Wind Tunnel Tests of a 0.65 Scale Ejection Seat with and Without Yaw Stabilizers PDF Download
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Author: Peter Ayoub
Publisher:
ISBN:
Category : Pilot ejection seats
Languages : en
Pages : 224
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Book Description
Author: Peter Ayoub
Publisher:
ISBN:
Category : Pilot ejection seats
Languages : en
Pages : 224
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Book Description
Author: Alastair Anthony
Publisher:
ISBN:
Category : Biomechanics
Languages : en
Pages : 52
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Book Description
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).
Author: J. O. Bull
Publisher:
ISBN:
Category : Aircraft survival equipment
Languages : en
Pages : 140
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Book Description
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)
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
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).
Author: Fred W. Hawker
Publisher:
ISBN:
Category : Biomechanics
Languages : en
Pages : 58
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Book Description
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).
Author: Bobby J. White
Publisher:
ISBN:
Category :
Languages : en
Pages : 132
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Book Description
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).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
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.
Author: Fred W. Hawker
Publisher:
ISBN:
Category : Biomechanics
Languages : en
Pages : 100
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Book Description
The ACES-2 seat was mounted in a wind tunnel in various attitudes of pitch and yaw. The hand and foot rests were equipped with means to measure limb dislodgement forces. Overall forces and moments were measured at the seat mount. Human subjects were used as seat occupants for gross force and moment data on the seat/occupant combination, as well as limb dislodgement force measurements. Anthropomorphic dummies were used for an extended range of yaw angles around to 180 degrees. Only gross force and moment data for the seat/occupant combination were taken with the dummy subjects. The limb dislodgement results are complementary to earlier tests at low pitch angles and show general reductions in magnitude as the pitch angle is increased.
Author:
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ISBN:
Category :
Languages : en
Pages : 0
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Book Description
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).
Author: Peter R. Payne
Publisher:
ISBN:
Category :
Languages : en
Pages : 86
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Book Description
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).
