CN-121980673-A - Multi-source energy dynamic configuration method for wide-speed-domain aircraft

CN121980673ACN 121980673 ACN121980673 ACN 121980673ACN-121980673-A

Abstract

The invention discloses a wide-speed-domain aircraft multi-source energy dynamic configuration method, and belongs to the technical field of calculation, calculation or counting. Aiming at the characteristics of strong nonlinearity, high dynamic property and multimodal distribution in TBCC mode conversion stage, the method firstly builds an environment vector e containing a flight working condition and an engine state, secondly builds a strong coupling nonlinear mechanism model of a TBCC engine and a multi-source electric energy generation system, further builds a multi-target optimization model taking thrust loss delta FN and unit thrust fuel consumption rate increment delta SFC as targets, adopts a model-driven environment perception EA-NSGA-II algorithm to jointly monitor the environment through the environment vector and adaptation degree change, dynamically tracks the pareto front edge by utilizing a local restarting, memory population and an environment prediction mechanism, and finally maps the solution set into a multi-source power distribution interval . The invention can output the optimal energy configuration scheme meeting the safety constraint under the wide-speed domain, particularly dynamic mode conversion working condition.

Inventors

ZHENG FENGYING
LU JIAN
ZHANG JINGYANG
ZHENG YIFENG
WANG YIQUN
LI LIN
Han Jianhao

Assignees

南京航空航天大学

Dates

Publication Date: 20260505
Application Date: 20251229

Claims (10)

