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Successbook
9 success stories, 73 viewpoints, 10 key learnings and 1 mission: successful innovation. The successbook takes a look at the innovation processes at a major Swiss corporation. Success factors and innovation myths are examined with the input of experts.
Failbook
74 failures, 10 key learnings and 1 mission: promoting a positive culture of mistakes in business. The innovation team at a major Swiss corporation reveal the things that others might want to keep secret – with charm, courage and humour, plus an ironic series of images from daily working life. Instead of glossing over mistakes, the book demonstrates how to draw valuable insights from failed projects and then use them to make progress in an innovation environment.
Wake Properties Behind an Ejection Seat Escape System and Aerodynamic Characteristics with Stabilization Parachutes at Mach Numbers from 0.6 to 1.5
A test was conducted in the Propulsion Wind Tunnel (16T) of the Propulsion Wind Tunnel Facility to determine the flow field in the wake of an ejection seat escape system at transonic flight conditions, and to determine the performance characteristics of a stabilization parachute attached to the back of the ejection seat model. The results were obtained for both simulated rocket-off and rocket-on conditions through a model angle-of-attack range from 0 to 30 deg. High pressure air was used to simulate the escape rocket jet plume at a sea-level altitude. The results show that the ejection seat model was statically unstable, but became longitudinally stable with the parachute for the test range investigated. (Author).
Aerodynamic Characteristics of an Ejection Seat Escape System with a Stabilization Parachute at Mach Numbers from 0.3 Through 1.2
A test was conducted in the 16-ft Transonic Wind Tunnel of the Propulsion Wind Tunnel Facility to determine the aerodynamic characteristics of a 0.5-scale ejection seat escape system and to determine the stability effects of a stabilization parachute attached to the back of the ejection seat model. The results were obtained for both simulated rocket-off and rocket-on conditions through a model angle-of-attack range from 0 to 30 deg and an angle-of-yaw range from 0 to 15 deg. High-pressure air was used to simulate the escape rocket jet plume at a sea-level altitude. Over the test range of this investigation, the results show that the ejection seat model was statically unstable but became longitudinally and directionally stable with the parachute using the three- and four-point bridle assemblies. Jet simulation and model yaw angle had little effect on the ejection seat longitudinal stability; however, jet simulation increased the parachute drag coefficient. (Author).
Design News
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Welt-Adressenbuch
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Advanced Ejection Seat for High Dynamic Pressure Escape Wind Tunnel Test Report
Wind tunnel tests were conducted to evaluate new high dynamic pressure protective devices incorporated into a conventional ejection seat. These tests are part of a development program 'Advanced Ejection Seat for High Dynamic Pressure Escape'. The objectives of this program are to develop an ejection seat design which will provide safe escape during emergency conditions encountered throughout the performance envelope of an aircraft with speed capability to 687 KEAS. Preliminary phases of this program have resulted in selection and definition of a windblast-shield, an aft body drag reduction boom, a horizontal stabilizer and a flow diverter. These devices were incorporated into a one-half scale ejection seat/crewmember model and were tested in the AEDC PWT 16-T transonic tunnel. Aerodynamic data derived from these tests are being used in six-degree-of-freedom computer simulations for performance assessments of the ejection seat configurations. (Author)
Wake Properties Behind an Ejection Seat Escape System and Aerodynamic Characteristics with Stabilization Parachutes at Mach Numbers from 0.6 to 1.5
A test was conducted in the Propulsion Wind Tunnel (16T) of the Propulsion Wind Tunnel Facility to determine the flow field in the wake of an ejection seat escape system at transonic flight conditions, and to determine the performance characteristics of a stabilization parachute attached to the back of the ejection seat model. The results were obtained for both simulated rocket-off and rocket-on conditions through a model angle-of-attack range from 0 to 30 deg. High pressure air was used to simulate the escape rocket jet plume at a sea-level altitude. The results show that the ejection seat model was statically unstable, but became longitudinally stable with the parachute for the test range investigated. (Author).
Aerodynamic Characteristics of an Ejection Seat Escape System with a Stabilization Parachute at Mach Numbers from 0.3 Through 1.2
A test was conducted in the 16-ft Transonic Wind Tunnel of the Propulsion Wind Tunnel Facility to determine the aerodynamic characteristics of a 0.5-scale ejection seat escape system and to determine the stability effects of a stabilization parachute attached to the back of the ejection seat model. The results were obtained for both simulated rocket-off and rocket-on conditions through a model angle-of-attack range from 0 to 30 deg and an angle-of-yaw range from 0 to 15 deg. High-pressure air was used to simulate the escape rocket jet plume at a sea-level altitude. Over the test range of this investigation, the results show that the ejection seat model was statically unstable but became longitudinally and directionally stable with the parachute using the three- and four-point bridle assemblies. Jet simulation and model yaw angle had little effect on the ejection seat longitudinal stability; however, jet simulation increased the parachute drag coefficient. (Author).
