Integration of a 7-kW Turboelectric Power System in a Vertical Take-Off and Landing Unmanned Aircraft

Johnsen, Joshua; Runnels, Timothy; Burgess, Johnathan M.; Rouser, Kurt P.

doi:10.2514/6.2021-3727

Cited by 3 publications

(10 citation statements)

References 4 publications

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“…Johnsen et al [18] previously laid out the rationale and analysis for the sizing and selection of the major components of the turboelectric propulsion and power system. The reader is directed to that previous work for details of the design, progressing logically from the lift rotors required for VTOL operation, propeller for horizontal flight, turbine engine for the main source of power, and then generator, battery, and electrical components for conditioning, distributing, and managing electrical current, and then, finally, the airflow required for cooling.…”

Section: Methodsmentioning

confidence: 99%

“…The turboelectric system includes the weights of the turboprop, system casing, rectifier, fuel pump, and ECU, as shown in Figure 4. There were components, such as the engine casing, with potential for weight reduction by a few pounds [18]. Overall these percentages are a good starting point for future aircraft.…”

Section: Aircraft Weight Breakdownmentioning

confidence: 97%

“…It was assumed that the turboelectric system would have the K-60TP turboprop running at full throttle during cruise (as shown later in the results section for power data). The turboprop is most fuel efficient near its maximum throttle [18]. An estimate of endurance can be calculated using the maximum fuel burn rate from the test bench [15].…”

Section: Fuel Burnmentioning

confidence: 99%

“…This aircraft has a maximum takeoff weight of 391 N (88 lbf) and includes four electrically driven lift rotors. The aircraft is powered by a turboelectric system based on a Kingtech K-60TP turboprop and includes batteries in a series hybrid configuration [18]. The K-60TP generates electrical power by driving a brushless DC motor mechanically coupled to the output shaft from the power turbine reduction gearbox.…”

Section: Introductionmentioning

confidence: 99%

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Integration and Flight Test of a 7 kW Turboelectric Vertical Take-Off and Landing Unmanned Aircraft

Johnsen¹,

Runnels²,

Burgess³

et al. 2022

Applied Sciences

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This paper evaluates the performance and practical challenges associated with fabricating and flight testing an unmanned aircraft powered by a turboelectric system based on a 7 kW turbine engine. Emerging hybrid gas-electric aircraft concepts have been the subject of numerous design studies and analytical evaluations; however, there is a critical need to identify and assess practical issues associated with integrating a hybrid turboelectric power system into an aircraft. The purpose of this study, relevant to emerging hybrid-powered aircraft, is to evaluate and retrofit a prototype turboelectric power system to an existing 391 N gross take-off weight unmanned airframe. The representative 7 kW turboelectric system was installed to identify challenges and to formulate data-driven recommendations for general application to urban air mobility. This work addresses performance, power and thermal management, vibration, and acoustic emissions. Results include a weight breakdown with the turboelectric system making up 21% of the total aircraft weight, in-flight voltage and current measurements with maximum loads observed during a dive pull-out, temperature measurements, accelerometer measurements, and far field sound pressure level measurements. Practical recommendations from this study are applicable to power system reliability, electronic component selection, cooling requirements, and peak power behavior, informing the design of future hybrid gas–electric aircraft.

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Section: Methodsmentioning

confidence: 99%

Section: Aircraft Weight Breakdownmentioning

confidence: 97%

Section: Fuel Burnmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Integration and Flight Test of a 7 kW Turboelectric Vertical Take-Off and Landing Unmanned Aircraft

Johnsen¹,

Runnels²,

Burgess³

et al. 2022

Applied Sciences

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“…The integration of this actively controlled turboelectric system in a VTOL UAS was conducted successfully [21]. Oklahoma State University has flown the featured turboelectric system on two platforms testing and proving flight worthiness.…”

Section: Future Workmentioning

confidence: 99%

Experimental Comparison of Direct and Active Throttle Control of a 7 kW Turboelectric Power System for Unmanned Aircraft

Burgess¹,

Runnels²,

Johnsen³

et al. 2021

Applied Sciences

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This article compares direct turbine throttle control and active turbine throttle control for a turboelectric system; the featured turboprop is rated for 7 kW of shaft output power. The powerplant is intended for applications in unmanned aerial systems and requires a control system to produce different amounts of power for varying mission legs. The most straightforward control scheme explored is direct turbine control, which is characterized by the pilot controlling the throttle of the turbine engine. In contrast, active control is characterized by the turbine reacting to the power demanded by the electric motors or battery recharge cycle. The transient response to electric loads of a small-scale turboelectric system is essential in identifying and characterizing such a system’s safe operational parameters. This paper directly compares the turbogenerator’s transient behavior to varying electric loads and categorizes its dynamic response. A proportional, integral, and derivative (PID) control algorithm was utilized as an active throttle controller through a microcontroller with battery power augmentation for the turboelectric system. This controller manages the turbine’s throttle reactions in response to any electric load when applied or altered. By comparing the system’s response with and without the controller, the authors provide a method to safely minimize the response time of the active throttle controller for use in the real-world environment of unmanned aircraft.

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The Critical Threshold of The Relationship Between Take-Off Load And Powertrain Load of the Aircraft

Yao

2023

HSET

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The critical threshold of the relationship between take-off load and powertrain load of the aircraft has long intrigued researchers and posed significant challenges. Delving into this subject, extensive research has been conducted to comprehend the intricate dynamics between these two variables. This thesis aims to contribute to this ongoing investigation by analyzing and drawing conclusions based on observed load variations and their impact on power system functionality. The study encompasses a comprehensive examination of various aircraft types, ranging from ultralight aircraft to wide-bodied aircraft and Unmanned Aerial Vehicles (UAVs). Each aircraft category presents unique characteristics and demands distinct engine requirements, further complicating understanding the take-off load to powertrain load relationship. By meticulously studying the changes in loads during the crucial take-off phase, this research aims to uncover valuable insights into the essentiality of an efficient power system. The findings of this study have the potential to enhance aircraft design and operations, ultimately leading to safer and more optimized flight experiences.

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Integration of a 7-kW Turboelectric Power System in a Vertical Take-Off and Landing Unmanned Aircraft

Cited by 3 publications

References 4 publications

Integration and Flight Test of a 7 kW Turboelectric Vertical Take-Off and Landing Unmanned Aircraft

Integration and Flight Test of a 7 kW Turboelectric Vertical Take-Off and Landing Unmanned Aircraft

Experimental Comparison of Direct and Active Throttle Control of a 7 kW Turboelectric Power System for Unmanned Aircraft

The Critical Threshold of The Relationship Between Take-Off Load And Powertrain Load of the Aircraft

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