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Title: Collision avoidance systems for UAS operating in civil airspace
Author: Alturbeh, Hamid
ISNI:       0000 0004 5346 1679
Awarding Body: Cranfield University
Current Institution: Cranfield University
Date of Award: 2014
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Operation of Unmanned Aerial Vehicles (UAVs) in civil airspace is restricted by the aviation authorities which require full compliance with regulations that apply for manned aircraft. This thesis proposes control algorithms for a collision avoidance system that can be used as an advisory system or a guidance system for UAVs that are flying in civil airspace under visual flight rules. An effective collision avoidance system for the UAV should be able to perform the different functionalities of the pilot in manned aircraft. Thus, it should be able to determine, generate, and perform safe avoidance manoeuvres. However, the capability to generate resolution advisories is crucial for the advisory systems. A decision making system for collision avoidance is developed based on the rules of the air. The proposed architecture of the decision making system is engineered to be implementable in both manned aircraft and UAVs to perform different tasks ranging from collision detection to a safe avoidance manoeuvre initiation. Avoidance manoeuvres that are compliant with the rules of the air are proposed based on pilot suggestions for a subset of possible collision scenarios. The avoidance manoeuvre generation algorithm is augmented with pilot experience by using fuzzy logic technique to model pilot actions in generating the avoidance manoeuvres. Hence, the generated avoidance manoeuvres mimic the avoidance manoeuvres of manned aircraft. The proposed avoidance manoeuvres are parameterized using a geometric approach. An optimal collision avoidance algorithm is developed for real-time local trajectory planning. Essentially, a finite-horizon optimal control problem is periodically solved in real-time hence updating the aircraft trajectory to avoid obstacles and track a predefined trajectory. The optimal control problem is formulated in output space, and parameterised by using B-splines. Then the optimal designed outputs are mapped into control inputs of the system by using the inverse dynamics of a fixed wing aircraft.
Supervisor: Whidborne, James F. Sponsor: Not available
Qualification Name: Thesis (Ph.D.) Qualification Level: Doctoral
EThOS ID:  DOI: Not available