Download or read book Wind Tunnel Tests of a 0 65 Scale Ejection Seat with and Without Yaw Stabilizers written by Peter Ayoub and published by . This book was released on 1984 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Preliminary Analysis of Wind Tunnel Test of a 1 2 Scale Model of an Ejecting Crewman and Ejection Seat written by Alastair Anthony and published by . This book was released on 1979 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Doubts were raised as to the integrity of the rest of the structure when the neck member of a model crewman failed during tunnel measurements of the limb forces during ejection. The accuracy of the load estimates used in the pretest stress analysis clearly needed to be checked. Meanwhile, testing was resumed at restricted pressure values with a non-load-measuring replacement for the neck member. From a sampling of the test data, the distribution of bending and torsional moments along the limbs is clearly revealed and, with its variation with attitude and Mach number, presents no great surprises. Values critical to the stress analysis confirm the estimated values. The neck pillar, designed by a subcontractor, had been designed for sensitivity in bending under the head loads without catering for torsion in the member if these load should in the event be appreciably offset from its axis. Although there is little confirmation of the magnitude of the head loads, there is some indication the offsets in excess of one inch in these loads are to be expected in the real situation, and that the resulting torsion was the cause of the failure. (Author).
Download or read book Advanced Ejection Seat for High Dynamic Pressure Escape Wind Tunnel Test Report written by J. O. Bull and published by . This book was released on 1980 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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)
Download or read book Aeromechanical Properties of Ejection Seat Escape Systems written by Bobby J. White and published by . This book was released on 1974 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt: Valid prediction of combat aircraft ejection seat performance has been impossible because of the lack of technical data on its basic physical properties and aerodynamic characteristics. Wind tunnel tests were conducted using a full scale F-101 ejection seat and a half scale F-106 ejection seat to determine the aerodynamic characteristics. Data were obtained at free stream Mach numbers of 0.2, 0.4, 0.6 and 0.8 for the full scale model and 0.6, 0.9, 1.2 and 1.5 for the half scale model. Angle of attack was varied from 0 to 360 degrees for the half scale model and -45 and +90 degrees for the full scale model. Yaw angles were varied from 0 to 45 degrees. The shape of the rocket catapult exhaust plume was simulated by using high pressure air. (Modified author abstract).
Download or read book Advanced Ejection Seat for High Dynamic Pressure Escape Wind Tunnel Test Report written by and published by . This book was released on 1980 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Download or read book Wind Tunnel Test of Aces II Ejection Seat with Anthropometric Dummy is Asymmetric Configurations written by Fred W. Hawker and published by . This book was released on 1979 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: Previous investigations have determined the aerodynamic forces and moments acting upon an open ejection seat and its occupant when the seat occupant was sitting symmetrically with respect to the seat axes, with his limbs in the correct 'stowed' positions. The present investigation was undertaken to determine the changes in the aerodynamic forces due to deviations from this ideal position; principally off-center asymmetry and changes to limb movement. (Author).
Download or read book Aerodynamic Characteristics of an Ejection Seat Escape System with a Stabilization Parachute at Mach Numbers from 0 3 Through 1 2 written by David E. A. Reichenau and published by . This book was released on 1972 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Download or read book Aerodynamic Characteristics of a Full Scale F 101 Ejection Seat with an Anthropomorphic Dummy at Free Stream MACH Numbers from 0 2 to 0 8 written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test was conducted in the wind tunnel to determine the aerodynamic characteristics of a full-scale F-101 ejection seat occupied by an anthropomorphic dummy at free-stream Mach numbers of 0.2, 0.4, 0.6, and 0.8. Angle of attack was varied from -45 to +90 deg, and angle of yaw was varied from 0 to +45 deg, depending on the angle of attack. The model was observed particularly directional and lateral stability near zero angle of yaw.
Download or read book Aerodynamic Characteristics of an Ejection Seat Escape System with a Stabilization Parachute at Mach Numbers from 0 3 Through 1 2 written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Download or read book Aerodynamic Characteristics of an Ejection Seat Escape System with a Stabilization Parachute at Mach Numbers from 0 3 Through 1 2 written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Download or read book Aerodynamic Characteristics of a Full Scale F 101 Ejection Seat with an Anthropomorphic Dummy at Free Stream MACH Numbers from 0 2 to 0 8 written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test was conducted in the wind tunnel to determine the aerodynamic characteristics of a full-scale F-101 ejection seat occupied by an anthropomorphic dummy at free-stream Mach numbers of 0.2, 0.4, 0.6, and 0.8. Angle of attack was varied from -45 to +90 deg, and angle of yaw was varied from 0 to +45 deg, depending on the angle of attack. The model was observed particularly directional and lateral stability near zero angle of yaw.
