• Current Industrial and Technological Trends in Aerospace
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• v.9 no.1
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• pp.64-76
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• 2011

The current development trend and status of a personal air vehicle, known as the novel concept of a transportation that combines a personal car with a light general aviation aircraft, is summarized to investigate its feasibility as a future transportation. In the paper, the development programs of a personal air vehicle such as AGATE, PAVE, SATS and NGATS are first summarized, and then the design, technical development and testing activities of Terrafugia's Transition and Moller International's M400 Skycar, which will be commercialized in a short time, are reviewed. Based on the assessment of technical issues with those vehicles, the key technologies for the future development of the personal air vehicle are suggested with two basic requirements of safety and mobility.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.6
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• pp.56-63
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• 2009

In this paper, we present technical survey results on propulsion systems for Personal Air Vehicles (PAV). Reciprocating engines are suitable for current PAVs because of their superior efficiency and price advantages, except they produce noise problems. Turbo-Shaft engines are suitable for VTOL PAVs because of high specific power and wide operating range even though they are expensive. However, fuel cells and batteries may replace conventional engines in the near future.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.3
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• pp.101-108
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• 2006

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.6-13
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• 2007

PAV(Personal Air Vehicle) can be an alternative of the saturated ground transportation in future and can be available in any time and anywhere. This paper describes some overview on high speed rotorcraft concepts for the PAV applications. First the requirement of PAV is surveyed. Then the existing concepts of high speed rotorcrafts are reviewed. Several on-going projects are summarized. Finally! technical issues of high speed rotorcraft to apply to PAV platform are explored.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.183-186
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• 2011

In this paper, we present some results of power analyses, and weight estimation on electric propulsion systems for Personal Air Vehicles(PAV) applications. When hybrid electric propulsion is adopted, its power performance using fuel cells and batteries is inferior to that of internal combustion engines for 1,000 kg PAV. However, hybrid electric propulsion systems may replace IC engines when energy density and power density is over $0.75kW{\cdot}hr/kg$and 2.5 kW/kg, respectively.

• Journal of Aerospace System Engineering
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• v.8 no.4
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• pp.1-6
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• 2014

This paper presents the trade-off study of conducting a survey of the weights for various kind of propulsion systems installed in the Smart Unmanned Aerial Vehicle TR-100, a tilt-rotor vehicle, which is developed by Korea Aerospace Research Institute, in order to predict the appropriate propulsion system for present and future Personal Air Vehicle, which has single mode and vertical take-off & landing. In order to perform the trade-off study, we set the requirements that the vehicle hovers for 1 hour with 1,000 kg maximum take off weights. In this study, the power systems are classified engine, which uses the fossil fuel - turboshaft engine, piston engine, diesel engine and rotary engine, and electric motor with fuelcell or Li-Ion battery. The results of trade-off study shows the power systems using fossil fuel are superior to using fuelcell or Li-Ion battery for weight of propulsion system. Also turboshaft engine is the best power system for the aspects of system weight, and the nexts are rotary engine, piston engine, diesel engine, electric motor with Li-Ion battery, and electric motor with fuelcell.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.21 no.5
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• pp.53-60
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• 2022

In this study, the conceptual design and performance evaluation of a personal air vehicle (PAV) is presented, which is a potential futuristic individual transportation. The blade element theory (BET) is employed to compute a rotational velocity. A computational fluid dynamics (CFD) simulation is performed to investigate the difference in the thrust performance in the rotor axis distance of a quad-copter PAV in hovering. Modal analysis is performed to create a Campbell diagram to investigate critical speed. Consequently, a quad-copter PAV changes the aerodynamics thrust and critical velocity according to the rotor axis distance.

• Electronics and Telecommunications Trends
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• v.38 no.3
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• pp.1-10
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• 2023

In this study, the status of global advanced air mobility (AAM) was investigated to derive information and communications technologies (ICTs) that should be prepared according to directions of domestic AAM development. AAM is an urban air traffic system for moving from city to city by electric vertical take-off and landing or personal aircraft. It is expected to establish a three-dimensional air traffic system that can solve ground traffic congestion caused by the rapid global urbanization. With the full-scale commercialization of AAM solutions, high-density air traffic is expected, and with the advent of the personal air vehicle (PAV), the flight space usage is expected to expand. Therefore, it is necessary to develop a safe AAM service through early research on core ICTs for autonomous flight.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.28 no.1
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• pp.83-89
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• 2020

Personal air vehicle (PAV) is considered by aviation engineers as a solution to provide fast urban mobility. The purpose of designing a optionally piloted PAV (OPPAV) is to provide an individual air vehicle. The airframe structure is designed with high strength carbon fiber composite to reduce the aircraft weight. This paper presents an overview of sizing process for OPPAV at the conceptual design level. It consists of load analysis, structural sizing and development of efficient design allowable values for composite material. The weight is estimated based on sizing process, including strength and stiffness requirements. The objective of this study is to present a overview of structural sizing procedure and fast tool for preliminary design phases.

• Journal of Aerospace System Engineering
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• v.13 no.3
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• pp.56-63
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• 2019

Performance analyses were performed on a propeller developed for use in a PAV (Personal Air Vehicle) under 600 kg Maximum Take-Off Weight (MTOW). The actuator disc theory and CFD analyses were used to estimate the hovering time with regards to MTOW variation for a given battery weight. The interference induced power factor kint was introduced to account for the effect of flow interference between the propellers and to estimate the performance of counter-rotating propellers. The Maximum Figure of Merit (FM) value of the propeller pitch was determined and the design RPM range for the required power inversely obtained from the CFD results. Previous research indicate that the flight time of large multi-copter is limited by the available battery energy density. Similarly, the propeller pitch settings and spacing are important factors in reducing the kint value.