Design and Dynamics of Kinetic Launcher for Unmanned Aerial Vehicles

Kondratiuk, Mirosław; Ambroziak, Leszek

doi:10.3390/app10082949

Cited by 7 publications

(8 citation statements)

References 16 publications

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“…The signal in this case is the pressure of the compressed air flowing through the connecting lines. Calculation of the cycle time of the pneumatic drive system comes down to the calculation of the operating time of the elements it consists of, i.e., to the dynamic analysis of these elements [3,[9][10][11][12].…”

Section: Research Objectmentioning

confidence: 99%

“…The operating cycle of the control and drive system is described by equations: change of pressure in the working chamber (1) [10], change of pressure in the evacuated chamber (2) [3,6,10,14], equation of motion (3) [3,7,10,14].…”

Section: Research Objectmentioning

confidence: 99%

“…To solve Equations ( 1) and ( 2), it is necessary to determine the mass intensity of the air stream flowing into the working chamber and the air stream flowing from the emptied chamber. Based on the analysis of the literature [3,7,10,14], the general form of the mass flow rate equation was adopted:…”

Section: Research Objectmentioning

confidence: 99%

“…The use of catapults also increases the operational capabilities of UAVs and eliminates the need to use airport runways for their take-off. Due to their operational qualities, pneumatic launchers are the most widely used [1][2][3][4]. Kondratiuk [3] and Gan et al [4] showed that, due to the power and take-off efficiency as well as operational values, pneumatic launchers were the most used.…”

Section: Introductionmentioning

confidence: 99%

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Estimating the Useful Energy of a Launcher’s Pneumatic Launch System UAV

Jastrzębski

Ułanowicz

2022

Energies

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The motivation behind solving the issue of estimating the flow parameters of the pneumatic system of a launcher was the need to obtain the take-off energy with a value exceeding 80 kJ. The take-off energy and the initial speed of the unmanned aerial vehicle (UAV) depends on the pressure drop time in the launcher’s pneumatic system. The aim of the research was to estimate the flow parameters of the trigger system of the UAV launchers in order to achieve the shortest time of its operation. Due to the lack of a description of the selection of pneumatic elements and their flow characteristics in the available literature, the article attempts to analytically describe the air flow through pneumatic units. The trigger system is described using the sonic conductivity and the critical pressure ratio. Due to the lack of numerical data on the flow parameters of pneumatic units, a test stand was designed and constructed to determine these parameters. The values of the sound conductivity and the critical pressure ratio were determined for each of the pneumatic units and for the entire system. The proposed method makes it possible to determine the relationship between the operating time and the values of the flow parameters of the pneumatic launch tube release system. It also provides guidelines for design and technological solutions for the trigger system of any pneumatic launcher.

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Section: Research Objectmentioning

confidence: 99%

Section: Research Objectmentioning

confidence: 99%

Section: Research Objectmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Estimating the Useful Energy of a Launcher’s Pneumatic Launch System UAV

Jastrzębski

Ułanowicz

2022

Energies

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“…Among them, the tailsitter has been a hot spot due to its simple design. Over the UAVs assisted with a launcher [9], the tail-sitter has the advantages of convenience and fast takeoff and landing ability. However, compared to the tilt wing or tilt rotors, most of tailsitters are less controllable in pitch motion during low-speed flight conditions, for example the early stage of the forward transition flight.…”

Section: Introductionmentioning

confidence: 99%

Transition Flight Control and Simulation of a Novel Tail-Sitter UAV With Varying Fuselage Shape

et al. 2021

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This article studies the model, control and simulation on transition flight of a novel tail-sitter with vertical takeoff and landing capability. The proposed tail-sitter adopts an innovative varying fuselage shape design to break the technical bottleneck in the balance of efficient horizontal flight and agile vertical flight. Overset grids and computational fluid dynamic methods are used to explore the vehicle's prestall aerodynamics, which are relative to not only the angle of attack and sideslip angle but also to the varying angle between two rear fuselage's parts. High angle of attack aerodynamics based on the improved Viterna and Corrigan stall model is also established for this novel tail-sitter. Meanwhile, an accurate model of the propeller is tested in a wind tunnel. Combining the forces and moments generated by propellers, aerodynamics and gravity, a 6DoF nonlinear timevarying dynamic model is built. A robust controller based on incremental dynamic inversion method is designed for this tail-sitter, which is good at dealing with uncertainties and external forces. Nominal and model mismatch conditions are simulated to verify the controller's performance. Different varying strategies for the mechanism are analyzed during the transition flight. Simulation results show that this novel tail-sitter can transform between vertical and horizontal flight mode easily and the varying strategy related to pitch angle is a prior choice for transition flight. INDEX TERMSNovel tail-sitter; Varying fuselage shape; Transition flight; Incremental nonlinear inversion method; Vertical takeoff and landing.

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