Download or read book On the Avoidance of Limb Flail Injury by Ejection Seat Stabilization written by Peter R. Payne and published by . This book was released on 1974 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: After a review of the various causes of limb flail injury during high speed escape from an aircraft in an open ejection seat, the problem of flailing due to seat aerodynamic instability is addressed. The author concluded that there is no practical way of avoiding injury in an unstable seat. The causes of ejection seat instability are then examined, and a number of conventional and unconventional stabilization systems discussed. The author concluded that a new approach -- the in-plane stabilizer -- is probably the optimum solution to the problem. The theory of the in-plane stabilizer is developed and its effectiveness confirmed by full scale wind tunnel tests with an F-105 seat containing live human subjects. (Author).
Download or read book Aerodynamic Characteristics of an Ejection Seat Escape System with Cold Flow Rocket Plume Simulation at Mach Numbers from 0 6 Through 1 5 written by and published by . This book was released on 1969 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test was conducted in a transonic wind tunnel to determine the aerodynamic characteristics of a 0.5-scale ejection seat escape system with a dummy crew member attached during simulated rocket-off and rocket-on conditions. Results were obtained at free-stream Mach numbers of 0.6, 0.9, 1.2, and 1.5 through a model angle-of-attack range of 360 deg and model yaw angles up to 45 deg. High pressure air was used to simulate the escape rocket jet plume at altitudes from sea level to 40,000 ft. (Author).
Download or read book Aerodynamic Characteristics of an Ejection Seat Escape System with Cold Flow Rocket Plume Simulation at Mach Numbers from 0 6 Through 1 5 written by David E. A. Reichenau and published by . This book was released on 1969 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test was conducted in a transonic wind tunnel to determine the aerodynamic characteristics of a 0.5-scale ejection seat escape system with a dummy crew member attached during simulated rocket-off and rocket-on conditions. Results were obtained at free-stream Mach numbers of 0.6, 0.9, 1.2, and 1.5 through a model angle-of-attack range of 360 deg and model yaw angles up to 45 deg. High pressure air was used to simulate the escape rocket jet plume at altitudes from sea level to 40,000 ft. (Author).
Download or read book X 15 Research Results written by Wendell H. Stillwell and published by . This book was released on 1965 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Engineering the Space Age a Rocket Scientist Remembers written by Robert Brulle and published by Createspace Independent Publishing Platform. This book was released on 2012-08 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Rarely is a reader exposed to such an extraordinary, multifaceted presentation of aerospace technology as Bob Brulle narrates in this book. After returning from duty as a combat fighter pilot in World War II, this Belgian immigrant developed a multitalented and innovative aerospace career path that addressed many of the aerospace professions. Along the way he forged a career in the aviation and space field that resulted in his participating in several of the most momentous aerospace achievements of the past century. He also expanded his education through hard work to a level at which he was qualified to teach graduate-level aerospace engineering courses. It is interesting to follow how the analysis and design techniques of aerospace vehicles progressed over the years, which incidentally reveals the large role that the computer played in making that possible. The story on the early Cape Canaveral operations was amusing and showed that enterprising innovations played a large role in a successful undertaking. Some of the projects described were a surprise, as I had never heard of them, like reading how a pencil-shaped missile was built that could fly and maneuver over an intercontinental distance at a high hypersonic velocity. He also described how American engineers and scientists fought the Cold War battle for technological supremacy on their desks and in their laboratories. The initiatives by which this enterprising engineer develops his technical approach to a project are very informative and offer the reader an insight into the workings of successful operations. He achieves an interesting behind-the-scenes look at how aerospace history is made by weaving in the historical significance of these projects as they are developed. As a former aeronautical engineer at the rapidly growing Mc- Donnell Aircraft Corporation, Bob gives us an interesting exposure to the importance of top management's relationship with the workforce in a successful company. "Mr. Mac" made it a point to make all his employees team members by frequent communication and friendly association.
Download or read book Sweeping Forward written by and published by . This book was released on 2013 with total page 328 pages. Available in PDF, EPUB and Kindle. Book excerpt: The X-29 was an unusual aircraft with a truly unique silhouette. It combined many features that challenged the technologies of its day and represented special problems for the developers and the team of testers responsible for documenting its features and design goals. This book is a look at the "big picture" of what this team accomplished in a relatively fast-paced test program involving the truly unique X-29.
