Aero-engine starting fuel oil flow control method
An aero-engine and engine starting technology, which is applied in the direction of engine starting, engine components, engine ignition, etc., can solve the problems of nonlinear model parameters, difficult acquisition of model parameters, and large influence of model parameters by environmental variables.
Active Publication Date: 2022-08-05
PLA NO 5719 FACTORY
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[0003]
Aiming at the problems that the model parameters of aeroengines are nonlinear, the model parameters are not easy to obtain, and the model parameters are greatly affected by environmental variables, a starting fuel flow control method based on online identification of model parameters and discrete proportional integral control is provided. This method can be used when the engine model is unknown. In the case of aero-engines, quickly realize the start-up test of the aero-engine and test the performance of the engine
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[0019] In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention.
[0020] Aero-engine starting fuel flow control method, including:
[0021] Step 1. Collect the fuel supply Wf(k) and the compressor speed N(k) corresponding to the first k cycles when the engine is started, and set the target value of the compressor speed for each control cycle.
[0022] Step 2. Calculate the fuel supply increase ΔWf(k-1) according to ΔWf(k-1)=Wf(k)-Wf(k-1), and Calculate the compressor speed where ΔT is the sampling period of the system;
[0023] Step 3. Construct matrices Y, X and A, where,
[0024]
[0025] In the formula, N is the order of the matrix;
[0026] Step 4. According to A=...
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The invention relates to the technical field of aero-engine starting control, and provides an aero-engine starting fuel flow control method in order to conveniently control starting fuel flow. Comprising the steps that 1, the oil supply amount and the actual rotating speed of a gas compressor corresponding to the first k periods when an engine is started are collected, and the rotating speed rate target value of the gas compressor in each control period is set; 2, calculating the oil supply increment and the rotating speed rate of a gas compressor; 3, constructing matrixes Y, X and A; 4, solving the current least square solution of the matrix A; 5, engine model parameters are obtained according to the least square solution; 6, the target oil supply amount of the next period is calculated according to the engine model parameters; and 7, repeating the steps 1-6 until the engine is successfully started. By adopting the steps, the starting fuel flow can be conveniently controlled.
Description
technical field [0001] The invention relates to the technical field of aero-engine starting control, in particular to an aero-engine starting fuel flow control method based on online identification of model parameters. Background technique [0002] The starting process of aero-engine is a typical nonlinear characteristic process. Improper control of fuel flow will cause over-temperature at start, engine thermal suspension, and over-start at start. Improper handling will directly damage the engine. At present, the fuel flow control of aero-engine starting is generally performed piecewise linearization of the engine starting process after the characteristic parameters of the engine components are obtained, and then the control parameters are calculated for each linearized model. In the early stage of this process, a large number of aerodynamic and thermal dynamic tests are required to obtain the characteristic parameters of the engine, and the test process is complicated and e...
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IPC IPC(8): F02C9/28F02C7/26G01M15/14G06F30/15
CPCF02C9/28F02C7/26G01M15/14G06F30/15Y02T90/00
Inventor 李洋胡惠芳赵柯程春陈明安
Owner PLA NO 5719 FACTORY