Design of a Hybrid Heavy Multirotor with Long Range and High Payload Carrying Capacity for Using in Disaster Management

Document Type : Research Paper

Authors

1 Department of Aerospace Engineering, Amirkabir University of Science and Technology, Tehran, Iran

2 Aerospace Engineering Department,, Amirkabir University of Technology, Tehran, Iran

3 Space Transportation Research Institute, Iranian Space Research Center, Tehran, Iran

Abstract

This study presents the conceptual design of an unmanned multirotor with a novel configuration whose main application is disaster management. This multirotor can carry 800 kg of cargo for a range of 400 km, and its forward flight speed is 100 km/h. A multirotor with the specified performance parameters has not yet been developed. Due to the stipulated performance, the electric propulsion system is inapplicable, and a hybrid propulsion system is considered for this multirotor. The hybrid propulsion system without energy conversion was selected for the proposed design after further investigating alternative hybridization approaches. Multirotor subsystems are conceptually designed based on take-off weight, i.e., take-off weight is first estimated, and then multirotor subsystems are designed based on it. Finally, the overall subsystems’ weight is compared to the predicted take-off weight. If there is a significant discrepancy, the procedure is repeated until the two values converge. This paper presents the last design loop, and the specifications of the electric propulsion system, fuel propulsion system, power transmission system, body structure, and skid are calculated.

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References

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