CN110816824A

CN110816824A - Power control method for turboprop aircraft

Info

Publication number: CN110816824A
Application number: CN201911023100.5A
Authority: CN
Inventors: 张志远
Original assignee: AVIC XAC Commercial Aircraft Co Ltd
Current assignee: AVIC XAC Commercial Aircraft Co Ltd
Priority date: 2019-10-25
Filing date: 2019-10-25
Publication date: 2020-02-21

Abstract

A power control method for a turboprop aircraft comprises a power rod, an accelerator table, an engine controller, a propeller controller, an electromechanical data computer and an atmospheric data computer, wherein the engine power rod is provided with a plurality of control gears in the full-moving stroke from the maximum reverse propeller power to the maximum takeoff power of an engine, the engine controller controls the working state of the engine, the propeller controller controls the working state of the propeller, the power rod controls the engine controller through the accelerator table, and the engine controller is linked with the propeller controller.

Description

Power control method for turboprop aircraft

Technical Field

The application relates to the technical field of airplane design, and further relates to a power control method of a turboprop airplane.

Background

The turboprop is taken as a typical branch transport plane, the power of the turboprop is provided by matching an engine and a propeller, the turboprop has the advantage of low oil consumption, and the power control of the turboprop is often complex due to the particularity of a power device. The prior turboprop aircraft is provided with a power rod and a state rod, the power rod is used for controlling an aircraft engine, the state rod is used for controlling an aircraft propeller, and the aircraft power can be controlled only by the unit through the matching use of the two control rods.

The control method has the disadvantages that the unit is required to synchronously control the working of the propeller while controlling the working state of the engine, the unit has large operation load and higher operation requirement on the flight unit, and additional training subjects are required to meet the flight requirement.

Disclosure of Invention

The application aims to provide a power control method of a turboprop aircraft, which cancels a state lever, controls a turboprop aircraft power system only through a power lever, greatly reduces the burden of a pilot and improves the manipulation feeling of the turboprop aircraft.

A power control method of a turboprop aircraft comprises a power rod, an accelerator stage, an engine controller, a propeller controller, an electromechanical data computer and an atmospheric data computer, wherein the engine power rod is provided with a plurality of control gears in the full-motion stroke from the maximum reverse propeller power of an engine to the maximum takeoff power, the engine controller controls the working state of the engine, and the propeller controller controls the working state of the propeller; 2) the throttle platform is internally provided with an angle sensor, the position of the power rod is detected by the angle sensor, the throttle platform transmits a power rod position signal to the electromechanical data computer, receives an aircraft system state signal of the electromechanical data computer and simultaneously receives an atmospheric data signal provided by the atmospheric data computer, processes the received aircraft system state signal, the atmospheric data signal and the power rod position signal, and transmits the processed signals to the engine controller; 3) after receiving the signal from the throttle platform, the engine controller controls the oil supply amount of the engine according to the signal, and simultaneously sends a propeller control instruction to the propeller controller according to a propeller control rule corresponding to the current engine state, so that the engine controller is linked with the propeller controller; 4) the propeller controller receives a propeller control instruction from the engine controller, controls the rotating speed and the blade angle of the propeller, and realizes control over the state of the propeller.

The beneficial effect of this application lies in: 1) the engine and the propeller of the airplane are simultaneously operated only through the power rod, so that the power control mode of the turboprop airplane is simplified, the weight of an airplane control system is reduced, and the space of a cockpit is released; 2) the power system of the turboprop is controlled by only using the power rod, so that the unit load is greatly reduced; 3) the power control mode of the turboprop aircraft is optimized, the training subjects of the unit are reduced, and the training difficulty of the unit is reduced.

The present application is described in further detail below with reference to the accompanying drawings of embodiments:

drawings

FIG. 1 is a schematic diagram of a method of power control for a turboprop aircraft.

FIG. 2 is a functional block diagram of a method of controlling the power of a turboprop aircraft.

FIG. 3 is a schematic diagram of the relationship of power lever position to engine power to propeller speed control.

The numbering in the figures illustrates: horizontal axis 1, vertical axis 2, engine power curve 3, propeller speed curve 4

Detailed Description

Referring to the drawings, FIG. 1 is a schematic illustration of a method of power control for a turboprop aircraft as provided herein. The power pole passes through throttle platform control engine controller in this application, and then synchronous control propeller controller realizes the synchronous control of engine and propeller.

The specific control principle is shown in figure 2, and the power control method of the turboprop aircraft comprises a power rod, an accelerator table, an engine controller, a propeller controller, an electromechanical data computer and an atmospheric data computer, wherein the engine controller controls the working state of the engine, and the propeller controller controls the working state of the propeller. The power rod controls an engine controller through an accelerator platform, and the engine controller is linked with a propeller controller.

