An Experimental Investigation of Thrust Vector Control by Secondary Injection PDF Download

Author: Richard D. Guhse
Publisher:
ISBN:
Category : Injections
Languages : en
Pages : 132

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Author: Philip Alan Graham
Publisher:
ISBN:
Category :
Languages : en
Pages : 110

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Author: Timothy A. Talda
Publisher:
ISBN:
Category :
Languages : en
Pages : 135

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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.

Author: Richard D. Guhse
Publisher:
ISBN:
Category : Injections
Languages : en
Pages : 130

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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.

Author: Tatsuo Yamanaka
Publisher:
ISBN:
Category :
Languages : en
Pages : 50

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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 123

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A theoretical and experimental investigation of thrust control by secondary gas injection was completed. Thrust control is treated from the two aspects of thrust modulation and vector control. The thrust modulation study is concerned with the use of injection as a means of throttling the main nozzle flow. The performance (flow throttling and thrust) of a variety of secondary injection configurations was measured with a low pressure-ratio, axially symmetric nozzle as well as a high pressure-ratio, two-dimensional nozzle. The flow throttling results agree with an anlysis based on three flow models and the schlieren photographs (from the two-dimensional tests) show that all three types of flow occur. The vector control study concerns asymmetric secondary gas injection as a means of controlling the direction of the thrust vector.

Author: Harold R. Henry
Publisher:
ISBN:
Category :
Languages : en
Pages : 64

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The report presents the fundamental equations of fluid mechanics have been applied to particular steady-state models of the interaction between secondary and primary fluids. The analysis has resulted in a system of equations and a numerical procedure which is amenable to solution by use of a high speed digital computer. A dimensional analysis has been performed and is presented herein as a guide to the performance of experiments and to the comparison between experimental and theoretical results. An experimental program has been planned within the scope of this project and is presented in the progress report dated July, 1965. The general discussion of three cases for which the shape of the secondary jet has been obtained is presented in the body of the report. A detailed presentation of one of the cases is presented in the appendix. The analysis and computation for the latter case was written as a Master's Thesis. (Author).

Author: Glenn B. Russell
Publisher:
ISBN:
Category :
Languages : en
Pages : 96

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An experimental investigation was conducted to determine the interaction of a thrust vector control device, employing the Coanda effect, on an exhaust jet issuing from a round convergent nozzle. The thrust vector device consisted of a curved surface which the jet attached to, and sideplates on each side of this surface. Opening control ports in the surface to ambient conditions caused the jet to detach from the surface. Test positions of the thrust vector device were 6, 9, and 12 degrees surface angle, 0.00 to 0.73 inches axial distance, and 0.00 to 0.40 inches radial distance. The best operation of the device occurred with a gap present between the surface of the device and the nozzle. This allowed the exhaust jet to pump entrained secondary air over the device's surface, creating a negative pressure distribution over the surface. A position with no gap present restricted the entrainment and pumping of secondary air, causing a portion of the exhaust jet to separate from the main airstream and form a separate core of air flowing over the surface. This separation resulted in a degradation of performance (lift and drag). The effects of surface angle, axial displacement, and radial displacement on the exhaust jet were found to be interrelated, and must all be considered together to find the optimum operating position of the device.

Author: Cornelius C. Shih
Publisher:
ISBN:
Category :
Languages : en
Pages : 122

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The report consists of four sections listed as follows: Performance characteristics of a supersonic fluidic amplifier with extended legs for a secondary injection thrust vector control system; secondary injection thrust vector control using vortex amplifiers; feasibility analysis of holographic techniques for applications to secondary injection TVC systems analysis; and, dynamic responses of pressure outputs resulting from control signal inputs in the operation of a supersonic fluidic amplifier. (Author).

Author: C. A. Zimmerman
Publisher:
ISBN:
Category :
Languages : en
Pages : 28

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Book Description
On the basis of experimentally acquired data, thrust vector control systems utilizing secondary injection of fluids into supersonic nozzles have been developed. Several widely divergent theoretical and analytical treatments of the phenomena have appeared as new applications were proposed. The paper reviews the several theories and attempts correlation with the experimental data. Secondary injection thrust vector control results from the injection of fluid (gas or liquid) into the primary exhaust stream of the rocket motor through ports in the divergent section of the nozzle. A shock is induced resulting in a pressure unbalance in the exit cone. The resultant side force, controllable in magnitude and direction, can be utilized for precise vehicle control. (Author).