CN112035962A - Superstructure model-based optimization method for airborne heat exchange network - Google Patents
Superstructure model-based optimization method for airborne heat exchange network Download PDFInfo
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Abstract
The application provides an aviation airborne heat exchange network optimization method based on a superstructure model, which comprises the following steps: determining the inlet and outlet parameters of cold and hot fluid in an airborne heat exchange network and the number of strands of cold and hot fluid; establishing a heat exchange network superstructure model according to the inlet and outlet parameters of the cold and hot fluid and the number of the cold and hot fluid, so as to establish the heat balance relationship of each heat exchange node; and constructing an optimized objective function under the optimal heat exchange area, calculating the heat exchange quantity of cold and hot fluids through the optimized objective function, and iteratively calculating the optimized objective function through an optimization algorithm to obtain the whole machine heat exchange network structure. The method provided by the application is used for integrally optimizing the heat exchange process from the perspective of a whole machine, is a forward design method of a heat network in a heat management system, can utilize the existing airborne heat sink to the maximum extent, simultaneously optimizes the weight of a heat exchange node and the heat exchange power margin, and provides an important guidance method for the light weight design of the system.
Description
Technical Field
The application belongs to the technical field of airborne heat exchange, and particularly relates to a superstructure model-based optimization method for an airborne heat exchange network.
Background
The airborne heat management system has more heat exchange nodes, complex working conditions in the heat exchange process, is realized based on a single system function, only considers the heat dissipation power grade, ensures that the system meets the most severe heat dissipation requirement of the system under typical severe working conditions, and performs the arrangement and design of heat exchange points according to the requirement.
The existing heat dissipation network design of the airborne heat management system does not have a comprehensive design method for synthesizing the cold and heat flow characteristics of the whole airborne heat sink and the heat dissipation load, the cold and heat resources of the whole airborne heat sink cannot be comprehensively designed and optimized from the heat dissipation angle, the system design is only carried out by the target realized by the single system function, the formed system has over-design conditions, although the requirements of the most harsh working condition of the airborne heat sink can be met to the maximum extent, the system design safety is better, the aspects of the sufficiency of the cold end heat sink utilization, the gradient optimization matching of the temperature and the like are not considered, the node arrangement of the system is difficult to optimize, the design margin of the node is overlarge, the matching performance of the cold and heat flows is poor, the limited heat sink resources of the airborne system are not fully utilized or the heat exchange power design of the.
Disclosure of Invention
The application aims to provide an aviation airborne heat exchange network optimization method based on a superstructure model, so as to solve or alleviate at least one problem in the background art.
The technical scheme of the application is as follows: an aviation airborne heat exchange network optimization method based on a superstructure model comprises the following steps:
determining the inlet and outlet parameters of cold and hot fluid in an airborne heat exchange network and the number of strands of cold and hot fluid;
establishing a heat exchange network superstructure model according to the inlet and outlet parameters of the cold and hot fluid and the number of the cold and hot fluid, so as to establish the heat balance relationship of each heat exchange node;
and constructing an optimized objective function under the optimal heat exchange area, calculating the heat exchange quantity of cold and hot fluids through the optimized objective function, and iteratively calculating the optimized objective function through an optimization algorithm to obtain the whole machine heat exchange network structure.
Further, the superstructure model at least comprises m hot fluids and N cold fluids, wherein the m hot fluids and the N cold fluids form S heat dissipation stages, S is max (m, N), and m and N are respectively equal to N + and are positive integers.
Further, the optimal heat exchange area refers to a minimum heat exchange area.
Further, the optimization algorithm comprises a particle swarm algorithm, a simulated annealing algorithm and a genetic algorithm.
Further, in the process of calculating the heat exchange quantity of cold and hot fluid by optimizing the objective function, the heat exchange quantity of the cold end and the hot end is calculated by an energy conservation law, a second thermodynamic law and a field synergistic temperature difference uniformity factor.
Further, the optimized whole machine heat exchange network structure comprises heat exchange node arrangement, node heat exchange quantity and the number of heat exchangers.
According to the aviation airborne heat exchange network optimization method based on the superstructure model, the mixed integer nonlinear mathematical model is abstracted and described for the airborne heat exchange network, the airborne heat exchange network superstructure model is established according to the inlet and outlet parameters of cold and hot material flows and the number of strands of the cold and hot fluid flows of the airborne heat exchange network, the initialization of the model is completed according to the cold and hot flow data of the heat management system, the solution optimization is carried out according to the mass conservation, the energy conservation, the second law of thermodynamics and the field cooperation theory, and the problem that the heat exchanger nodes are unreasonably arranged is solved; the heat exchange amount of the heat exchange nodes is optimized through an intelligent algorithm, the whole heat exchange process is optimized by taking the minimum heat exchange area as a target function, the heat exchange node arrangement, the node heat exchange amount and the number of heat exchangers of the whole machine heat exchange network are finally obtained, and the over-design problem of the heat exchange power of the system heat exchange nodes is solved.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a flowchart of a superstructure model-based aircraft engine heat exchange network optimization method.
Fig. 2 is a schematic diagram of a heat exchange network of an onboard thermal management system according to an embodiment of the present application.
