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Energy optimization configuration and evaluation method based on thermoelectric coupling

A technology of energy optimization and thermoelectric coupling, which is applied in the field of aircraft energy management, can solve problems such as increasing the computational complexity of the system, increasing the scale of optimization problems, and increasing computational overhead, so as to achieve good global search performance, reduce shaft power extraction, and improve reliability effect

Active Publication Date: 2021-09-28
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The characteristics of energy coupling and design variables between different subsystems of the electromechanical system increase the scale of the optimization problem, resulting in an increase in computational overhead
In addition, the entire electromechanical system may have multiple optimization objectives, and the system requires precise analysis methods, which will increase the computational complexity of the entire system

Method used

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  • Energy optimization configuration and evaluation method based on thermoelectric coupling
  • Energy optimization configuration and evaluation method based on thermoelectric coupling
  • Energy optimization configuration and evaluation method based on thermoelectric coupling

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0048] Embodiment 1. Shaft power extraction model.

[0049] The mission power spectrum of the overall flight mission of the aircraft is as follows: image 3 As shown, the task requirements of the main subsystems of the aircraft electromechanical system are given here, mainly including the AC load, high-voltage DC load, low-voltage DC load, and high-power load of the power supply system; the actuator mechanical load of the hydraulic system, the hydraulic motor mechanical load, etc. Loads: Air-conditioning system loads of environmental control systems, electric heating anti-icing system loads, compressors and other thermal power loads. In the space-time large-scale equivalent mission profile model, the load power can be equivalent to Figure 4 shown. The energy sources of these loads come from the shaft power extraction and bleed air of the engine and the bleed air of the ram air, which can be converted to the shaft power extraction of the engine, and then equivalent to the fu...

Embodiment 2

[0057] Embodiment two, weight model.

[0058] The weight of the electromechanical system of the aircraft is another key indicator. This type of indicator mainly includes two parts, namely, the quality of the typical equipment of the subsystem of the electromechanical system and the amount of auxiliary medium used in the subsystem, such as the amount of hydraulic oil in the hydraulic system and the environmental control system. Coolant, i.e. fuel / lubricating oil consumption, etc.

[0059] In engineering practice, for an aircraft generator, a specific rated power corresponds to a specific weight, so the relationship between the rated power and weight of the equipment can be established, and the weight can be expressed as a function of the rated power. Figure 5 Typical generator power densities are shown.

[0060] The converter is similar to the generator, and the required converter weight can be estimated by fitting the curve of the relationship between the weight and the rate...

Embodiment 3

[0070] Embodiment 3, overload and heat dissipation model.

[0071] In the overall task profile, there is a characteristic task profile, that is, the profile under the use of high-power loads. The use of high-power loads puts forward higher requirements for the aircraft electromechanical system, which requires that the aircraft electromechanical system can provide sufficient power supply, It can also complete energy conversion and heat dissipation in the case of high-power tasks. Therefore, this task profile is extracted separately for analysis and optimization of peak power extraction and heat dissipation performance.

[0072]In the high-power task load profile, when the power demand of the weapon system reaches the maximum, the actuating power of the wing rudder surface also reaches the maximum, the engine runs at full power and the extractable shaft power cannot exceed the rated value, which meets the normal supersonic flight and maneuvering of the aircraft state, so the en...

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Abstract

The invention belongs to the technical field of aircraft energy management, and relates to an energy optimization configuration and evaluation method based on thermoelectric coupling. The method comprises the steps of firstly, conductingmulti-objective optimization on a to-be-optimized system architecture, a preset top-layer design objective serving as an optimization objective, the component specifications and the component number of the system architecture serving as variables, and optimizingthe component specifications and the component number of the system architecture; then, according to the reliability data of each equipment, determining an initial connection mode between the equipment; and finally, for the initial connection mode, verifying the reliability of the system architecture, and if the system reliability is not met, increasing system redundancy, carrying out multi-objective optimization again, and determining the component specification and the component number of the system architecture until the system architecture meets the reliability. The aircraft secondary energy system architecture optimization method and strategy are formed by establishing the multi-target and multi-parameter multi-stage optimization model of the aircraft electromechanical system, and the reliability of the whole optimization process is improved.

Description

technical field [0001] The application belongs to the technical field of aircraft energy management, and in particular relates to an energy optimization configuration and evaluation method based on thermoelectric coupling. Background technique [0002] The aircraft electromechanical system integrates the power supply system, hydraulic system and environmental control system, etc., and is the general term for the systems that perform various functions of flight support on the aircraft. With the development of aviation technology, the electromechanical system of aircraft is gradually developing in the direction of multi-electric and all-electric, and the use of advanced weapons and equipment has made the demand for aircraft electricity continue to increase. On the other hand, a large increase in electric power will also greatly increase the thermal load, and thermal issues must be taken into account when configuring energy. Therefore, it is very necessary to optimize the ener...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/15G06F30/27G06N3/12G06F111/06G06F111/10G06F119/08
CPCG06F30/17G06F30/15G06F30/27G06N3/126G06F2111/06G06F2111/10G06F2119/08Y02P90/82
Inventor 林鹏赵民梁兴壮艾凤明李征鸿王鹤雷涛
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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