An angle sensor is arranged in the throttle platform, the position of the power rod is detected through the angle sensor, the throttle platform transmits a position signal of the power rod to the electromechanical data computer, receives an aircraft system state signal of the electromechanical data computer and simultaneously receives an atmospheric data signal provided by the atmospheric data computer, the throttle platform processes the received aircraft system state signal, the received atmospheric data signal and the position signal of the power rod, and transmits the processed signals to the engine controller. When the power rod moves between the gears, the rotating speed of the propeller is kept constant, the engine controller controls the oil supply amount of the engine to adjust the power of the engine, and the propeller controller adjusts the angle of the blade of the propeller, so that the control and adjustment of the power of the airplane are realized.

The engine controller continuously detects the engine state during the working period, and exchanges data with the propeller controller to provide the warning function of the engine and the propeller for the airplane.

The propeller controller receives a propeller control relation instruction signal from a corresponding engine controller, and controls the rotating speed and the blade angle of the control relation according to the control rule of the propeller controller, so that the state of the propeller is controlled. And the propeller controller monitors the working state of the propeller in real time in the working process and feeds back working data to the engine controller.

In the embodiment, as shown in fig. 3, the horizontal axis 1 is the full-motion stroke of the engine power lever, and the engine power lever is provided with six basic gears, namely, maximum reverse propeller (MAXREV), ground slow vehicle (GI), air slow vehicle (FI), Maximum Climb (MCL), Normal Takeoff (NTO) and Maximum Takeoff (MTO), in the full-motion stroke from the maximum reverse propeller power of the engine to the maximum takeoff power. The vertical axis 2 is the engine power, and an engine power curve 3 reflects the relationship of the corresponding engine powers of the engine power lever in different gears; the propeller rotation speed curve 4 reflects the relationship of the corresponding propeller rotation speeds of the engine power lever in different gears. In an embodiment the propeller control is in a constant speed control mode, i.e. the propeller is rotating at a constant speed N1 when the power lever is in the maximum MAX REV position, N2 when the power lever is between MAX REV and FI, N3 when the power lever is between FI and MCL, N4 when the power lever is between MCL and NTO, and N5 when the power lever is between NTO and MTO.

Engine power is a dynamic function of power lever position. The engine controller mainly determines and controls the power of the engine according to the position of the power rod, the external atmospheric temperature, the total pressure, the static pressure and other information; the propeller control law is also a dynamic function of the position of the power lever, and the engine controller determines the propeller control law and the rotating speed according to the angle of the power lever.

And after receiving the signal from the throttle platform, the engine controller controls the oil supply amount of the engine according to the signal, and simultaneously sends a propeller control instruction to the propeller controller according to a propeller control rule corresponding to the current engine state, so that the engine controller is linked with the propeller controller. The propeller controller receives a propeller control instruction from the engine controller, controls the rotating speed and the blade angle of the propeller, and realizes control over the state of the propeller.

Typically, 2 engines are installed on a turboprop, one power rod and one engine controller for each engine, one for each propeller, and one for each propeller. The two power rods are arranged on the same accelerator platform, the accelerator platform collects the positions of the two power rods, the position information and the atmospheric data information of an airplane system are combined, the data are comprehensively processed and then are respectively sent to corresponding engine controllers, the engine controllers control the oil supply of the engines according to control instructions of the accelerator platform, propeller control instructions are synchronously sent to the corresponding propeller controllers, and the propeller controllers adjust the spiral states.

The method is universal and suitable for single-engine or multi-engine turboprop aircrafts.

Claims

1. A power control method for a turboprop aircraft comprises a power rod, an accelerator stage, an engine controller, a propeller controller, an electromechanical data computer and an atmospheric data computer, wherein the engine power rod is provided with a plurality of control gears in the full-motion stroke from the maximum reverse propeller power to the maximum takeoff power of an engine, the engine controller controls the working state of the engine, and the propeller controller controls the working state of the propeller.

2. The method of power control for a turboprop aircraft of claim 1, wherein the throttle station includes an angle sensor for detecting the position of the power rod, the throttle station transmitting a power rod position signal to the electromechanical data computer and receiving an aircraft system status signal from the electromechanical data computer and receiving an atmospheric data signal from the atmospheric data computer, the throttle station processing the received aircraft system status signal and atmospheric data signal with the power rod position signal and transmitting the processed signals to the engine controller.

3. A method as claimed in claim 1 or claim 2, wherein the engine controller receives a signal from the throttle station and controls the amount of oil supplied to the engine in response to the signal, and the engine controller sends a propeller control command to the propeller controller in response to a propeller control law corresponding to the current engine state, thereby effecting linkage between the engine controller and the propeller controller.

4. A method for controlling power of a turboprop aircraft according to claim 3, wherein the propeller controller receives a propeller control command from the engine controller to control the speed of rotation of the propeller and the angle of the blade angle to effect control of the state of the propeller.

5. A method according to claim 3, wherein the propeller control law is a constant speed control mode, i.e. the speed of the propeller is constant when the power lever is between different gears, and the propeller controller is only required to adjust the blade angle to control the propeller.