FIG. 3 is a diagram of a thermal management system superstructure model constructed based on the heat exchange network of FIG. 2.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
The method of the present application is further illustrated or described with respect to the on-board thermal management system heat exchange network shown in fig. 1.
The method mainly comprises the following steps:
s1, firstly, according to the actual conditions of the airborne heat sink and the heat source, the number of cold and hot flows of the heat management system is analyzed, and the inlet and outlet parameters of the cold and hot flows in the airborne network and the number of the cold and hot flows are determined.
A typical on-board thermal management system thermal network, such as that shown in fig. 1, contains five streams of cold and hot fluids, fuel, oil, hydraulic oil, bleed air, and coolant, respectively. Wherein, the inlet and outlet parameters of each cold fluid and hot fluid are determined according to the design requirements.
And S2, establishing a heat exchange network superstructure model and initializing.
And determining cold and hot flows of the heat exchange network, giving a heat exchange boundary of the node, performing superstructure description according to the heat exchange network fluid contained in the heat management system, and establishing a superstructure model. The superstructure model at least comprises a heat exchange network with the heat dissipation stage number S formed by M hot flows or N cold flows, and S is determined by max (M, N).
For example, in the embodiment shown in fig. 1, there are 5 hot fluids, 1 cold fluid, and 5 heat dissipation stages, of which only the 1 st stage is shown. The cold utility is ram air.
The resulting superstructure model is shown in fig. 3.
And S3, constructing an optimization function taking the optimal heat dissipation area as an optimization target.
The established objective function comprises the heat dissipation area of a radiator, the use of cold public works and the like, and is used as an optimization objective function of the superstructure model.
The optimum heat radiation area is usually the minimum heat exchange area or the like, and thus the heat sink can be designed to be as small as possible.
S4, establishing a heat balance relation for each heat exchange node, establishing a heat balance relation for a cold common project, calculating the heat exchange quantity of the cold end and the hot end according to an energy conservation law, a second law of thermodynamics, a field cooperative temperature difference uniformity factor and the like according to initialization, and performing shaping optimization on a heat exchange network.
S5, initializing a heat exchange network superstructure model by using intelligent algorithms such as a particle swarm algorithm, simulated annealing and a genetic algorithm, and solving an optimal solution of a heat exchange network and optimizing a heat exchange network structure by using an optimized objective function of the heat exchange network;
and S6, finally, obtaining a heat exchange network structure with the minimum heat exchange area as a constraint through iterative optimization, wherein the heat exchange network structure comprises heat exchange node arrangement, the number of heat exchange nodes, the heat exchange amount of each node and the like.
The optimization method of the aviation onboard heat exchange network provided by the application is used for integrally optimizing the heat exchange process from the perspective of a whole machine, a forward design method of a core heat network in a heat management system based on a system engineering idea is established, the gap of the missing of the overall optimization design method of the heat network of the heat management system of the aviation onboard system is filled, the optimization design of the heat exchange node arrangement and the heat exchange quantity of the heat management network of the aviation onboard system can be guided by the method, the existing onboard heat sink is utilized to the maximum extent, the weight and the heat exchange power margin of the heat exchange node are optimized at the same time, and an important guidance method is provided for the light weight design of the system.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. An aviation airborne heat exchange network optimization method based on a superstructure model is characterized by comprising the following steps:
determining the inlet and outlet parameters of cold and hot fluid in an airborne heat exchange network and the number of strands of cold and hot fluid;
establishing a heat exchange network superstructure model according to the inlet and outlet parameters of the cold and hot fluid and the number of the cold and hot fluid, so as to establish the heat balance relationship of each heat exchange node;
and constructing an optimized objective function under the optimal heat exchange area, calculating the heat exchange quantity of cold and hot fluids through the optimized objective function, and iteratively calculating the optimized objective function through an optimization algorithm to obtain the whole machine heat exchange network structure.
2. The superstructure model-based optimization method for the airborne heat exchange network of the aviation, wherein the superstructure model at least comprises m hot fluids and N cold fluids, the m hot fluids and the N cold fluids form a heat dissipation stage S, S ═ max (m, N), and m, N ∈ N +, and N + is a positive integer.
3. The superstructure model-based optimization method for an airborne heat exchange network according to claim 1, wherein the optimal heat exchange area refers to a minimum heat exchange area.
4. The superstructure model-based optimization method for an airborne heat exchange network according to claim 1, wherein the optimization algorithm comprises a particle swarm algorithm, a simulated annealing algorithm and a genetic algorithm.
5. The superstructure model-based optimization method for the airborne heat exchange network of the aviation, wherein in the process of calculating the heat exchange amount of the cold fluid and the hot fluid by the optimization objective function, the heat exchange amount of the cold end and the hot end is calculated by the law of conservation of energy, the second law of thermodynamics and the field cooperative temperature difference uniformity factor.
6. The superstructure model-based optimization method for the airborne heat exchange network of the aircraft according to claim 1, wherein the optimized structure of the whole aircraft heat exchange network comprises node arrangement, node heat exchange amount and the number of heat exchangers.
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