A Study on Transient Performance Characteristics of the Canard Rotor Wing Type Unmanned Aerial Vehicle Propulsion System During Flight Mode Transition

2005 ◽  
Vol 128 (3) ◽  
pp. 573-578 ◽  
Author(s):  
Changduk Kong ◽  
Jongha Park ◽  
Myoungcheol Kang
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Propulsion System ◽  
Performance Characteristics ◽  
Mode Transition ◽  
Transient Performance ◽  
Turbojet Engine ◽  
Flight Mode ◽  
Rotor Wing ◽  
Aerial Vehicle ◽  
Rotary Wing

A propulsion system of the CRW (Canard rotor wing) type UAV (unmanned aerial vehicle) was composed of the turbojet engine, exhaust nozzles (including some tip jet nozzles and a main nozzle), and the duct system (including straight ducts, curved ducts, and master valve). The CRW-type UAV has three different flight modes, such as the rotary wing mode for takeoff and landing, the high-speed forward flight mode with the fixed wing, and the transition flight mode between the previously mentioned two flight modes. In order to evaluate transient performance characteristics of the CRW-type UAV propulsion system during flight mode transition, the propulsion system was modeled using SIMULINK®, which is a user-friendly graphical-user-interface-(GUI) type dynamic analysis tool provided by MATLAB, in this study. The transition flight mode between the rotary wing mode and the fixed wing mode was simulated by considering area variation of the master valve and the main exhaust nozzle. In order to verify acceptability of the main turbojet engine model, performance simulation results using SIMULINK were compared to results using the commercial program GSP. Through this simulation, proper operation of the master valve and the variable area main nozzle can be found for safe flight transition. Therefore, performance characteristics were investigated depending on various angle positions of the master valve.

A Study on Transient Performance Characteristics of the CRW Type UAV Propulsion System During Flight Mode Transition

2005 ◽  
Author(s):  
Changduk Kong ◽  
Jongha Park ◽  
Myoungcheol Kang
Keyword(s):  
Propulsion System ◽  
Performance Characteristics ◽  
Mode Transition ◽  
Main Duct ◽  
Transient Performance ◽  
Steady State Condition ◽  
Turbojet Engine ◽  
Flight Mode ◽  
Rotary Wing ◽  
Transition Flight

A propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) was composed of the turbojet engine, exhaust nozzles including some tip jet nozzles and a main nozzle and the duct system including straight ducts, curved ducts and master valve. The CRW type UAV has three different flight modes such as the rotary wing mode for take-off and landing, the high-speed forward flight mode with the fixed wing and the transition flight mode between the previously mentioned two flight modes. In order to evaluate transient performance characteristics of the CRW type UAV propulsion system during flight mode transition, the propulsion system was modeled using SIMULINK®, which is an user-friendly GUI type dynamic analysis tool provided by MATLAB, in this study. Considering area variation of the master valve and the main exhaust nozzle simulated the transition flight mode between the rotary wing mode and the fixed wing mode. In order to verify acceptability of the main turbojet engine model, performance simulation results using SIMULINK® were compared with results using the commercial program GSP. Moreover the performance characteristics of the propulsion system were investigated depending on position angle variation of the master valve at both the rotary wing mode and the fixed wing mode. In the transient performance behaviors at the rotary wing flight mode, the more turbine inlet temperature over shoot occurs and the net thrust at tip jet nozzles, decreases rapidly at initial condition then increase fast to the converged steady-state condition. Therefore, the fuel throttle should be slowly performed for safe operation of engine. During flight mode transition from the rotary wing mode to the fixed wing mode, rotary duct pressure was fell down to atmospheric pressure, but main duct pressure was mostly kept due to very small friction loss. Total net thrust was oscillatory increased. During flight mode transition from the fixed wing mode to rotary wing mode, rotary duct pressure was rapidly increased, but main duct pressure was mostly kept. Total net thrust also was oscillatory decreased. Through this investigation, it was found that severe thrust fluctuation should be considered for safe flight during flight mode transition even though operation of the master valve is slowly scheduled. Therefore a solution for improving the thrust oscillation will be suggested later.

