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An analytical study was conducted to develop a procedure for determining the deceleration characteristics of vehicles landing on gas-filled bags of various arbitrary shapes. The analysis developed is applicable for landing on planetary or lunar surfaces for sinking speeds that are small compared to the sonic velocity of the gas contained within the bag. For relatively high velocities a light gas such as hydrogen or helium should probably be used. A series of calculations was made for four bag shapes for impact on the earth at seal-level conditions for sinking speeds consistent with descent by parachute to determine how deceleration characteristics were influenced by various factors entering the equations.
A complete reference text to airdrop recovery systems with self-inflating airbags, focusing on analysis, test data, and engineering practicalities Comprehensively covers the fundamental theories, design, matching, and analysis of airdrop recovery systems that include a parachute and self-inflating airbag system Gives step-by-step guidance to aid readers in analyzing and designing their own recovery systems Highlights advanced research programs in the field of airdrop recovery systems, such as simulation and optimization methods.
This excellent book highlights all aspects of the analysis and design of buildings subject to impact, explosion and fire. It is a definitive reference book and contains 10 chapters from a wide international prospective. Three-dimensional finite element and discrete element techniques are included. They are applied to buildings such as the World Trade Center (WTC Twin Towers) and the Federal Building in Oklahoma on the basis of the designers drawings, data and other information. Many small case studies are also included. The book has a comprehensive bibliography and a large appendix providing background analysis and computer subroutines of recently developed programs.
An experimental investigation has been made to determine the landing characteristics of a conical-shaped reentry capsule by using torus-shaped air bags for impact alleviation. An impact bag was attached below the large end of the capsule to absorb initial impact loads and a second bag was attached around the canister to absorb loads resulting from impact on the canister when the capsule overturned. A 1/6-scale dynamic model of the configuration was tested for nominal flight paths of 600 and 900 (vertical), a range of contact attitudes from -250 to 300, and a vertical contact velocity of 12.25 feet per second. Accelerations were measured along the X-axis (roll) and Z-axis (yaw) by accelerometers rigidly installed at the center of gravity of the model. Actual flight paths, contact attitudes, and motions were determined from high-speed motion pictures. Landings were made on concrete and on water.