| CPC F02C 9/00 (2013.01) [G06F 18/214 (2023.01); G06F 18/2411 (2023.01); G06N 20/10 (2019.01); F05D 2200/11 (2013.01); F05D 2200/12 (2013.01); F05D 2200/13 (2013.01); F05D 2200/14 (2013.01); F05D 2200/24 (2013.01); F05D 2270/02 (2013.01); F05D 2270/304 (2013.01); F05D 2270/3061 (2013.01); F05D 2270/44 (2013.01); F05D 2270/71 (2013.01); F05D 2270/803 (2013.01)] | 1 Claim |
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1. An adaptive boosting algorithm-based turbofan engine direct data-driven control method, wherein the method comprises the following steps:
step 1: establishing a data set for the design of a turbofan engine direct data-driven controller
step 1.1: collecting control signals during the operation of the turbofan engine, including input fuel flow wf(n) of turbofan engine, corrected relative rotary speed n1cor(n) of low-pressure rotor, and corrected relative rotary speed n2cor(n) of high-pressure rotor, wherein n=1, 2, . . . , indicating the nth sampling period;
step 1.2: Δu represents the input of turbofan engine, Δy represents the output of turbofan engine, Δn1cor(n) and Δn2cor(n) respectively represent the variations of corrected relative rotary speeds of low-pressure rotor and high-pressure rotor of the turbofan engine, and Δwf(n) represents the variation of the input fuel flow of turbofan engine, defining
Δu=[Δwf(1),Δwf(2), . . . ,Δwf(n)]T
Δy=[Δn2cor(1),Δn2cor(2), . . . ,Δn2cor(n)]T
[Δu,Δy] is the original data set for the design of the turbofan engine direct data-driven controller;
step 1.3: using the corrected relative rotary speed n2cor of high-pressure rotor as a scheduling parameter p (with the dimension equal to 1), and converting the scheduling parameter p to be within [−1,1], as shown in the following formula:
 wherein n2cor_max and n2cor_min are respectively the upper limit and lower limit of the relative rotary speed n2cor of high-pressure rotor of the turbofan engine;
step 2: adopting the methods of mean substitution and analysis of the Box-plot to perform data cleaning on the data in the data set [Δu,Δy], and filling missing data and eliminating outlier data in the data set;
step 3: adopting the LSSVM algorithm to design the turbofan engine controller
step 3.1: adopting the random sampling method to use 80% of the data set as a training data set and 20% as a testing data set;
step 3.2: adopting the Gauss kernel function Ω=K(p,t,k) to map the training data set to a high-dimensional feature space with the dimension of z from the original space so as to realize the linear regression of the training data set in the z-dimensional feature space, wherein the kernel function is expressed as follows:
 wherein t and k respectively represent the time t and the time k, p(t) and p(k) represent the scheduling parameters of the time t and the time k, σ is the initial hyper-parameter radial basis width of the Gauss kernel function, and σ>0 is required;
step 3.3: establishing the optimization problem of LSSVM:
 wherein ω is the normal vector of a hyperplane, the hyper-parameter γ is the weight for balancing “computation power for finding an optimal hyperplane” and “minimum deviation between training set and testing set”, yi is the dependent variable after the control signals are given, e is the training error, b is the bias operator, and N is the number of samples in the training data set;
step 3.4: using the Gaussian kernel function in step 3.2 and solving the optimization problem in step 3.3 to obtain the LSSVM regression function, which is expressed as follows:
 wherein ylssvm is the output of the turbofan engine controller designed based on the LSSVM algorithm, a is the Lagrangian operator, b is the bias operator, and N is the number of samples in the training data set;
step 4: using the adaptive boosting method and the output of the turbofan engine controller designed based on the LSSVM algorithm established in step 3 to construct an adaptive boosting algorithm-based turbofan engine direct data-driven controller, and adjusting the parameters of the controller
step 4.1: the training data set is T=[Δu′,Δy′], and [Δu′,Δy′] is the turbofan engine control data set obtained after data cleaning, wherein Δu′ is a control signal, Δy′ is the measured value Δn2cor of high-pressure rotor variation, and the basic learners in the adaptive boosting algorithm adopt the turbofan engine controller designed based on the LSSVM algorithm constructed in step 3 to give the initial hyper-parameter radial basis width σ and the weight γ and set epoch as the iteration number of the basic learners;
step 4.2: initializing the weight of the training data set to D(1)=(w11, w12, . . . , w1N),
 i=1, 2, . . . , N, where w is the weight of each sample in the training data set;
step 4.3: for the iteration number k=1, 2, . . . , epoch, using the training data set of the weight D(k) for training to obtain the basic learner Gk(x), and calculating the maximum error Ek predicted by the basic learner on the training data set, which is expressed as follows:
Ek=max|yi−Gk(xi)|,i=1,2, . . . ,N
step 4.4: calculating the relative error of each data sample in the training data set, and adopting a linear error, a square error or an exponential error, which are respectively expressed as follows:
 step 4.5: calculating the regression error rate eregression, as shown in the following formula:
 wherein wki is the weight of the data sample in the training data set obtained from the last iteration, and eki is the relative error obtained in step 4.4;
step 4.6: calculating the weight coefficient weightk of the basic learner, as shown in the following formula:
 step 4.7: updating the sample weight distribution of the training data set, and adaptively adjusting the initial hyper-parameter radial basis width σ according to the regression error rate, which is expressed as follows:
 wherein wki is the weight coefficient of the ith data sample at the kth iteration, σk is the hyper-parameter σ at the kth iteration, and Zk=Σi=1Nwki·weightk1-eki is the normalized operator;
step 4.8: averaging the predictive values yc generated by all iterations to obtain the final strong learner output yfinal, which is expressed as follows:
 step 5: using the cross validation method to determine the initial hyper-parameter radial basis width σ and the weight γ to satisfy the validation error of less than 0.1%, and maintaining the condition of σ,γ>ζ at all times during the iteration, wherein ζ is a smaller number not less than 0, if not in line, discarding the initial value, and selecting larger radial basis width σ and weight γ as the initial values of iteration to complete the design of the adaptive boosting algorithm-based turbofan engine direct data-driven controller.
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