1. A method for dynamically configuring multi-source energy of a wide-speed-domain aircraft, comprising: S1, acquiring flight conditions and TBCC engine state parameters, and constructing an environment vector comprising Mach number, flight height, total temperature/total pressure of an air inlet channel, TBCC engine mode and compression part stability margin characterization quantity; S2, a unified coupling nonlinear mechanism model of the TBCC engine and a multi-source power generation system thereof is established, the mechanism model obtains thrust, unit thrust fuel consumption rate and parameters for safety evaluation according to input environment vectors and decision variables, the decision variables comprise output power of various power generation modes of the multi-source power generation system, and the parameters for safety evaluation comprise key section temperature, rotating part rotating speed and compression part stability margin; S3, under the condition of meeting power requirements and safety constraints, constructing a multi-objective energy management optimization model taking thrust loss and unit thrust fuel consumption increment as optimization objectives; S4, solving the multi-objective energy management optimization model by adopting a mechanism model-driven environment perception non-dominant sorting genetic algorithm II to obtain a pareto optimal solution set; S5, carrying out boundary extraction on the pareto optimal solution set obtained in the S4, obtaining a multi-source power distribution interval corresponding to the full envelope discrete operating point, interpolating the multi-source power distribution interval according to the current environment vector, and selecting an optimal decision variable after obtaining a multi-source power distribution real-time interval; And S6, driving the mechanism model to carry out safety check by the current environment vector and the optimal decision variable, and obtaining the multi-energy power distribution scheme meeting the safety constraint of the full envelope.
2. The method for dynamically configuring multi-source energy of a wide-speed-domain aircraft according to claim 1, wherein the S3-constructed multi-objective energy management optimization model comprises: optimization target: , , Power balance constraint: , Critical section temperature constraints: , rotating component rotation speed constraint: , Compression part stability margin constraint: , Modal feasible region constraint, turbofan modal stage order =0, Stamping mode stage command =0 And =0; Wherein, the In order to achieve a loss of thrust, Is the increment of the unit thrust fuel consumption rate, 、 The fuel consumption rate of the reference thrust and the reference unit thrust which are not extracted by power generation under the same environment vector, As a decision variable And an environment vector The pushing force of the lower part is equal to the pushing force, As a decision variable And an environment vector The unit thrust fuel consumption rate of the lower part, The output power of the shaft work extraction, the turbofan bleed air turbine and the ram bleed air turbine are respectively, In order for the power to be required, As a decision variable And an environment vector Lower critical section The temperature of the mixture is set to be higher than the temperature, As a decision variable And an environment vector Lower rotating part Rotational speed , As a decision variable And an environment vector Lower compression member The stability margin is set to be equal to the margin, Is a key section The maximum value of the temperature is set, Is a rotary part The maximum value of the rotational speed, Is a compression member Stability margin minimum.
3. A method for dynamically configuring multi-source energy of a wide-speed-domain aircraft according to claim 2, wherein S4 is specifically implemented by using Combining gene coding strategies will make decision variables Constraint processing assistance parameters Mapping to the chromosomal gene of the individual, In each generation of evolutionary iterations, the following algorithm flow is performed: s41, processing auxiliary parameters according to constraint The chromosome genes of each individual in the generation population are subjected to dynamic step-length constraint restoration and fitness evaluation; S42, when monitoring the first When the environment of the generation population changes drastically, calculate the first After the comprehensive environmental change amplitude of the generation population is changed, S43 is carried out, and the first generation population is monitored Severe environmental changes or the first generation of population S45 is carried out when the comprehensive environmental change amplitude of the generation population exceeds a threshold value; S43, according to the first Adaptive adjustment of comprehensive environmental change amplitude of generation population Evolution parameters of the generation population; S44, forecast the first The comprehensive environmental change amplitude of the generation population is that of the first Self-adaptively adjusting the first generation of population according to S43 when the predicted value of the comprehensive environment change amplitude exceeds the threshold value Evolution parameters of the generation population; S45, the first The generation population performs a restart operation, and is fed back to S41.
4. A method for dynamically configuring multiple energy sources for a wide-speed-range aircraft according to claim 3, wherein in S41, the auxiliary parameters are processed according to constraints The chromosome genes of each individual in the generation population are subjected to dynamic step-length constraint restoration, which comprises the following steps: In the first place Individual individuals When the power balance constraint is violated, utilize the first Individual individuals A kind of electronic device Gene dynamic regulation repair step length, update the first Individual individuals A kind of electronic device The gene is , , Is a target deviation vector; In the first place Individual individuals Against the constraint of the modal feasible region according to The rate of decay is controlled to gradually approach the modal feasible region.
5. The method according to claim 4, wherein in S41, the auxiliary parameter pair is processed according to constraint After dynamic step-size constraint repair is carried out on chromosome genes of each individual in the generation population, the fitness evaluation is carried out according to the following method, specifically, the method comprises the following steps of And (d) Generation group environment vector Driving the mechanism model to output a key section Temperature T i % E), rotating parts Rotational speed Or stability margin If the security constraint is still violated, then the violation is calculated and a penalty function is applied.
6. The method according to claim 5, wherein in S42, after monitoring the first step of When the environment of the generation population changes drastically, calculate the first The comprehensive environmental change amplitude of the generation population is specifically as follows: First, the Amplitude of variation of physical environment vector of generation population Or the variation amplitude of the algorithm fitness statistics When the threshold value is exceeded, the first judgment The generation group environment is mutated, , 、 Is the first Generation group, the first The environmental vector of the generation population, 、 Is the first Generation group, the first The fitness mean value of the generation population; On monitoring of the first Environmental change frequency of generation population When the threshold value is exceeded, the first judgment The generation of the severe environmental change of the population, calculate the first Comprehensive environmental change amplitude of generation population , , , To be algebraic of the last time an environmental mutation was detected, Is a normalized weight coefficient.
7. The method for dynamically configuring multiple energy sources for a wide-speed-range aircraft according to claim 6, wherein in S43, according to the first embodiment The evolution parameters are adaptively adjusted according to the comprehensive environmental change amplitude of the generation population, and the method specifically comprises the following steps: According to the first Comprehensive environmental change amplitude of generation population Definition of the first embodiment Adaptive adjustment parameters for generation population , , Adjusting a threshold value for the set environmental change amplitude; By means of Dynamically adjusting the first Variation rate of generation population Cross rate of First, the Enlarging the generation population when the environmental change is extremely severe Population size of generation population , , , , As a basis for the rate of variation, As a basis for the crossing rate of the beam, As a function of the size of the base population, 、、 The value is a positive number of adjustment factors.
8. The method for dynamically configuring multiple energy sources for a wide-speed-range aircraft according to claim 7, wherein said S44 predicts the first time series model The comprehensive environmental change amplitude of the generation population.
9. The method for dynamically configuring multiple energy sources for a wide-speed-range aircraft according to claim 8, wherein said S45 pair is the first The generation group executes restarting operation, which is specifically as follows: Optimal individuals of the current pareto front And the corresponding first Generation group environment vector Storing in memory bank , ; Retrieving in the memory bank Historical environment vector records similar to the population environment vector are recorded, and the searched memory bank is searched Strip context vector recording Corresponding historical optimal individual set And the first Elite individuals with maintained generation population Randomly generated supplemental individuals Fusion, reconstruct the first Population of generations Is that If not find and get the first Historical environment vector records similar to the generation population environment vector are recorded, local population restarting is executed, and only the first population is reserved Elite individuals of the generation population The rest individuals are randomly reset, and the first is reconstructed Population of generations Is that , Is the first after random reset Individual to the first The number of individuals who are to be treated, Is the total number of individuals; For the reconstructed first Population of generations And (3) performing selection, crossover and mutation operations according to the self-adaptive adjustment evolution parameters determined in the step (S43) to generate a next generation population.
10. The method for dynamically configuring multiple sources of energy in a wide-speed-range aircraft according to claim 9, wherein said searching and the first searching in said memory bank The method for recording the historical environment vectors similar to the population environment vectors comprises the following steps of calculating the first Generation group environment vector And the first memory bank Strip context vector recording Is a weighted euclidean distance of (c).

