Low- and high-altitude tests of parachutes designed for use in low-density atmospheres
Parachutes for low density atmospheres, describing low and high altitude test results
Eckstrom, C. V.↗
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An investigation of parachute opening loads, and a new engineering method for their determination
Parachute trajectory and opening load prediction based on inflation process and added mass, determining drag area as function of distance
Mcewan, A. J.↗
Effect of suspension line elasticity on parachute loads
Parachute opening load amplification due to suspension line elasticity, using two-body spring- mass model
Greene, G. C.↗
Method for estimating minimum required ejection velocity for parachute deployment
Approximate method for estimating minimum required ejection velocity for parachute deployment
Huckins, E. K., III↗
Flight tests of cross, modified ringsail, and disk-gap-band parachutes from a deployment altitude of 3.05 km /10,000 ft/
Flight tests of cross, modified ringsail, and disk-gap-band parachute deployment performance from low altitudes with structural load data
Eckstrom, C. V.↗
Effects of a simulated Martian mission on the mechanical properties of Dacron parachute material
Mechanical properties of Dacron parachute fabrics in simulated Martian atmosphere
Spence, D. C.↗
Drag coefficients for partially inflated flat circular parachutes
Free-body tests of flat circular parachutes and determination of aerodynamic drag coefficients during partial inflation
Scher, S. H.↗
High-Altitude Flight Test of a Reefed 12.2-Meter-Diameter Disk-Gap-Band Parachute with Deployment at a Mach Number of 2.58
High altitude flight test of reefed 12.2-meter-diameter disk-gap-band parachute with deployment at 2.58 Mach number
Preisser, J. S.↗
Performance of disk-gap-band, ringsail, and cross parachutes at low earth altitudes
Parachutes for low density atmospheres, describing low and high altitude test results
Eckstrom, C. V.↗
Evaluation of massless-spring modeling of suspension-line elasticity during the parachute unfurling process
A general theory on mathematical modeling of elastic parachute suspension lines during the unfurling process was developed. Massless-spring modeling of suspension-line elasticity was evaluated in detail. For this simple model, equations which govern the motion were developed and numerically integrated. The results were compared with flight test data. In most regions, agreement was satisfactory. However, poor agreement was obtained during periods of rapid fluctuations in line tension.
Poole, L. R.↗
Apollo 15 mission main parachute failure
The failure of one of the three main parachutes of the Apollo 15 spacecraft was investigated by studying malfunctions in the forward heat shield, broken riser, and firing the fuel expelled from the command module reaction control system. It is concluded that the most probable cause was the burning of raw fuel being expelled during the latter portion of depletion firing. Recommended corrective actions are included.
Source record↗
Computer program for investigating effects of nonlinear suspension-system elastic properties on parachute inflation loads and motions
A computer program is presented by which the effects of nonlinear suspension-system elastic characteristics on parachute inflation loads and motions can be investigated. A mathematical elastic model of suspension-system geometry is coupled to the planar equations of motion of a general vehicle and canopy. Canopy geometry and aerodynamic drag characteristics and suspension-system elastic properties are tabular inputs. The equations of motion are numerically integrated by use of an equivalent fifth-order Runge-Kutta technique.
Poole, L. R.↗
Suspension-line wave motion during the lines-first parachute unfurling process
A new mathematical approach to modeling the lines-first parachute unfurling process is presented. The unfurling process is treated as two distinct phases: a suspension-line unfurling phase, during which a massless-spring model of the suspension-line elasticity may be employed; and a canopy unfurling phase, during which a formulation considering suspension-line wave mechanics is employed. Histories of unfurled length and tension at the vehicle obtained using the model are compared with flight test data, and generally good agreement is observed.
Poole, L. R.↗
Drag and stability characteristics of a variety of reefed and unreefed parachute configurations at Mach 1.80 with an empirical correlation for supersonic Mach numbers
An investigation was conducted at Mach 1.80 in the Langley 4-foot supersonic pressure tunnel to determine the effects of variation in reefing ratio and geometric porosity on the drag and stability characteristics of four basic canopy types deployed in the wake of a cone-cylinder forebody. The basic designs included cross, hemisflo, disk-gap-band, and extended-skirt canopies; however, modular cross and standard flat canopies and a ballute were also investigated. An empirical correlation was determined which provides a fair estimation of the drag coefficients in transonic and supersonic flow for parachutes of specified geometric porosity and reefing ratio.
Couch, L. M.↗
Drag coefficient of 20-degree conical ribbon parachute
An empirical formula for the steady-state drag coefficient of a 20-degree conical ribbon parachute is developed. The derived expression takes into account the effect of suspension line length and geometric porosity within the limits of practical design. Also included are factors which provide drag reduction due to skirt reefing and the wake behind a primary body. The calculated values are in agreement with the available experimental results.
Utreja, L. R.↗
Monorail for production handling of large parachutes
Heavy parachutes are transported through work and inspection stations via monorail system.
Crowell, R. T.↗
Prediction of the drag coefficient of a 20-degree conical ribbon parachute
An empirical formula for the steady state drag coefficient of a 20 degree conical ribbon parachute is developed. The derived expression takes into account the effect of suspension line length and geometric porosity within the limits of practical design. Also included are factors which provide drag reduction due to skirt reefing and the wake behind a primary body. The calculated values are in agreement with the available experimental results.
Utreja, L. R.↗
Scale parachute fabrication
Report describes highlights in developing six 12.5-percent scale drogue parachute models. Deployment bags are fabricated for each model.
Bacchus, D.↗