The Use of LS-DYNA to Simulate the Inflation of a Parachute Canopy

Tutt, Benjamin; Taylor, Anthony P.

doi:10.2514/6.2005-1608

Cited by 43 publications

(24 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The high level of design details shows also how several design factors can compete to either provoke, or cancel out desired changes in inflation performance. Finally, the existence of such detailed dynamical modeling for slider-reefed parafoils and for other types of parachutes (such as ribbon-type parachute [11 -13]), should be viewed as necessary precursors to those upcoming, full-fledged CFD-FSI descriptions of inflating parachutes [19,20], if only to understand the physics that may be lost or modified by the inevitable numerical instabilities arising in such non-linear, high-degree-of-freedom simulation systems. In this respect, studying the history of numerical weather prediction may provide invaluable guidance on how the understanding of complex phenomena via low order dynamical modeling can help in guiding the development and validation of the type of the high-order numerical modeling that is embodied in CFD-FSI [21].…”

Section: A Source Of Physical Insightmentioning

confidence: 99%

“…Thus, the more tension in the lines at fixed canopy expansion force, the slower the canopy expansion rate, and thereby the smaller the value of the spreading constant K ipm . Final adjustments to (20) are made to express d 2 Σ/dt 2 more explicitly in terms of slider drag area Σ slider , as well as to add the extra drag contributed to wing drag by a pilot chute directly linked to the slider. Finally, the ½ -factors appearing in (20) are cancelled out, a move demanded by the comparison with experimental data discussed in the next section.…”

mentioning

confidence: 99%

“…Final adjustments to (20) are made to express d 2 Σ/dt 2 more explicitly in terms of slider drag area Σ slider , as well as to add the extra drag contributed to wing drag by a pilot chute directly linked to the slider. Finally, the ½ -factors appearing in (20) are cancelled out, a move demanded by the comparison with experimental data discussed in the next section. Combining (17) and (20), and defining the contents of the square bracket as being equal to the function Δ(t), one obtains: (21) with ψ ~ 1/5.…”

mentioning

confidence: 99%

See 2 more Smart Citations

Three-Stage Model for Slider-Reefed Parafoil Inflation

Potvin

Peek²

2007

19th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar

View full text Add to dashboard Cite

This paper discusses the definition and validation of an upgraded model of slider-reefed parafoil inflation. Unlike an early version which focused only on the slider-descent phase, this improved model incorporates the dynamics of the all-important slider-up phase which precedes slider-descent. The model is "dynamical" in that it involves a physical description of the cell inflation process and corresponding parachute drag area expansion. The upgrade is also detailed enough to require over 15 input parameters describing the deployment conditions, canopy dimensions, and most importantly, slider dimensions and drag characteristics. The simulation outputs not only include the evolutions of the drag force and parachute-payload descent rate, but also the actual duration of the slider-up stage. The model can be applied to both sail-slider and pilot chutecontrolled slider configurations, but not to sliders that are physically and temporarily attached to the wing during the early phases of inflation. It will be shown that simulations are the most accurate for canopy-slider designs that have been "tuned" to reduce surging. Nomenclature a(t) = Instant value of the parachute-payload acceleration/deceleration a max = Maximum deceleration sustained during the slider descent phase A c-inlet = Mean center cell opened surface area during the center cell pressurization stage A outboardcell = Mean opened outboard cell surface area during the outboard cell pressurization stage C D (t) = Instant drag coefficient of the parafoil F inlet = Fraction of mean opened center cell inlet, in terms of total center cell inlet area F end = Fraction of final canopy drag area (after slider-descent) to steady state drag area F linedrive = Net slider down-pushing force (minus grommet friction) F max = Maximum drag force sustained during inflation F sliderdrag = Drag force generated by the slider g = Acceleration of gravity constant (t) S(t))Σ slider-extra = Extra slider drag area (generated by PCS pilot chute, slider dome geometry, etc.) Σ slider = Slider drag area (from fabric within grommeted frame) θ(t) = Angle between the side wall of the tip cells and the horizontal <(1-sinΩ-μcosΩ)> = "Slider-push" factor during the slider-descent phase <Δ(t)> = Average value of the dynamical factor of the canopy spreading rate constant <Σ sld > = Average canopy drag area during the slider-descent phase

show abstract

Section: A Source Of Physical Insightmentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

