Contribution to research of spoiler and dome deflector TVC systems in rocket propulsion

Davidović, Nikola; Miloš, Predrag; Jojić, Branislav; Miloš, Marko

doi:10.17559/tv-20140621063849

Cited by 3 publications

(7 citation statements)

References 2 publications

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“…The experimental research is conducted on the experimental nozzle dome deflector integrated on the propellant powered experimental thrust generator, fig. 10, within total pressure domain values presented in [2]. Figure 9 has shown separated induced relative lateral forces and estimated thrust losses shown in fig.…”

Section: Comparative Analysis Of Experimental and Cfd Simulation Modelmentioning

confidence: 91%

“…'s longitudinal observed cross-sections, fig. 1(a) As presented in the papers [1,2,12,13] both interceptors and dome deflectors are making so called liquid wedge as a form of re-circulation zone. This is visible within the boundaries attached to the lip of immersed deflector depth and boundary-layer separation point, at the length, l, (considered previously here), and given in the tab.…”

Section: Flow Simulation Visual Analysismentioning

confidence: 99%

“…The construction of nozzle obstacle gas-dynamical thrust vector control (TVC) subsystems is aimed to design the lateral thrust force most frequently used in small tactical missiles for the flight control coupled by guidance laws. Components of these systems such as the jet tabs (nozzle interceptors), jet avators nozzle dome deflector, and other types of nozzle mechanical obstacles are motor/nozzle internal thrust vectoring devices explained in detail in papers [1][2][3] All are intended to realize complex internal nozzle flow fields, with high values of flow parameters and gradients with the aim of the thrust vectoring, being of the priority competence [4]. As the choice for TVC applications the flow fields' parameters become of crucial importance for TVC performances predictions.…”

Section: Introductionmentioning

confidence: 99%

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Nozzle flow gas-dynamical properties under dome deflector thrust vector system effect

Boulahbal¹,

Momcilo²,

Rezgui³

2019

THERM SCI

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The paper discusses the gas-dynamical disturbances in the nozzle jet-flow, discovered by numerical simulations, caused by mechanical-shaped jet obstacles, immersed in the exit area of the nozzle flow for thrust vector control purposes. External profiled tab shaped as a dome deflector is used to disturb the flow in the exit area, which provides the comprehensive 3-D nozzle separated flow zones with different high gradients of flow stream parameters. Discovered complexity of the flow pattern in the 3-D nozzle separated zone is exploited by complex CFD simulations and used for the numerical calculations, implemented by FLUENT commercial code. Pressure and temperature distributions data along the nozzle walls, as well as on the deflector wall, are used to estimate induced lateral and thrust forces by pressure integral. Induced forces estimated by numerical simulations and hot gases nozzle tests are compared as relative efficiency values to prove the quality of numerical simulations. Numerical calculations are carried out in the nozzle, obstacle, and the gap flows showed good agreement to the calculated and measured induced forces. The main aim of the developed method is to establish an approved calculation tool to compare and choose thrust vector control possibilities based on tabs with different forms of immersion in the external jets.

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Section: Comparative Analysis Of Experimental and Cfd Simulation Modelmentioning

confidence: 91%

Section: Flow Simulation Visual Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Nozzle flow gas-dynamical properties under dome deflector thrust vector system effect

Boulahbal¹,

Momcilo²,

Rezgui³

2019

THERM SCI

View full text Add to dashboard Cite

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“…Ratios beyond 30% can hardly be achieved in operational practice with 3D nozzles (practical limit in [14] is set to about 20%), except in case of small rocket nozzles (40% value, mentioned in [7]). In case of rocket engines, zero gap would represent an "ideal" tab, with maximum effectiveness; small gap is allowable for different technological and/or operational reasons.…”

Section: Cfd Analysis Of Jet Tabs and Comparisons With The Experimentmentioning

confidence: 99%

“…In case of rocket engines, zero gap would represent an "ideal" tab, with maximum effectiveness; small gap is allowable for different technological and/or operational reasons. Larger gaps, of the order of 5% ÷ 10%, would substantially degrade tab efficiency [3], [14], etc.…”

Section: Cfd Analysis Of Jet Tabs and Comparisons With The Experimentmentioning

confidence: 99%

Comparative CFD analysis of a 2D supersonic nozzle flow with jet tab and jet vane

2017

Teh. vjesn.

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Original scientific paper In this study, a CFD (Computational Fluid Dynamics) computational model has been established, with the aim to properly simulate complex supersonic flow generated by a 2D convergent-divergent nozzle. For the purpose of rocket engine thrust vector control (TVC) simulations, initially several jet tab positions were used to generate up to 30% shadowing of the nozzle exit, without and with a gap between tab and exit. Numerical results were compared with the existing experimental data, both quantitatively and qualitatively, and fair agreements have been obtained in both senses. The same CFD settings have then been applied for the computational analysis of another TVC type -the jet vane, which was analysed in four different adopted configurations with respect to the nozzle. Stable convergence of solutions has been achieved, up to 40° of vane deflections. Performed calculations have enabled comparisons of the two considered TVC types, in the sense of the achieved thrust force deflections, and thrust losses. Keywords: CFD analysis; flow visualization; jet tab; jet vane; supersonic nozzle; thrust vector control Usporedna CFD analiza 2D strujanja supersoničnog mlaznika sa spojlerom i s mlaznim krilcemIzvorni znanstveni članak U okviru ove studije, ustanovljen je CFD (Computational Fluid Dynamics) proračunski model za potrebe analize kompleksnog nadzvučnog strujnog polja generiranog 2D konvergentno-divergentnim mlaznikom. U cilju simulacije upravljanja vektorom potiska (UVP) raketnih motora, najprije je rabljen spojler, postavljen u nekoliko položaja do maksimalnih 30% zasjenčenja površine izlaznog presjeka, bez procjepa i s procjepom u odnosu na izlaz. Proračunski rezultati uspoređeni su s raspoloživim eksperimentalnim rezultatima kvantitativno i kvalitativno, pri čemu su u oba slučaja dobivena zadovoljavajuća

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Gas rudder 2DOF FOPID position control based on CSFLA optimisation

Qi,

Deng,

Shen

et al. 2024

J. Phys.: Conf. Ser.

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Aiming at the problems of parameter variety, rigid-flexible coupling and external unknown factors interference in the process of spacecraft propulsion, a two-degree-of-freedom fractional-order PID (2DOF FOPID) controller based on a coevolutionary shuffled frog leaping algorithm (CSFLA) is designed for the high-precision control of the gas rudder servo control system. The anti-interference and target tracking capabilities of 2DOF PID is combined with the advantage of FOPID, which is insensitive to the parameters of the controlled object, to improve the performance of the control system as a whole. CSFLA is formed by integrating the self-learning evolution of elite populations and the interactive learning strategy among populations into the SFLA to enhance the global searching ability and searching accuracy of SFLA, and CSFLA is used to optimize the parameters of the 2DOF FOPID controller. The simulation results show that the designed CSFLA-2DOF FOPID controller has the advantages of fast response speed, small overshoot, strong tracking performance and strong anti-disturbance ability, which improves the dynamic and static performance and anti-disturbance ability of the gas rudder servo control system.

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Contribution to research of spoiler and dome deflector TVC systems in rocket propulsion

Cited by 3 publications

References 2 publications

Nozzle flow gas-dynamical properties under dome deflector thrust vector system effect

Nozzle flow gas-dynamical properties under dome deflector thrust vector system effect

Comparative CFD analysis of a 2D supersonic nozzle flow with jet tab and jet vane

Gas rudder 2DOF FOPID position control based on CSFLA optimisation

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