Description

Multi-source energy dynamic configuration method for wide-speed-domain aircraft Technical Field The invention relates to a hypersonic aircraft comprehensive energy optimization and engine control technology, discloses a wide-speed-range aircraft multi-source energy dynamic configuration method, in particular relates to a multi-source electric energy generation and energy efficiency collaborative optimization dynamic configuration method for a turbine-based combined cycle power system, and belongs to the technical field of calculation, calculation or counting. Background A Turbine-based combined cycle (TBCC) power system works in parallel with a punching channel through a turbofan channel, so that wide-speed-range propulsion from subsonic speed to hypersonic speed is realized. In hypersonic aircraft missions, the onboard electrical load is large and varies rapidly with the mission phase, often requiring extraction of shaft work from the engine main shaft or driving of an air turbine to generate electricity from the passage bleed air. The influence of multi-source power generation on the main power has the characteristics of strong nonlinearity and strong coupling, namely, the power extraction can change the working point of a gas compressor, the temperature before a turbine, the rotating speed and the stability margin, so that the thrust and the unit thrust fuel consumption rate are influenced, and particularly, in the mode conversion stage, the working state and the constraint boundary of an engine also fluctuate drastically along with the rapid change of the Mach number, the altitude and other physical flight environments, so that the mathematical solution space of the optimization problem presents the characteristics of high dynamic change and multimodal distribution. The existing multi-objective optimization method is characterized in that an optimization algorithm is separated from an engine model, a unified closed loop is not formed by fitness calculation and safety constraint evaluation, the safety constraint and the optimality of a full envelope are difficult to ensure simultaneously under the condition of rapid change of physical working conditions, and meanwhile, aiming at the space mutation of an optimization solution caused by the change of a physical flight environment, the existing algorithm lacks a memory multiplexing and prediction parameter adjustment mechanism, and is easy to fall into local optimum or to converge and lag in the environment mutation. Therefore, it is necessary to propose an algorithm-model depth coupling multi-source energy dynamic configuration method facing to TBCC mode conversion characteristics. Disclosure of Invention The invention aims to overcome the defects of the background art, and provides a multi-source energy dynamic configuration method for strong nonlinearity, high dynamic property and multimodal distribution characteristics of a TBCC (tunnel boring and control) mode conversion stage, which aims to dynamically determine a multi-source power optimal distribution interval in a full flight envelope range and ensure safety constraint by integrally coupling a TBCC engine mechanism model, a safety margin model and an environment-aware evolutionary optimization algorithm, thereby solving the technical problems that the existing multi-target optimization method is difficult to ensure the safety constraint and the optimality of the full envelope simultaneously in a dynamic environment and the mode conversion characteristic is not fully utilized and is easy to fall into local optimum. In order to achieve the aim of the invention, the invention adopts the following technical scheme: A method for dynamically configuring multi-source energy of a wide-speed-domain aircraft, comprising: S1, acquiring flight conditions and TBCC engine state parameters, and constructing an environment vector comprising Mach number, flight height, total temperature/total pressure of an air inlet channel, TBCC engine mode and compression part stability margin characterization quantity; S2, a unified coupling nonlinear mechanism model of the TBCC engine and a multi-source power generation system thereof is established, the mechanism model obtains thrust, unit thrust fuel consumption rate and parameters for safety evaluation according to input environment vectors and decision variables, the decision variables comprise output power of various power generation modes of the multi-source power generation system, and the parameters for safety evaluation comprise key section temperature, rotating part rotating speed and compression part stability margin; S3, under the condition of meeting power requirements and safety constraints, constructing a multi-objective energy management optimization model taking thrust loss and unit thrust fuel consumption increment as optimization objectives; s4, solving a multi-objective energy management optimization model by adopting a mechanism model-driven environment pe