITT1 training = T1 actual, ITT2 training = T1 actual, ITT3 training = ITT3 + ITTINDTB3.

9. The method according to claim 5, characterized in that: Ng1 training = 0, Ng2 training = 0, Ng3 training = Ng3 + NGINDTB3; ITTINDTB3: Inter-turbine temperature deviation value; NGINDTB3: Gas turbine speed deviation value.

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