See 1 more Smart Citation

Three-Stage Model for Slider-Reefed Parafoil Inflation

Potvin

Peek²

2007

19th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar

View full text Add to dashboard Cite

show abstract

“…This technique recently advanced rapidly with the introduction of an ALE solver into the explicit finite element code LS-DYNA, allowing fully coupled fluid structure interaction simulation for compressible flows. Taylor 133 reports the use of the code to study the post inflation collapse phenomenon and Tutt 134 discusses modeling of parachute inflation. Simulation of the Huygens parachute system in the supersonic regime was presented by Lingard.…”

Section: -119mentioning

confidence: 99%

Aerodynamic Decelerators for Planetary Exploration: Past, Present, and Future

Cruz

Lingard²

2006

AIAA Guidance, Navigation, and Control Conference and Exhibit

View full text Add to dashboard Cite

In this paper, aerodynamic decelerators are defined as textile devices intended to be deployed at Mach numbers below five. Such aerodynamic decelerators include parachutes and inflatable aerodynamic decelerators (often known as ballutes). Aerodynamic decelerators play a key role in the Entry, Descent, and Landing (EDL) of planetary exploration vehicles. Among the functions performed by aerodynamic decelerators for such vehicles are deceleration (often from supersonic to subsonic speeds), minimization of descent rate, providing specific descent rates (so that scientific measurements can be obtained), providing stability (drogue function -either to prevent aeroshell tumbling or to meet instrumentation requirements), effecting further aerodynamic decelerator system deployment (pilot function), providing differences in ballistic coefficients of components to enable separation events, and providing height and timeline to allow for completion of the EDL sequence. Challenging aspects in the development of aerodynamic decelerators for planetary exploration missions include: deployment in the unusual combination of high Mach numbers and low dynamic pressures, deployment in the wake behind a blunt-body entry vehicle, stringent mass and volume constraints, and the requirement for high drag and stability. Furthermore, these aerodynamic decelerators must be qualified for flight without access to the exotic operating environment where they are expected to operate. This paper is an introduction to the development and application of aerodynamic decelerators for robotic planetary exploration missions (including Earth sample return missions) from the earliest work in the 1960s to new ideas and technologies with possible application to future missions. An extensive list of references is provided for additional study.

show abstract

“…Kim and Peskin applied the immersed boundary method to calculate the inflating process under small Reynolds number [9]. Tutt et al applied the arbitrary Lagrangian-Eulerian method to solve the practical engineering problems [10,11]. Karagiozis et al used the large eddy simulation method to investigate the supersonic parachute [12].…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Extra-Large Parachute’s Pre-Inflation in Finite Mass Situation

Sun

Cheng

Yang

2018

Autex Research Journal

View full text Add to dashboard Cite

The extra-large parachutes were different from the common parachutes because of their size and opening process. Some undesirable inflation phenomena such as canopy winding and whipping usually appeared in their pre-inflation process. However, the mechanical mechanism of these phenomena was very difficult to be explained by experimental means. In this paper, the pre-inflation process in finite mass situation of an extra-large parachute was calculated by explicit finite elements. According to the results, the pre-inflation process can be subdivided into symmetric inflation stage, undesirable inflation stage, and stable inflation stage. The canopy winding and whipping mainly occurred in the second stage. With the continuous deceleration of parachute-payload system, the top of canopy without effective constraints would appear winding and whipping under the function of inertia force. The canopy winding and whipping increased the difficulty of canopy expanding and then caused asymmetric inflation. The above undesirable phenomena had a great influence on the deceleration effect and were easy to cause the recovery failure. The actual airdrop experiments also proved that the lack of effective constraints on the canopy top will cause undesirable inflation phenomena. The conclusions in this paper can also provide a reference for extra-large parachute design and research.

show abstract

The Use of LS-DYNA to Simulate the Inflation of a Parachute Canopy

Cited by 43 publications

References 0 publications

Three-Stage Model for Slider-Reefed Parafoil Inflation

Three-Stage Model for Slider-Reefed Parafoil Inflation

Aerodynamic Decelerators for Planetary Exploration: Past, Present, and Future

Numerical Study of Extra-Large Parachute’s Pre-Inflation in Finite Mass Situation

Contact Info

Product

Resources

About