Experimental and theoretical comparison of the Probe Thrust Vector Control concept

Cavalleri, Robert; Tiarn, Weihnurng; Lewis, Lynn

doi:10.2514/6.1991-2476

Cited by 7 publications

(3 citation statements)

References 2 publications

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“…Furthermore, they attempted an active cooling technique around the probe to prolong the service life of the material and clarified how the coolant distributes in the flow field and how much of it is essential. Cavalleri et al 28 experimentally and theoretically investigated multiple probes control technology mounted on a flat plate and found that a quick response is gained. What needs to be emphasized is that the experiment is carried out in a uniform freestream instead of an accelerating supersonic flow like a converging-diverging nozzle flow.…”

Section: Introductionmentioning

confidence: 99%

Study on aerodynamic features of rod thrust vector control for physical applications

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Mechanical thrust vector control is a classical and important branch in the vectoring control field, offering an extremely reliable control effect. In this article, a simple technology using a cylindrical rod has been numerically investigated to achieve jet controls for three-dimensional conical axisymmetric nozzles. Complex flow phenomena caused by the cylindrical rod on a flat plate and in a converging–diverging nozzle are elucidated with the purpose of a profound understanding of this technique for physical applications. Published experimental data are used to validate the dependability of current CFD results. A grid sensitivity study is carried through and analyzed. The result section discusses the impacts of three factors on performance, involving the rod penetration height, rod location, and nozzle pressure ratio. Significant vectoring performance variations and flow topologies descriptions are illuminated in full detail. When the rod penetration height changes, this technique has an effective control range, namely H/Rt ≤ 0.4. In this effective control range, the vectoring angle and efficiency increase and the thrust coefficient decreases with a deeper rod insertion. As the rod location moves downstream towards the nozzle exit, the vectoring angle increases and the thrust coefficient decays. Moreover, the direction of jet deflection remarkably varies for diverse rod locations. While the nozzle pressure ratio increases, the vectoring angle initially increases to reach the maximum level and then decays slightly. Meanwhile, the thrust coefficient continuously increases.

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Section: Introductionmentioning

confidence: 99%

Study on aerodynamic features of rod thrust vector control for physical applications

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…They expounded that this potential technique has adequate capacity to generate a required thrust and saves much weight and cost. Cavalleri et al [28] experimentally and theoretically investigated multiple probe control technology mounted on a flat plate in a supersonic freestream and found that a quick response is gained. Cavalleri [29] testified excellent pitching and yawing control effectiveness using four probes with an interval of 90 °.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Rod Thrust Vector Control for Physical Applications

2021

International Journal of Aerospace Engineering

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Mechanical thrust vector control is a classical and significant branch in the thrust vector control field, offering an extremely reliable control effect. In this article, steady-state and unsteady-state aerodynamic characteristics of the rod thrust vector control technology are numerically investigated in a two-dimensional supersonic nozzle. Complex flow phenomena caused by the penetrating rod in the diverging part of the supersonic nozzle are elucidated with the purpose of a profound understanding of this simple flow control technique for physical applications. Published experimental data are used to validate the dependability of current computational fluid dynamics results. A grid sensitivity study is carried through and analyzed. The result section discusses the impacts of two important factors on steady-state aerodynamic features, involving the rod penetration height and the rod location. Furthermore, unsteady-state flow features are analyzed under various rod penetration heights for the first time. Significant vectoring performance variations and flow topology descriptions are illuminated in full detail. While the rod penetration height increases, the vectoring angle increases, whereas the thrust coefficient decreases. As the rod location moves downstream close to the nozzle exit, the vectoring angle and thrust coefficient increase. In terms of unsteady-state aerodynamic effects, certain pressure oscillations occur upstream of the rod, which resulted from the expanding and shrinking of the upstream anticlockwise separation bubbles.

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“…However in 1990's Cavelleri and his coworkers proposed use of a solid probe instead of secondary injection for thrust vector control for rocket 3nozzles and the results of their findings can be found in Ref. [23][24][25][26][27] Recently experiments were conducted using such method in a convergent-divergent (C-D) nozzle for wall pressure distribution and for calculation of forces and moments generated to access the effectiveness of the method. 28 In the present work the results of preliminary investigation on the possible use of a rectangular solid strut spanning the width of expansion ramp surfaces in SERN of a scramjet thruster model have been presented.…”

Section: Introductionmentioning

confidence: 99%

An experimental investigation on the use of a rectangular strut in a scramjet thruster for thrust vector control

Rose

Sridhar

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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An experimental investigation was carried out to find the effect of a strut spanning across the width of a single expansion ramp of a laboratory model scramjet thruster as a thrust vector control device. Cold flow tests were conducted with operating total pressures ranging from 4 bar to 10 bar and the thruster exhaust was to ambient atmosphere. The mass flow rate varied from 0.105 kg/s to 0.263 kg/s. Experiments were conducted by varying the strut height at different operational total pressures to find if any thrust vector control could be achieved to supplement the maneuverability of hypersonic vehicle with aerodynamic control. The laboratory model consisted of an isolator, a divergent combustor followed by a single expansion ramp. Except the side walls, the thruster was fabricated with stainless steel. A high quality acrylic sheet was used for internal flow visualization by a schilieren system. The wall pressure was recorded at different locations from the combustor inlet to ramp trailing edge. Shock pattern was studied from the schilieren images and it was observed that an increase in strut height caused a downward deflection of the exhaust. From the wall pressure distribution, two dimensional side force coefficient and pitching moment coefficient were calculated and the effect of strut height variation on the above coefficients was plotted. Results from experiments indicated that the presence of the strut yielded noticeable changes in side force and pitching moment. The increase in strut height provided exhaust stream directional changes which may be useful in maneuvering the vehicles employing scramjet propulsion system.

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Experimental and theoretical comparison of the Probe Thrust Vector Control concept

Cited by 7 publications

References 2 publications

Study on aerodynamic features of rod thrust vector control for physical applications

Study on aerodynamic features of rod thrust vector control for physical applications

Numerical Study on Rod Thrust Vector Control for Physical Applications

An experimental investigation on the use of a rectangular strut in a scramjet thruster for thrust vector control

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