[PDF] Parachute Recovery Systems eBook

Author : Theo W. Knacke
Publisher :
Page : 524 pages
File Size : 41,60 MB
Release : 1992
Category : Sports & Recreation
ISBN :

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The purpose of this manual is to provide recovery system engineers in government and industry with tools to evaluate, analyze, select, and design parachute recovery systems. These systems range from simple, one-parachute assemblies to multiple-parachute systems, and may include equipment for impact attenuation, flotation, location, retrieval, and disposition. All system aspects are discussed, including the need for parachute recovery, the selection of the most suitable recovery system concept, concept analysis, parachute performance, force and stress analysis, material selection, parachute assembly and component design, and manufacturing. Experienced recovery system engineers will find this publication useful as a technical reference book; recent college graduates will find it useful as a textbook for learning about parachutes and parachute recovery systems; and technicians with extensive practical experience will find it useful as an engineering textbook that includes a chapter on parachute- related aerodynamics. In this manual, emphasis is placed on aiding government employees in evaluating and supervising the design and application of parachute systems. The parachute recovery system uses aerodynamic drag to decelerate people and equipment moving in air from a higher velocity to a lower velocity and to a safe landing. This lower velocity is known as rate of descent, landing velocity, or impact velocity, and is determined by the following requirements: (1) landing personnel uninjured and ready for action, (2) landing equipment and air vehicles undamaged and ready for use or refurbishment, and (3) impacting ordnance at a preselected angle and velocity.

Author : Theo W. Knacke
Publisher :
Page : 182 pages
File Size : 50,87 MB
Release : 1987
Category :
ISBN :

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This manual provides the recovery system engineer in Government and industry with tools to evaluate, select, design, test, manufacture, and operate parachute recovery systems. These systems range from simple, one-parachute assemblies to multiple-parachute systems, and may include equipment for impact attenuation, flotation, location, retrieval, and disposition. All system aspects are discussed, including the need for parachute recovery, the selection of the most suitable recovery system concept, a computerized approach to parachute performance, force and stress analysis, geometric gore design, component layout, material selection, system design, manufacturing, and in-service maintenance.

Author : T. W. Knacke
Publisher :
Page : 56 pages
File Size : 35,66 MB
Release : 1985
Category :
ISBN :

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This manual provides the recovery system engineer in Government and industry with tools to evaluate, select, design, test, manufacture, and operate parachute recovery systems. These systems range from simple, one-parachute assemblies to multiple-parachute systems, and may include equipment for impact attenuation, flotation, location, retrieval, and disposition. All system aspects are discussed, including the need for parachute recovery, the selection of the most suitable recovery system concept, a computerized approach to parachute performance, force and stress analysis, geometric gore design, component layout, material selection, system design, manufacturing, and in-service maintenance.

Author : M. Neustadt
Publisher :
Page : 50 pages
File Size : 23,34 MB
Release : 1966
Category : Parachutes
ISBN :

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Multi-stage parachute recovery systems are used for (1) aerial delivery systems, (2) escape of personnel from disabled aircraft and (3) recovery of spacecraft. Factors related to the dynamics of the payload-parachute system are very importamt in the optimum design of parachute recovery systems. A three-degree-of-freedom mathematical analysis is presented here giving the motion of a typical vehicle during recovery. This analytical method is a useful tool because it yields parachute loads for a variety of vehicle dynamic conditions and parachute configurations, and enables the designer to predict undesirable recovery attitudes.

Author : R. C. Sluis
Publisher :
Page : 5 pages
File Size : 22,21 MB
Release : 1957
Category :
ISBN :

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The X7A-3 vehicle has a parachute recovery system. This parachute system consists of two parachutes, a supersonic drag parachute, and a supersonic main canopy. Upon initiation of the recovery sequence, this parachute system allows the vehicle to descend at a safe velocity and the vehicle lands on the nose recovery spike, remains in a vertical position, and is capable of being reflown.

Author : Ian A. Whalley
Publisher :
Page : 10 pages
File Size : 19,51 MB
Release : 1973
Category : Pilot ejection seats
ISBN :

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The USAF B-1 Strategic Bomber employs the Ejectable Crew Module Escape concept. The crew module, which forms an integral portion of the forward fuselage during normal flight and encompasses the presurized crew cabin, is designed to afford maximum protection for the six crew members. The Parachute Recovery System (PRS) must be capable of performing at speeds from zero to mach 2.3 and at altitudes from zero to 70,000 ft, including adverse cases. The PRS selected for the B-1 crew module PRS consists of a mortar-deployed 14.2-ft nominal diameter variable porosity conical ribbon parachute, to accomplish initial deceleration and stabilization, and a cluster of three 69.8-ft nominal diameter slotted Ringsail main parachutes, to provide the required terminal descent rate. Main parachute deployment is by means of two mortar-deployed 8.4-ft nominal diameter ring slot pilot parachutes. Technical areas presented include component design, development and qualification testing, overall system performance, reliability, and other interesting aspects.

Author : T. W. KNACKE
Publisher :
Page : 1 pages
File Size : 26,80 MB
Release : 1962
Category :
ISBN :

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A performance an lysis was conducted on two parachute recovery systems developed for the B-70 encapsulated seat and the USD-5 surveillance drone. Optimization of aerodyna ic and textile esign controlled deployment and opening, and us of a cluster of two indep ndently d ployed parachutes for the USD-5 dro e r sulted in a highly predictable perform nce, in the highest known drag area per weight ratio for the USD-5 syst, and a hig velocity c pability for the B-70 system. Equations were developed through data analysis for the opening process and the drag area increase versus ti e during par c ute openi g for extended skirt parachutes. These equations permit e a computer analysis of the total parachute deceleration process with computer results showing less than 10% deviation from actual test data. The developed computer method may well be suitable for performance analysis of recovery processes using ribbon, ring slot, and other solid material type parachutes. (Author).