Electromagnetic UAV launch system

Bhatia, Darshan Kiran; Aljadiri, Rita T.

doi:10.1109/icite.2017.8056924

Cited by 6 publications

(7 citation statements)

References 1 publication

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“…There are five launching device systems (LD) commonly used for launching UAVs: pneumatic, hydraulic, bungee cord, kinetic energy and rocket assisted take off (RATO) systems [4]- [8]. Also, there are other systems, such as electromagnetic LD [9] and spring drive LD [10]. Among those, the pneumatic and bungee cord LDs are the most frequently used.…”

Section: Launcher Design Theorymentioning

confidence: 99%

Design and Testing of a Bungee Cord Based Launcher for LSU-02 UAV

Budiyanta

Pranoto

Adi

et al. 2023

Majalah Ilmiah Pengkajian Industri

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The LSU-02 is one of the unmanned aerial vehicles (UAVs) developed by LAPAN (now BRIN). It has a good endurance and flight range, i.e., it can fly for four hours and up to 200 km. However, the UAV needs a good and long runway to do the takeoff and landing operations. In real missions, sometimes it is hard to find the proper runway. Therefore, a method for taking-off without a runway, namely using a launcher, is required. The two most frequently used launcher systems are pneumatic launcher and bungee cord launcher. However, based on our experience using the launcher for LSU-03 UAV, a pneumatic launcher is considered less practical due to its complex and heavy construction. For the LSU-02 to be able to carry out missions in remote areas, a simpler and lightweight launcher is needed. Therefore the bungee cord-based launcher was chosen. The initial requirement for the launcher is that the launcher should able to push the LSU-02 with a maximum takeoff mass of 15 kg put on a 7 kg cradle (total mass 22 kg) and reach the launch speed of 15.2 m/s at the end of launching track. The simulation result shows that the launcher needs a time of 0.28 s to achieve a velocity of 15.2 m/s. Meanwhile, in 0.28 s, the UAV travel distance is 2.55 m. This is the minimum effective length required by the launcher. The real launcher was built with an effective length of 2.7 m. The launcher was tested for launching the LSU-02 with the UAV takeoff mass of 14.4 kg and the cradle mass of 7.5 kg (total of 21.9 kg). It was able to successfully launch the LSU-02 in 0.27 s with a travel distance on the launching rail of 2.5 m. Keywords: Bungee cord, Design, Launcher, LSU-02, Testing, UAV

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Section: Launcher Design Theorymentioning

confidence: 99%

Design and Testing of a Bungee Cord Based Launcher for LSU-02 UAV

Budiyanta

Pranoto

Adi

et al. 2023

Majalah Ilmiah Pengkajian Industri

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“…Electromagnetic launchers provide precise control over acceleration. There are no restrictions on the weight of the aircraft with electromagnetic catapults (they are used on modern aircraft carriers [11]), and the increase in acceleration can be precisely controlled [12,13].…”

Section: Introductionmentioning

confidence: 99%

“…Navies of global leaders strive to retrofit their aircraft carriers with aircraft take-off and landing systems based on magnetic levitation. The leading example, in this case, is EMALS (Electromagnetic Aircraft Launching System) and the AAG (Advanced Arresting Gear) braking system developed by General Atomics for the US Navy [12,13]. The developed technology demonstrated that, compared to conventional steam devices, electromagnetic catapults accelerate aircraft in a smoother manner, reducing the load on their airframes; they are also smaller, generate less noise and their operation and maintenance are easier.…”

Section: Introductionmentioning

confidence: 99%

VR-Supported Analysis of UAV—Magnetic Launcher’s Cart System

2023

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The subject of the research is a model of a magnetic launcher, which is an innovative alternative to commercially occurring unmanned aircraft launchers (UAV). As the take-off is an energy-demanding phase of the flight; therefore, abandoning the power supply of the UAV during this phase significantly affects increasing the potential range and duration of UAV flight. The magnetic launcher offers the significant advantage of minimizing friction between the starting cart and the launcher, resulting in the higher energy efficiency of the system. Research conducted so far has shown that the possibility of accelerating the aircraft on the longer runway offered by the launcher reduces aircraft overloads occurring during take-off. As a result, the launcher, aircraft, and onboard equipment are much safer. This paper presents the system’s mathematical modeling and numerical simulation results for micro-class UAV take-off and landing using the analyzed magnetic launcher. The computer program for analyzing system dynamics was implemented in the MATLAB environment. Simulation results were visualized graphically and as animations in Virtual Reality. The VR application was implemented in Unity and ran on VR goggles Oculus Quest2. The simulations carried out show that—in the absence of control—an important factor reducing the takeoff distance and affecting the aircraft load is the adoption of a non-zero takeoff thrust of the UAV. The initial pitch angle also has a significant impact on the takeoff process. With an increase in this parameter, the length of the takeoff distance decreases and the lift-off speed decreases, but too much pitch angle may result in the aircraft descending in the first moments of flight, which could lead to a collision with the launch rails.

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“…The need for motion control, repeatability of startup parameters, protection against overloads and operator safety has numerous researchers working, in Poland as well as abroad, on controlled launcher design. The investigation of electrically powered devices has been particularly popular and has been considered both in the past [10][11][12] as well today [13][14][15][16][17], even concerning for UAVs of a few hundred kilograms weight [18]. A prototype of a synchronous magnetic launcher for MAVs having a mass up to 2 kg has been developed at the BUT [8,[19][20][21] with research into a similar prototype for aircraft weighing 10, 20 and 25 kg also initiated [22].…”

Section: Introductionmentioning

confidence: 99%

Design and Dynamics of Kinetic Launcher for Unmanned Aerial Vehicles

Kondratiuk

Ambroziak

2020

Applied Sciences

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Assisting in the starting procedure of Unmanned Aerial Vehicles (UAVs) is one of many very important areas of modern aviation research. Supported start-up saves fuel or electrical energy, increases operator safety and level of autonomy, extends the application area, and, in some applications, even enables the operator to shape the motion characteristics of the initial phase of a UAV’s flight. Currently used solutions, depending on an aircraft’s class, are based on the utilization of rubber, pneumatic or electromagnetic launchers. All of these launchers are used for the medium class of UAVs and all of them use the potential energy previously stored in stretched rubber, compressed air or electrical voltage. In this paper, authors propose the novel concept of a launcher powered through kinetic energy stored in a rotary wheel driven by an electric motor. Using the transmission systems of the drive and the controlled clutch and an electromagnetic brake, it is possible to precisely control the speed and acceleration of the launched object. Within the paper, the authors present and discuss the applied equations of dynamics, the results of a simulation that was carried out using the MATLAB/Simulink software and a conceptual CAD model of preliminary engineering solutions for the kinetic UAV launcher. The work is summarized in the conclusions section, which details the practical implementation of the device.

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Electromagnetic UAV launch system

Cited by 6 publications

References 1 publication

Design and Testing of a Bungee Cord Based Launcher for LSU-02 UAV

Design and Testing of a Bungee Cord Based Launcher for LSU-02 UAV

VR-Supported Analysis of UAV—Magnetic Launcher’s Cart System

Design and Dynamics of Kinetic Launcher for Unmanned Aerial Vehicles

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