scholarly journals Sizing of a Turboprop Engine Powered High Altitude Unmanned Aerial Vehicle and It`s Propulsion System for an Assumed Mission Profile in Turkey

2020 ◽  
Vol vm01 (is01) ◽  
pp. 5-8
Author(s):  
Ali Dinç
Keyword(s):  
High Altitude ◽  
Unmanned Aerial Vehicle ◽  
Forest Fires ◽  
Power Level ◽  
Aircraft Design ◽  
Propulsion System ◽  
Target Cost ◽  
Turboprop Engine ◽  
Aerial Vehicle ◽  
Mission Profile

In this study, preliminary sizing of a turboprop engine powered high altitude unmanned aerial vehicle and it`s propulsion system for an assumed mission profile in Turkey was performed. Aircraft mission profile is one of the most important design inputs in aircraft design. While the aircraft is dimensioned according to the requirements in the specification (useful payload, range, target cost, etc.), parameters such as cruise altitude and speed within the mission profile affect the engine type, power level, fuel quantity, and therefore the overall dimensions and total weight of the aircraft. The unmanned aerial vehicle with turboprop engine investigated in this study, can stay in the air for at least 24 hours at high altitude (40000 ft) and can be used for border surveillance, coast control, forest fires and land exploration.

scholarly journals SIZING OF A TURBOPROP ENGINE POWERED HIGH ALTITUDE UNMANNED AERIAL VEHICLE AND IT`S PROPULSION SYSTEM FOR AN ASSUMED MISSION PROFILE IN TURKEY

2019 ◽  
pp. 19-23
Author(s):  
Ali DİNÇ
Keyword(s):  
High Altitude ◽  
Unmanned Aerial Vehicle ◽  
Forest Fires ◽  
Power Level ◽  
Aircraft Design ◽  
Propulsion System ◽  
Target Cost ◽  
Turboprop Engine ◽  
Aerial Vehicle ◽  
Mission Profile

ABSTRACT In this study, preliminary sizing of a turboprop engine powered high altitude unmanned aerial vehicle and it`s propulsion system for an assumed mission profile in Turkey was performed. Aircraft mission profile is one of the most important design inputs in aircraft design. While the aircraft is dimensioned according to the requirements in the specification (useful payload, range, target cost, etc.), parameters such as cruise altitude and speed within the mission profile affect the engine type, power level, fuel quantity, and therefore the overall dimensions and total weight of the aircraft. The unmanned aerial vehicle with turboprop engine investigated in this study, can stay in the air for at least 24 hours at high altitude (40000 ft) and can be used for border surveillance, coast control, forest fires and land exploration.

scholarly journals Stepwise fusion algorithm with dual correction for multi-sensor navigation

2018 ◽  
Vol 15 (3) ◽  
pp. 172988141877993 ◽  
Author(s):  
Rong Wang ◽  
Zhi Xiong ◽  
Jianye Liu ◽  
Yuxuan Cao
Keyword(s):  
High Altitude ◽  
Unmanned Aerial Vehicle ◽  
Error Estimation ◽  
Attitude Determination ◽  
Vehicle Navigation ◽  
Fusion Algorithm ◽  
Aerial Vehicle ◽  
Determination System ◽  
Long Endurance ◽  
Sensor Navigation

In high-altitude, long-endurance unmanned aerial vehicles, a celestial attitude determination system is used to enhance the inertial navigation system (INS)/global positioning system (GPS) to achieve the required attitude performance. The traditional federal filter is not applicable for INS/GPS/celestial attitude determination system information fusion because it does not consider the mutually coupled relationship between the horizontal reference error in the celestial attitude determination system and the navigation error; this limitation results in reduced navigation accuracy. This article proposes a novel stepwise fusion algorithm with dual correction for multi-sensor navigation. Considering the horizontal reference error, the celestial attitude determination system measurement model is constructed and the issues involved in applying the federal filter are discussed. Then, preliminary error estimation and horizontal reference compensation are added to the navigation architecture. In addition, a sequential update strategy is derived to estimate the attitude error with the compensated celestial attitude determination system based on the preliminary estimation. A stepwise correction filtering algorithm with interactive preliminary and sequential updates that can effectively fuse celestial attitude determination system measurements with the INS/GPS is constructed. High-altitude, long-endurance unmanned aerial vehicle navigation in a remote sensing task is simulated to verify the performance of the proposed method. The simulation results demonstrate that the horizontal reference error is effectively compensated, and the attitude accuracy is significantly improved after stepwise error estimation and correction. The proposed method also provides a novel multi-sensor integrated navigation architecture with mutually coupled errors; this architecture is beneficial in unmanned aerial vehicle navigation applications.

