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
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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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