Steady-State/Transient Performance Simulation of the Propulsion System for the Canard Rotor Wing UAV During Flight Mode Transition

2004 ◽  
Author(s):  
Changduk Kong ◽  
Myoungcheol Kang ◽  
Jayoung Ki ◽  
Jongha Park ◽  
Sooseok Yang
Keyword(s):  
Steady State ◽  
High Speed ◽  
Propulsion System ◽  
Duct System ◽  
Forward Flight ◽  
Performance Simulation ◽  
Flight Mode ◽  
Rotor Wing ◽  
Main Engine ◽  
Rotary Wing

A steady-state/transient performance simulation model was newly proposed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) in various flight modes. The studying CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by the engine bypass exhaust gas and the high speed forward flight mode using the fixed wing and main engine thrust. The proposed propulsion system is consisted of the main engine system and the duct system. A flight vehicle may generally select the engine with a proper type and a specific model with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip nozzles, and variable main nozzle. In order to establish the safe operation of the propulsion system, performance simulation should be needed. In this study, a performance model of the Smart UAV propulsion system with ducts, tip jets and variable main nozzle, which has flight capability of the rotary wing mode for the take-off/landing and low speed forward flight as well as the fixed wing mode for high speed forward flight, has been newly developed. With the proposed model, steady-state performance analysis was performed at various flight modes and conditions, such as rotary wing mode, fixed wing mode, compound wing mode, altitude and flight speed. Through this analysis, it was confirmed that the engine performance simulation results without the duct system were well agreed with the engine manufacturer’s data, and the safe operation range of the proposed propulsion system was investigated at three flight modes. And the dynamic behavior of the system was modeled and simulated using the SIMULINK®.

Modeling and control of a quadrotor tail-sitter unmanned aerial vehicles

2021 ◽  
pp. 095965182110504
Author(s):  
Hongbo Xin ◽  
Yujie Wang ◽  
Xianzhong Gao ◽  
Qingyang Chen ◽  
Bingjie Zhu ◽  
...  
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Euler Angle ◽  
Level Flight ◽  
Aerial Vehicles ◽  
Flight Mode ◽  
Aerial Vehicle ◽  
Hover Flight ◽  
And Control

The tail-sitter unmanned aerial vehicles have the advantages of multi-rotors and fixed-wing aircrafts, such as vertical takeoff and landing, long endurance and high-speed cruise. These make the tail-sitter unmanned aerial vehicle capable for special tasks in complex environments. In this article, we present the modeling and the control system design for a quadrotor tail-sitter unmanned aerial vehicle whose main structure consists of a traditional quadrotor with four wings fixed on the four rotor arms. The key point of the control system is the transition process between hover flight mode and level flight mode. However, the normal Euler angle representation cannot tackle both of the hover and level flight modes because of the singularity when pitch angle tends to [Formula: see text]. The dual-Euler method using two Euler-angle representations in two body-fixed coordinate frames is presented to couple with this problem, which gives continuous attitude representation throughout the whole flight envelope. The control system is divided into hover and level controllers to adapt to the two different flight modes. The nonlinear dynamic inverse method is employed to realize fuselage rotation and attitude stabilization. In guidance control, the vector field method is used in level flight guidance logic, and the quadrotor guidance method is used in hover flight mode. The framework of the whole system is established by MATLAB and Simulink, and the effectiveness of the guidance and control algorithms are verified by simulation. Finally, the flight test of the prototype shows the feasibility of the whole system.

scholarly journals Penentuan Lintasan Pergerakan Quadcopter Berbasis GPS (Global Positioning System)

2019 ◽  
Vol 1 (2) ◽  
pp. 1-14
Author(s):  
Abdur Rohman Harits Martawireja ◽  
Hadi Supriyanto
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Global Positioning System ◽  
Positioning System ◽  
Global Positioning ◽  
Aerial Vehicle ◽  
Rotary Wing

UNMANNED AERIAL VEHICLE (UAV) merupakan sebuah kendaraan udara tanpa awak yang dapat dikendalikan. Terdapat dua tipe UAV, yakni fixed wing dan rotary wing. Quadcopter menjadi salah satu tipe UAV rotary wing yang banyak digunakan dalam berbagai kebutuhan, seperti eksplorasi dan pengambilan citra. Pada penelitian ini Quadcopter berfungsi sebagai kendaraan yang harus bergerak mengikuti lintasan, dimana lintasan yang dikuti oleh Quadcopter berasal dari GPS yang dihasilkan oleh objek yang diikuti (Modul Utama). Tipe GPS yang terpasang pada Quadcopter (GPS1) maupun pada Modul Utama (GPS2) adalah  GPS Ublox NEO. Prinsip kerja sistem adalah quadcopter mengikuti Koordinat-koordinat lintasan yang dihasilkan oleh GPS1, di mana data-data lintasan GPS1 dikirim ke Quadcopter menggunakan media Bluetooth.  Dalam pergerakannya, Quadcopter akan terus-menerus membandingkan data-data koordinat yang dihasikan posisi Quadcopter dengan data-data koordinat lintasan yang sudah diterima. Pengujian pada Receiver GPS Modul Utama (GPS1) dan Receiver GPS Quadcoter (GPS2), kedua GPS mampu mendapatkan data GPS dari satelit.  Kesalahan/perbedaan data dari GPS1 dan GPS2  pada pengujian pergerakkan Quadcopter  untuk mengikuti  Modul Utama sebagai titik tujuan sebesar 53% pada garis lintang dan 51% pada garis bujur.

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