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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.
Design News
None
Welt-Adressenbuch
None
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)
Wind Tunnel Measurements of Total Force and Extremity Flail Potential Forces on a Crew Member in Close Proximity to a Cockpit
In order to determine the aerodynamic forces acting upon a crew member/escape seat combination at transonic speeds, and the flail potential forces acting on the crewmember's extremities, an existing half scale man/seat combination was integrated with a model of the forward portion of the F-16. The combination was tested in the Arnold Engineering Development Center Propulsion Wind Tunnel (PWT) Facility Transonic Wind Tunnel (16T) during the period September 9 to September 15, 1978, over the Mach number range 0.4 to 1.2. The basic data obtained in this way are reported in Reichenau. The present report describes the experimental set-up in detail and presents some typical force and force area (f...
