Some Challenging Aspects of Optimal Power Management of Unmanned Aerial Vehicle Modular Hybrid Propulsion Systems

An optimal control framework has been developed to assess the operation of an unmanned aerial vehicle (UAV) powered by a modular hybrid propulsion system (MHPS). The framework is used to assess the effects of MHPS power hybridization level and energy hybridization mass ratio on the UAV performance for two specified mission types. The results are then used to suggest selection guidelines for MHPS configurations and operational guidelines for an MHPS-powered UAV to execute various mission types with different mission requirements. Two specific mission types are selected for illustration: one, a Survey mission, consisting of climb, dash, survey, dash, and descent phases; the other, a Loiter mission, consisting of climb, dash, loiter, dash, and descent phases. Power hybridization level 𝐻ₚ refers to the percentage of propulsive power sourced from the electric motor, rather than the internal combustion engine. Energy hybridization mass ratio 𝑅ₘ refers to the percentage of energy storage system mass taken up by batteries, rather than carbon fuel. From the results of Survey mission execution optimized for minimum completion time, there are three distinct regimes defined by energy storage system (ESS) mass ratio values 𝑅ₘ₁ and 𝑅ₘ₂. MHPS configurations with 𝑅ₘ₁ ≤ 𝑅ₘ ≤ 𝑅ₘ₂ can achieve the minimum attainable mission completion time; mission completion time is longer, and total energy consumption is lower, for configurations with 𝑅ₘ < 𝑅ₘ₁ and 𝑅ₘ > 𝑅ₘ₂. From the results of Loiter mission execution optimized for minimum energy consumption, there is a distinct demarcation boundary at a threshold value of ESS mass ratio 𝑅ₘ₃ for each specific 𝐻ₚ . All UAV MHPS configurations with 𝑅ₘ ≥ 𝑅ₘ₃ will utilize the same amount of energy to complete the mission; configurations with 𝑅ₘ < 𝑅ₘ₃ require higher energy consumption to complete the same mission.

Name thesis:degree_name

Master

Department dc:contributor.department

Massachusetts Institute of Technology. Department of Aeronautics and Astronautics

Grantor dc:publisher

Massachusetts Institute of Technology

Year dc:date.issued

2022

Author dc:creator

• Kunycky, Alexander

Advisor dc:contributor.advisor

• Tan, Choon Sooi

Statement dc:rights

• In Copyright - Educational Use Permitted
• Copyright MIT

Licence dc:rights.uri

• http://rightsstatements.org/page/InC-EDU/1.0/

Handle dc:identifier.uri

https://hdl.handle.net/1721.1/143263

OAI identifier oai:identifier

oai:dspace.mit.edu:1721.1/143263