[PDF] Development Of The B 1 Crew Module Parachute Recovery System eBook

Author : Ian A. Whalley
Publisher :
Page : 10 pages
File Size : 32,49 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 : E. G. Ewing
Publisher :
Page : 502 pages
File Size : 14,92 MB
Release : 1979
Category : Parachutes
ISBN :

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This document serves as the third revision of the USAF Parachute Handbook which was first published in 1951. The data and information represent the current state of the art relative to recovery system design and development. The initial chapters describe representative recovery applications, components, subsystems, material, manufacture and testing. The final chapters provide empirical data and analytical methods useful for predicting performance and presenting a definitive design of selected components into a reliable recovery system.

Author : Daniel J. Kolega
Publisher :
Page : 55 pages
File Size : 16,92 MB
Release : 1975
Category :
ISBN :

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Evaluation of a contractor designed parachute recovery system for the B-1 Crash Data Recorder/Crash Position Indicator (CDR/CPI) resulted in a 45-inch diameter solid flat canopy design effort by the ASD Parachute Branch at Wright-Patterson AFB, Ohio. The recovery system performance was evaluated through a series of static deployment tests, low speed helicopter airdrop tests at Wright-Patterson AFB, and high speed deployment tests conducted at the Whirl Tower Facility located at the National Parachute Test Range, El Centro, California.

Author : Theo W. Knacke
Publisher :
Page : 524 pages
File Size : 14,41 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 :
Publisher :
Page : 6 pages
File Size : 15,9 MB
Release : 1991
Category :
ISBN :

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A successfully deployment of a parachute system highly depends on the efficiency of the deployment device and/or method. There are several existing methods and devices that may be considered for a deployment system. For the F111 Crew Escape Module (CEM), the recovery parachute system deployment is initiated by the firing of a catapult that ejects the complete system from the CEM. At first motion of the pack, a drogue gun is fired, which deploys the pilot parachute system. The pilot parachute system then deploys the main parachute system, which consists of a cluster of three 49-ft diameter parachutes. The pilot parachute system which extracts the F111 Crew Escape Module recovery parachute system must provide reasonable bag strip velocities throughout the flight envelope (10 psf to 300 psf). The pilot parachute system must, therefore, have sufficient drag area at the lower dynamic pressures and a reduced drag area at the high end of the flight envelope. The final design that was developed was a dual parachute system which consists of a 5-ft diameter guide surface parachute tethered inside a 10-ft diameter flat circular parachute. The high drag area is sustained at the low dynamic pressures by keeping both parachutes intact. The drag area is reduced at the higher extreme by allowing the 10-ft parachute attachment to fail. The discussions to follow describe in detail how the system was developed. 4 refs., 10 figs., 2 tabs.