Design concept of a high-altitude long-endurance unmanned aerial vehicle

1999 ◽  
Vol 2 (1) ◽  
pp. 19-44 ◽  
Author(s):  
Zdobysław Goraj ◽  
Andrzej Frydrychiewicz ◽  
Jacek Winiecki
Keyword(s):  
High Altitude ◽  
Unmanned Aerial Vehicle ◽  
Design Concept ◽  
Aerial Vehicle ◽  
Long Endurance

Multi-Disciplinary Design Optimization of Unmanned Aerial Vehicle

2011 ◽  
Author(s):  
Cheolwan Kim ◽  
Yung-Gyo Lee
Keyword(s):  
Unmanned Aerial Vehicle ◽  
General Procedure ◽  
Optimization Technique ◽  
Aircraft Design ◽  
Preliminary Design ◽  
Approximation Model ◽  
Diamond Sample ◽  
Design Variables ◽  
Aerial Vehicle ◽  
Euler Solver

A general procedure of preliminary design of aircraft and one-way fluid-structure interaction (FSI) applied to aircraft design is introduced briefly. Then, FSI and optimization technique are implemented to optimize a wing shape of an unmanned aerial vehicle (UAV) for minimum cruise drag. FSI analysis and optimization processes for minimizing drag of UAV are explained. Design variables are wing taper ratio and dihedral angle, and objective function is the cruise drag of UAV. Fluid solution is generated with Euler solver and structural analysis is performed with FEM solver, Diamond. Sample points are selected by Design of Experiment (DOE) method and Kriging method is used for generation of an approximation model.

scholarly journals High altitude long endurance of unmanned aerial vehicle (UAV) ITB solar panel conceptual design

2021 ◽  
Vol 1173 (1) ◽  
pp. 012055
Author(s):  
M A Moelyadi ◽  
M A Sulthoni ◽  
M F Zulkarnain ◽  
M F Akbar ◽  
B K Assakandari
Keyword(s):  
High Altitude ◽  
Conceptual Design ◽  
Unmanned Aerial Vehicle ◽  
Solar Panel ◽  
Aerial Vehicle ◽  
Long Endurance

Emissions prediction of an aero-piston gasoline engine during surveillance flight of an unmanned aerial vehicle

2020 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Ali Dinc ◽  
Murat Otkur
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Test Data ◽  
Gasoline Engine ◽  
Exhaust Emissions ◽  
Piston Engine ◽  
Content Type ◽  
Fuel Flow ◽  
Aerial Vehicle ◽  
Ground Test ◽  
Mission Profile

Purpose The purpose of this study is to perform the preliminary design, flight performance and exhaust emissions calculations of a piston engine powered unmanned aerial vehicle (UAV) during a flight cycle which consists of multiple flight altitudes and airspeeds. Design/methodology/approach A genuine computer model in Matlab/Simulink was developed to predict the size and weight of UAV and piston engine (using Avgas 100LL fuel) performance together with exhaust emissions in an iterative process. Findings The amount of emitted exhaust gases including carbon dioxide, carbon monoxide, hydrocarbons and nitrogen oxides were calculated in a typical UAV mission profile as a whole and also divided into mission flight segments. Research limitations/implications Emissions were calculated based on fuel flow and engine speed inputs based on ground test data for emission indices. Test data for emission indices was very limited. Practical implications As UAV utilization has been increasing around the world, this study presents important and noticeable results on the emissions that need to be considered for environmental purposes. Originality/value In literature, emission prediction studies for UAVs are very rare. In fact, UAVs typically have quite different flight speeds and altitudes than regular manned aircraft and emissions change with speed and altitude. Additionally, unlike manned aircraft, UAVs can fly more than 24 h with different operation characteristics. The originality of this study presents the emission predictions of a piston engine UAV which flies with a significantly different mission profile than a manned aircraft.

Sign in / Sign up

Export Citation Format

Share Document