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Multi-rotor aircraft power system and a rapid aircraft body design method

A technology of multi-rotor aircraft and power system, which is applied in the field of rapid design of multi-rotor aircraft power system and fuselage, and can solve the problems of high cost and low efficiency

Active Publication Date: 2019-04-19
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But this method is inefficient and expensive

Method used

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  • Multi-rotor aircraft power system and a rapid aircraft body design method
  • Multi-rotor aircraft power system and a rapid aircraft body design method
  • Multi-rotor aircraft power system and a rapid aircraft body design method

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Embodiment Construction

[0092] Before executing the online method, the offline method is implemented as follows.

[0093] For the motor model is JFRC U3508KV550 (I mMax =20A U mMax =22.2VK v =550) motor, the battery type is ACE LiPo 6S 5300mHA (U b =22.2V I mMax =159A C b =5300mHA) battery, the ESC model is HobbyWing X-Rotor 40A (U eMax =22.2V I eMax =40A), assuming that the optional propellers are shown in Table 2:

[0094] APC 13x5.5

12x5.5CF

APC 12x4.5

APC 11x5.5

APC 10x4.5

GF 10x4.5

APC 10x3.8

DJI 9.4x5

[0095] Table 2 Available propeller models

[0096] According to the off-line method steps, the screened results are shown in Table 3. If the propeller size is too large (Table 3: >12x5.5), formula (1) cannot be satisfied, because the current at full throttle Exceeded the motor's maximum limit of 20A, so it was ruled out. If the propeller is too small (Table 3: mep is too small and is therefore also excluded. Therefore, only two prope...

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Abstract

The invention provides a multi-rotor aircraft power system and fuselage rapid design method, which comprises the following steps of: after a design requirement is given, calculating a plurality of groups of combinations of a power system, a fuselage and a battery which meet the design requirement through an offline calculation optimization and pre-stored power system database, and sorting the results according to the advantages and disadvantages. The method is divided into two parts: the first part is an offline method; The method comprises the following five steps: step 1, selecting a power system combination meeting requirements for a certain motor; And step 2, calculating the obtained parameters of the power system. Step 3, standardizing parameters. And step 4, calculating an index function, and selecting an optimal combination. And 5, repeating the previous four steps, and establishing a power system combination database. The second part is an online method and is divided into three stages: the first stage: screening power system combinations meeting requirements according to requirements; In the second stage, battery and machine body parameters are selected; And in the third stage, the objective function is calculated, and the results are sorted.

Description

technical field [0001] The invention relates to a fast design method for a power system and fuselage of a multi-rotor aircraft, belonging to the field of design. Background technique [0002] With the development of aircraft technology, the market demand is increasing. Facing the needs of different industries, a large number of aircraft of different sizes, different loads, and different endurance times need to be designed. The present invention is mainly aimed at the overall type selection design of the multi-rotor aircraft, including the type selection of the power system (motor, propeller, electric adjustment), fuselage and battery. In the actual design process, a lot of trial and error experiments are often required to select the power system, airframe and battery capacity that meet the specific design requirements. But this method is inefficient and expensive. Therefore, a rapid design method for the power system and fuselage of a multi-rotor aircraft is very meaningfu...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F2111/06G06F2111/04G06F2113/28G06F30/15G06F2119/06Y02T90/00
Inventor 全权戴训华柯晨旭
Owner BEIHANG UNIV
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