Author: Timothy A. Talda (2LT, USAF.)Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages :
Book Description
Experimental Investigation of Two-dimensional Confined Jet Thrust Vector Control
Author: Timothy A. Talda (2LT, USAF.)Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages :
Book Description
Experimental Investigation of Two-Dimensional Confined Jet Thrust Vector Control
Author: Timothy A. TaldaPublisher:
ISBN:
Category :
Languages : en
Pages : 135
Book Description
Different types of thrust vector control systems are described, and a comparison of present systems is presented. Confined jet thrust vector control is shown to be an effective alternative. A two-dimensional nozzle that operates as a confined jet thrust vector control nozzle is experimentally demonstrated. Effects of changing geometric variables and inputs on ease of vectoring and performance of vectored thrust are analyzed. Schlieren photographs and movies show flow characteristics. Predictions of performance of operable nozzles are made based on results found in the experiments. Recommendations for further study are made. Keywords: Thrust control; Secondary injection; Two dimensional; Thrust vector control systems; Flow visualization.
Two-Dimensional Confined Jet Thrust Vector Control: Operating Mechanisms and Performance
Author: Jeffrey L. CatonPublisher:
ISBN:
Category :
Languages : en
Pages : 168
Book Description
An experimental investigation of two-dimensional confined jet thrust vector control nozzles was performed. Thrust vector control was accomplished by using secondary flow injection in the diverging section of the nozzle. Schlieren photographs and video tapes were used to study flow separation and internal shock structures. Nozzle performance parameters were determined for nozzle flow with and without secondary flows. These parameters included nozzles forces, vector angles, thrust efficiencies, and flow switching response times. Vector angles as great as 18 degrees with thrust efficiencies of 0.79 were measured. Several confined jet nozzles with variations in secondary flow port design were tested and results were compared to each other. Converging-diverging nozzles of similar design to the confined jet nozzles were also tested and results were compared to the confined jet nozzle results. Existing prediction models for nozzle side to axial force ratio were evaluated. A model for nozzle total forces based on shock losses that predicted values very close to actual results was developed. Keywords: Two dimensional flow; Flow visualization; Control jets; Rocket nozzles; Nozzle gas flow; Reconvergent nozzles. Theses.
Two-Dimensional Confined Jet Thrust Vector Control with Flow Visualization and Variable Flow Geometry
Author: James W. CatesPublisher:
ISBN:
Category :
Languages : en
Pages : 68
Book Description
In this experimental investigation, the performance parameters considered were axial force, side force, and vector angle. Variables included primary pressure, exit-to-throat area ratio, and exit-to-throat axial length. With each test configuration, it was possible to define specific operating modes where the flow was oscillatory, vectored/switchable, and vectored/unswitchable. Only one test configuration yielded a stable axial flow on which secondary injection could be used to study vectoring. Switchable flows existed only at low pressure below the range of test pressures making it impossible to study switching characteristics. Because the flows were attached over the entire range of test pressures, geometric effects were based on the study of these attached flows. Results indicate that the theoretical equations for predicting wall separation points in unconfined nozzles do not accurately predict the separation points in confined jet nozzles. Small variations in axial length, as examined in this study, had a minimal impact on nozzle performance. Primary pressure and exit-to-throat area ratio have the most significant impact on two-dimensional nozzle performance. Keywords: Two dimensional flow; Flow visualization; Axial thrust. (Theses).
Experimental Evaluation of Design Variables for Two-Dimensional Confined Jet Thrust Vector Control Nozzles
Author: Timothy M. HawkesPublisher:
ISBN:
Category :
Languages : en
Pages : 101
Book Description
An experimental study of the axial and vectoring performance of two - dimensional (2-D) confined jet thrust vector control (CJTVC) nozzles was performed. The effects of adding secondary injection ports and changing exit height and secondary injection port location were studied on several 2-D CJTVC nozzles. The axial and vectoring performance results for these nozzles were measured over a range of pressure ratios. An analytical method for predicting flow separation was found to be applicable to these nozzles. Guidelines for designing 2-D CJTVC nozzles, that can be vectored using secondary injection, were established.
Experimental Study of Three-dimensional Confined Jet Thrust Vector Control (CJTVC).
Author: Bobby G. Brown (CAPT, USAF.)Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
An Experimental Investigation of Thrust Vector Control by Secondary Injection
Author: Richard D. GuhsePublisher:
ISBN:
Category : Injections
Languages : en
Pages : 130
Book Description
An experimental investigation was conducted to examine the flow field produced when a secondary gas is injected into a supersonic primary stream. A preliminary analytical investigation revealed that several parameters (such as the primary and secondary gas properties, flow conditions and geometrical parameters) were influential in determining the nature of the flow field produced by secondary injection and the resulting side force. The investigation reported herein is concerned with the results of a systematic variation of these parameters. Experiments were conducted in a Mach 2.0, two-dimensional blow down wind tunnel utilizing air as the primary and secondary gases. The secondary gas was injected through a rectangular slot extending the width of the primary nozzle. The area of the slot was varied from 1/2% to 10% of the primary nozzle throat area in five increments. For each value of slot area the secondary to primary stagnation pressure ratio was varied from 0.301 to 1.175 in six increments. The experiments were conducted for injection normal to the nozzle axis and at an angle of 10 degree upstream of this normal at an axial position where the primary Mach number was 1.90. In each case preliminary diagnostic investigations (optical) were conducted to determine the nature of the flow field.
Two-dimensional Confined Jet Thrust Vector Control
Author: T. A. TaldaScientific and Technical Aerospace Reports
Author: Experimental Study of Axisymmetric Confined Jet Thrust Vector Control Nozzle Performance and Behavior
Author: Peter G. Lambert (CAPT, USAF.)Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description