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Design and Analysis of Unmanned Aircraft Systems for Earth and Venus.

Record Type:	Language materials, manuscript : Monograph/item
Title/Author:	Design and Analysis of Unmanned Aircraft Systems for Earth and Venus./
Author:	Rosales Rosales, Jesus.
Description:	1 online resource (147 pages)
Notes:	Source: Dissertations Abstracts International, Volume: 85-03, Section: B.
Contained By:	Dissertations Abstracts International85-03B.
Subject:	Aerospace engineering. -
Online resource:	click for full text (PQDT)
ISBN:	9798380163576

Design and Analysis of Unmanned Aircraft Systems for Earth and Venus.
Rosales Rosales, Jesus.

Design and Analysis of Unmanned Aircraft Systems for Earth and Venus. - 1 online resource (147 pages)

Source: Dissertations Abstracts International, Volume: 85-03, Section: B.

Thesis (Ph.D.)--New Mexico State University, 2023.

Includes bibliographical references

The lower complexity, higher affordability, and ever growing versatility of Unmanned Aircraft Systems (UAS) compared to manned aircraft is driving research aimed at extending their operating environment to new frontiers. This thesis covers two topics, the development of an autonomous soaring algorithm for flight in the Earth atmosphere and the development of an aerobot for flight in the Venus atmosphere. For the first topic, similar to soaring birds, convective updrafts in the atmosphere are exploited for staying airborne without expending energy. For the second topic, as for airships in the Earth atmosphere, the vehicle is kept afloat by buoyancy forces.The autonomous soaring algorithm is evaluated for waypoint navigation missions in a simulation environment. The simulation environment is based on a three-degrees-of-freedom point-mass aircraft model and a thermal model. The aircraft characteristics for the simulation environment, such as glide polar and zero-lift drag coefficient, are estimated from flight tests with a model motor glider. The algorithm consists of an outer and an inner loop. The outer loop is responsible for the waypoint navigation and thermaling while the inner loop models the low-level three-axis and motor control provided by an autopilot during flight testing. Thermaling flights with fixed and automatically adjusted bank angle are investigated.A statistical analysis reveals a weak dependence on the bank angle and thermaling lift coefficient. As an important step towards flights tests, the autonomous soaring algorithm was implemented in Matlab/Simulink with the UAV Toolbox Support Package for PX4 Autopilots. A simulation environment was built in Simulink for validating the implementation. First steps were taken towards hardware-in-the-loop simulations.The conceptual design of a hybrid aerial vehicle (i.e., aerobot) for the exploration of the upper Venus atmosphere is a multi-disciplinary challenge that encompasses fluid dynamics and thermodynamics, structural design, and planetary science among others. The vehicle will float like a balloon and harvest solar energy which is stored in batteries. The neutral buoyancy reduces the energy consumption and makes the vehicle robust and fail-safe. Energy stored in the batteries can be used for powered flight with horizontal and vertical mobility to explore aspects of the atmosphere. The vehicle is intended to operate near 55 km altitude and to explore the cloud layer of the planet. Based on a trade study, the wing span was set to 25 m. Equations are developed for the altitude and gas temperature during neutrally buoyant flight. The equations take into account the volumetric expansion of the structure and the requirement that the differential pressure needs to be larger than the dynamic pressure in forward flight. An aerodynamic analysis provides the lift and drag coefficient curves and indicates that the vehicle is pitch-stable in forward flight. A powered flight analysis provides the maximum achievable airspeed in straight and level flight and the flight ceiling. Finally, two different propeller designs, that mimic propellers seen on terrestrial airships, were analyzed with JBlade, which is based on blade element momentum theory.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798380163576Subjects--Topical Terms:

686400
Aerospace engineering.
Subjects--Index Terms:

Autonomous soaring algorithmIndex Terms--Genre/Form:

554714
Electronic books.

Design and Analysis of Unmanned Aircraft Systems for Earth and Venus.
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520 $a The lower complexity, higher affordability, and ever growing versatility of Unmanned Aircraft Systems (UAS) compared to manned aircraft is driving research aimed at extending their operating environment to new frontiers. This thesis covers two topics, the development of an autonomous soaring algorithm for flight in the Earth atmosphere and the development of an aerobot for flight in the Venus atmosphere. For the first topic, similar to soaring birds, convective updrafts in the atmosphere are exploited for staying airborne without expending energy. For the second topic, as for airships in the Earth atmosphere, the vehicle is kept afloat by buoyancy forces.The autonomous soaring algorithm is evaluated for waypoint navigation missions in a simulation environment. The simulation environment is based on a three-degrees-of-freedom point-mass aircraft model and a thermal model. The aircraft characteristics for the simulation environment, such as glide polar and zero-lift drag coefficient, are estimated from flight tests with a model motor glider. The algorithm consists of an outer and an inner loop. The outer loop is responsible for the waypoint navigation and thermaling while the inner loop models the low-level three-axis and motor control provided by an autopilot during flight testing. Thermaling flights with fixed and automatically adjusted bank angle are investigated.A statistical analysis reveals a weak dependence on the bank angle and thermaling lift coefficient. As an important step towards flights tests, the autonomous soaring algorithm was implemented in Matlab/Simulink with the UAV Toolbox Support Package for PX4 Autopilots. A simulation environment was built in Simulink for validating the implementation. First steps were taken towards hardware-in-the-loop simulations.The conceptual design of a hybrid aerial vehicle (i.e., aerobot) for the exploration of the upper Venus atmosphere is a multi-disciplinary challenge that encompasses fluid dynamics and thermodynamics, structural design, and planetary science among others. The vehicle will float like a balloon and harvest solar energy which is stored in batteries. The neutral buoyancy reduces the energy consumption and makes the vehicle robust and fail-safe. Energy stored in the batteries can be used for powered flight with horizontal and vertical mobility to explore aspects of the atmosphere. The vehicle is intended to operate near 55 km altitude and to explore the cloud layer of the planet. Based on a trade study, the wing span was set to 25 m. Equations are developed for the altitude and gas temperature during neutrally buoyant flight. The equations take into account the volumetric expansion of the structure and the requirement that the differential pressure needs to be larger than the dynamic pressure in forward flight. An aerodynamic analysis provides the lift and drag coefficient curves and indicates that the vehicle is pitch-stable in forward flight. A powered flight analysis provides the maximum achievable airspeed in straight and level flight and the flight ceiling. Finally, two different propeller designs, that mimic propellers seen on terrestrial airships, were analyzed with JBlade, which is based on blade element momentum theory.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2024
538 $a Mode of access: World Wide Web
650 4 $a Aerospace engineering. $3 686400
650 4 $a Mechanical engineering. $3 557493
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653 $a Autonomous soaring algorithm
653 $a Hybrid airships
653 $a Unmanned Aircraft Systems
653 $a Venus exploration vehicle
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710 2 $a New Mexico State University. $b Mechanical and Aerospace Engineering. $3 1470303
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