Approaches to Automatic Stall/Spin Detection Based on Small-Scale UAV Flight Testing

This paper presents methodologies and techniques for stall/spin flight testing using commercially off-the-shelf model aircraft and flight data systems. Flight test procedures allowing systematic and efficient testing are outlined, as well as piloting techniques to obtain quality spin flight data. Two spin flight test campaigns with different testbeds are described, including the aircraft, flight data system and ground station setups. Flight test data for the two testbeds are presented and the incipient, developed and recovery characteristics are analyzed. The spin data is consistent across spin maneuvers for a given aircraft, and also similar between aircrafts of different scale, showing the accuracy of the flight test methodology and instrumentation. Nomenclature bwing span CG center of gravity V airspeed at the center of gravity V stallStall speed Re stall Reynolds number at stall p, q, r roll, pitch and yaw rates Ω spin rate, Ω (p 2 + q 2 + r 2 ) 1/2

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“…9, two campaigns were undertaken: one with a 1/10 scale Taylorcraft and another with a 1/5 scale Super Cub.…”

Section: Spin Flight Test Campaignsmentioning

confidence: 99%

Stall/Spin Flight Test Techniques with COTS Model Aircraft and Flight Data Systems

Bunge

Savino

Kroo

2015

AIAA Flight Testing Conference

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“…For example, significant effort has been put into studying aerodynamic qualities [2,3], especially in high angle-of-attack conditions [4][5][6], as well as in the development of new control algorithms [7][8][9][10]. There have also been studies of UAV performance through stall or upset maneuvers [11][12][13][14]. In addition, new aircraft configurations [15][16][17][18] and flight control hardware and software [19][20][21][22][23] have been tested.…”

Section: Introductionmentioning

confidence: 99%

A Cyber-Physical Prototyping and Testing Framework to Enable the Rapid Development of UAVs

2022

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In this work, a cyber-physical prototyping and testing framework to enable the rapid development of UAVs is conceived and demonstrated. The UAV Development Framework is an extension of the typical iterative engineering design and development process, specifically applied to the rapid development of UAVs. Unlike other development frameworks in the literature, the presented framework allows for iteration throughout the entire development process from design to construction, using a mixture of simulated and real-life testing as well as cross-aircraft development. The framework presented includes low- and high-order methods and tools that can be applied to a broad range of fixed-wing UAVs and can either be combined and executed simultaneously or be executed sequentially. As part of this work, seven novel and enhanced methods and tools were developed that apply to fixed-wing UAVs in the areas of: flight testing, measurement, modeling and emulation, and optimization. A demonstration of the framework to quickly develop an unmanned aircraft for agricultural field surveillance is presented.

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“…As such, it does not explicitly consider some aspects of stall that are important for many smaller general aviation, unmanned aerial system, and military aircraft, such as stall induced spin. 13 Extensive prior research has been conducted under the topic of upset prevention and recovery to address loss-of-control, 14 which is a multifaceted topic, where the type of stall considered here is often viewed as a simple case. For example, Gandhi et.…”

Section: Introductionmentioning

confidence: 99%

Stall Recovery Guidance Using Fast Model Predictive Control

Schuet

Lombaerts

Kaneshige

et al. 2017

AIAA Guidance, Navigation, and Control Conference

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Based on a detailed analysis of recent loss-of-control events, the Aircraft State Awareness Joint Safety Analysis Team has identified the need to develop algorithms and display strategies to provide control guidance for recovery from approach-to-stall or stall. In order to be effective, such guidance should enhance the pilot's ability to execute the Federal Aviation Administration's recommended stall recovery procedure. This paper explores the use of a fast model predictive control algorithm that determines near optimal recovery guidance, which quantifies the aircraft configuration and situation dependent recovery information required to maximize the effectiveness of the recovery. This information includes the magnitude of the initial pitch down maneuver, the specific amount of airspeed and thrust needed before pulling out of the recovery dive, as well as the maximum pitch-up rate that can be sustained without causing a secondary stall. The algorithm was integrated and tested with an in-house desktop simulator that implements the General Transport Aircraft model and the associated stall aircraft dynamics. Preliminary results are presented to demonstrate the use of the proposed approach as a recovery aid for pilots.

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Approaches to Automatic Stall/Spin Detection Based on Small-Scale UAV Flight Testing

Cited by 17 publications

References 13 publications

Stall/Spin Flight Test Techniques with COTS Model Aircraft and Flight Data Systems

Stall/Spin Flight Test Techniques with COTS Model Aircraft and Flight Data Systems

A Cyber-Physical Prototyping and Testing Framework to Enable the Rapid Development of UAVs

Stall Recovery Guidance Using Fast Model Predictive Control

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