Selection method for power system of pure electric drive multi-rotor aircraft for transportation tasks

A multi-rotor aircraft and power system technology, applied in the field of pure electric drive multi-rotor aircraft power system selection, to achieve balanced performance and endurance performance, use of battery power, and high matching effect

Active Publication Date: 2020-10-13
ZHEJIANG LAB
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention aims at the type selection and matching problem of the existing pure electric drive multi-rotor aircraft power system, and proposes a pure electric drive multi-rotor aircraft power system selection method

Method used

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  • Selection method for power system of pure electric drive multi-rotor aircraft for transportation tasks
  • Selection method for power system of pure electric drive multi-rotor aircraft for transportation tasks
  • Selection method for power system of pure electric drive multi-rotor aircraft for transportation tasks

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Experimental program
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Embodiment

[0037] This embodiment takes a multi-rotor manned aircraft as an example for illustration.

[0038] First determine the load and battery life indicators, taking the load of 100kg and battery life of 15 minutes as an example. Set the battery power safety margin to 25%, and the battery life margin to 5 minutes. According to the basis of initial value setting, the following equations are listed to solve:

[0039]

[0040] Among them, m Battery is the battery weight; m Body is the weight of the fuselage, which is equal to the weight of the battery in m according to the setting basis Battery ;m Load is the load weight, which is equal to 100kg in this example; t is the endurance time, which is 15min in this example; η FE is the power efficiency of the power system, which is equal to 6k / W according to the setting basis; ρ Energy It is the energy density of the battery, which is equal to 180Wh / kg according to the setting basis; η Pack is the battery group efficiency, accordi...

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Abstract

The invention discloses a transportation task-oriented pure-electric-drive multi-rotor aircraft power system model selection method, and belongs to the technical field of pure electric drive multi-rotor aircrafts. Through estimation and performance analysis on the weight of each part of an aircraft to guide model selection, the matching degree of an aircraft power system is evaluated by using thethrust-weight ratio of the whole aircraft, the power control allowance, the effective working range of a battery and the discharge rate of the battery, finally the endurance time of the aircraft is calculated, and the overall power performance and endurance performance of the aircraft are verified. According to the model selection method, a good model selection optimization method for the power system of the pure electric drive multi-rotor aircraft is provided, the performance and endurance performance of the power system of the aircraft can be balanced, and the endurance time is prolonged onthe premise that task requirements are met.

Description

technical field [0001] The invention relates to the technical field of multi-rotor aircraft, in particular to a method for selecting a power system of a purely electric drive multi-rotor aircraft for transportation tasks. Background technique [0002] Due to the unique advantages of vertical take-off and landing, hovering in the air, and flexible maneuverability, the multi-rotor aircraft has a low threshold for use, and it has been used in many fields such as aerial photography, exploration, logistics and transportation. However, limited by the current battery technology, battery life has always been the biggest shortcoming of pure electric drive multi-rotor aircraft. Especially in the field of transportation, there is a more urgent demand for load and battery life. On the other hand, compared with fossil fuels, electric energy is clean, efficient, and renewable, which is undoubtedly the future development direction. Therefore, optimizing the selection of the power system ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00B64D27/24
CPCB64D27/24B64F5/00Y02T50/60
Inventor 成利波华强朱运征谢安桓张丹朱世强
Owner ZHEJIANG LAB
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