External Pitching Moment (EPM) Due to Turbine Engine Exhaust Impingement on Rocket Assisted Take Off (RATO) Bottle

Martel, John; Dudley, Jonathan G.

doi:10.2514/6.2007-862

Cited by 6 publications

(3 citation statements)

References 2 publications

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“…Presently, a significant number of researchers are engaged in investigating the complex interaction between booster rockets, turbojet engines, UAVs, launch pads during the launch phase [1,2,3,4], and auto takeoff systems [5]. Notably, Martel and Dudley [6] explored the impact of engine exhaust on booster rockets, leading to additional pitching moments. Moreover, the asymmetrical arrangement of the launch pad track can also have a profound effect on the thrust and moment during the takeoff phase [7].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Stability Study of Turbojet Engine During Unmanned Aerial Vehicle Assisted Taking Off Stage

Du,

Wu,

Wang

et al. 2023

J. Phys.: Conf. Ser.

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Rocket Assisted Take Off (RATO) technology is utilized for the takeoff phase of various types of UAVs. RATO creates heavy axial overload for a UAV system, which consequently increases the inlet pressure of the fuel pump of the UAV’s turbojet engine. This situation leads to an abrupt change in fuel supply for its combustor, eventually causing drastic changes in the operating state of the compressor system. In addition, it may potentially induce compressor surge. To resolve this problem, through an experimental investigation, this study delves into the dynamic response of the fuel system during the RATO phase. A two-zone dual-wave coupled compressor model has been established for the intake-turbojet engine system to scrutinize the aerodynamic stability of the turbojet engine during the RATO phase. The findings reveal that when the increase of fuel pump inlet pressure causes changes in the fuel flow rate, it is essential for the engine to re-establish aerodynamic equilibrium in order to mitigate the impacts of abrupt fuel flow step increases. Moreover, it has been observed that the more the ratio of the length of the intake and the cross-section area, the greater the contribution of the inertial force of airflow in the pipe it brings within the passage. This results in a stronger suppression of combustion chamber pressure and flow rate fluctuations induced by fuel step supply, thereby rendering the compressor less susceptible to surge. In summary, this research contributes valuable insights for appropriate matching of intakes, enhancing the ability of the turbojet engine against fuel step supply in the combustion chamber during the takeoff stage and augmenting the aerodynamic and thermodynamic overload resistance capability of the engine.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic Stability Study of Turbojet Engine During Unmanned Aerial Vehicle Assisted Taking Off Stage

Du,

Wu,

Wang

et al. 2023

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

show abstract

“…Compared to the UAV with two boosting rockets, the advantage of UAV with one rocket assisted takeoff is that the synchronism problem is avoided. In paper [5,6,7], the launch dynamics for the UAV with one rocket assisted takeoff, the rail influence on the launch performance and the interaction between the rocket bottle and engine exhaust are analyzed respectively. In this paper, a takeoff process of a small scaled UAV with a single rocket booster is analyzed.…”

Section: Introductionmentioning

confidence: 99%

Takeoff Analysis and Simulation of a Small Scaled UAV with a Rocket Booster

Liu

Fang

et al. 2011

AMR

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This paper analyses the takeoff process of a small scaled UAV (unmanned aerial vehicle) with a single rocket booster. Because the thrust provided by the rocket booster is 10 times as large as the thrust provided by the engines, the effects caused by the boosting rocket on total mass, compound centre of gravity and inertia can not be neglected and are all considered. The inertia of the boosting rocket is calculated by the means of finite element method. Based on the analysis, a nonlinear dynamic model of the UAV is built. Several simulations with different takeoff parameters are conducted to test the takeoff performance. By analyzing simulation results, the acceptable range of boosting angle is investigated.

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“…Much refinement was done on the SDB Moment on the BQM-167 due to engine exhaust computational model as part of this study, which resulted impinging the Rocket Assisted Take Off (RATO) body in the current 11 million cell model. was extremely successfulI 5 3. The desired RATO angle The freestream run matrix that was done in support of setting was calculated from these predicted forces and the model refinement consisted of 800+ computational moments, which ensured successful launch of the target points spread over several different Mach numbers and a drone.…”

Section: F-16 Sdb Jettison Studiesmentioning

confidence: 99%

Applied Computational Fluid Dynamics in Support of Aircraft/Store Compatibility and Weapons Integration-2007 Edition

Babcock

2007

2007 DoD High Performance Computing Modernization Program Users Group Conference

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External Pitching Moment (EPM) Due to Turbine Engine Exhaust Impingement on Rocket Assisted Take Off (RATO) Bottle

Cited by 6 publications

References 2 publications

Aerodynamic Stability Study of Turbojet Engine During Unmanned Aerial Vehicle Assisted Taking Off Stage

Aerodynamic Stability Study of Turbojet Engine During Unmanned Aerial Vehicle Assisted Taking Off Stage

Takeoff Analysis and Simulation of a Small Scaled UAV with a Rocket Booster

Applied Computational Fluid Dynamics in Support of Aircraft/Store Compatibility and Weapons Integration-2007 Edition

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