Parafoil steady turn response to control input

Brown, Glen

doi:10.2514/6.1993-1241

Cited by 28 publications

(19 citation statements)

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“…4 and 7 and computational fluid dynamics data obtained for the steady state turn in Ref. 28. However it was impossible to implement this data directly.…”

Section: Aerodynamics Modelmentioning

confidence: 99%

“…Moreover, the estimation of the apparent mass terms even for the case of the fixed-geometry parafoil is nonintuitive. 21,28,29 The apparent mass has the following important property: it changes with orientation of the associated motion. Therefore, appropriate choice of truth data can obviously identify the apparent mass terms that dominate specific motion.…”

Section: Parameter Identification Techniquementioning

confidence: 99%

See 1 more Smart Citation

On the Development of a Six-Degree-of-Freedom Model of a Low-Aspect-Ratio Parafoil Delivery System

Mortaloni

Yakimenko

Dobrokhodov

et al. 2003

17th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar

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Numerous papers in the area of parafoil system design have been published over the past 50 years. They cover the following major topics: The future of the Army's air delivery mission includes the use of precision-guided autonomous airdrop methods to resupply troops in the field. High-glide systems, ram-air parafoil-based, allow for a safe standoff delivery as well as wind penetration. This paper addresses the development of a six-degree-offreedom model of a low-aspect ratio controllable parafoil-based delivery system. The model is equally suitable for modeling and simulation and for the design of guidance, navigation and control (GNC) algorithms. This gliding parafoil model was developed in the MATLAB/Simulink ® environment. Apparent mass and inertia effects are included in the model. Initial test cases have been run to check model fidelity.Advanced computational methods for the 3D flow simulation around the parafoil canopy; [1][2][3] Wind-tunnel experiments; [4][5][6][7] Real drop experiments. [8][9][10][11][12][13][14][15][16][17][18]

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“…4 and 7 and computational fluid dynamics data obtained for the steady state turn in Ref. 28. However it was impossible to implement this data directly.…”

Section: Aerodynamics Modelmentioning

confidence: 99%

Section: Parameter Identification Techniquementioning

confidence: 99%

On the Development of a Six-Degree-of-Freedom Model of a Low-Aspect-Ratio Parafoil Delivery System

Mortaloni

Yakimenko

Dobrokhodov

et al. 2003

17th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar

View full text Add to dashboard Cite

show abstract

“…The usual means to create some semblance of altitude control is through a weaving maneuver back and forth across a desired trajectory path to "dump" altitude as progress is made along the desired path. [3][4][5][6][7][8][9][10] Near the intended ground impact location, current autonomous systems either spiral over the target or S-turn to the target. A key to the success for these algorithms is accurate descent rate estimation which is difficult to accomplish and prone to error.…”

Section: Introductionmentioning

confidence: 99%

Use of Dynamic Incidence Angle for Glide Slope Control of Autonomous Parafoils

Slegers

Beyer

Costello

2007

19th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar

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Strickly speaking, most autonomous parafoil and payload aircraft possess only lateral control, achieved by right and left parafoil brake deflection. An innovative new technique to achieve direct longitudinal control through dynamic incidence angle changes is reported. Addition of this extra control channel requires simple rigging changes and an additional servo actuator. The ability of dynamic incidence angle to alter the glide slope of a parafoil and payload aircraft is demonstrated through a flight test program with a micro parafoil system. Results from the flight test program are synthesized and integrated into a 6 degreeof-freedom simulation. The simulation model is subsequently used to assess the utility of glide slope control to improve autonomous flight control system performance. Through Monte Carlo simulation, impact point statistics with and without glide slope control indicate that dramatic improvements in impact point statistics are possible using direct glide slope control. , , u v w = Velocity components of mass center in a body reference frame., , p q r = Angular velocity components in a body reference frame. Γ= Canopy incidence angle.

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“…Hence, autonomous controllers for these air vehicles are greatly challenged to track threedimensional trajectories and impact a specific ground target point. The usual means to create some semblance of altitude control is through a weaving maneuver back and forth across a desired trajectory path to "dump" altitude as progress is made along the desired path [3][4][5][6][7][8][9][10]. Near the intended ground impact location, current autonomous systems either spiral over the target or S-turn to the target.…”

mentioning

confidence: 99%