Numerical Investigation of Rail Influence on Initial Forces and Moments for Subscale Aerial Drone with Rocket Assisted Take-Off (RATO)

Martel, John; Eymann, Timothy A.

doi:10.2514/6.2008-6401

Cited by 3 publications

(2 citation statements)

References 4 publications

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“…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]. Compared to single solid-rocket boosters [8], double solid-rocket boosters [9] exhibit different internal ballistic performance, asymmetrical installation, unsynchronized ignition time, and varying time to reach the end of combustion, resulting in the problem of synchronous operation of double solid-rocket boosters.…”

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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Addressing Launch and Deployment Uncertainties in UAVs with ESO-Based Attitude Control

Yang,

Cai,

et al. 2024

Drones

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This paper describes the design and implementation of a novel three-axis attitude control autopilot scheme for tube-launched, air-deployed UAVs. In early flight tests, various factors, such as model uncertainties during launch, aerodynamic uncertainties, geometric parameter changes during deployment, and significant uncertainties in booster rocket installation, exceeded the control capabilities of the attitude autopilot, causing flight instability. In order to address these issues, a numerical simulation model of the full launch process considering deviations was established based on early flight tests. A cascade attitude controller was then designed using an extended state observer (ESO), and the boundedness of control errors under unknown bounded disturbances was theoretically proven, providing requirements for the parameter tuning of the cascade controller. Comparative experiments and a second flight test both demonstrate that the ESO-based cascade attitude controller exhibits strong feedforward disturbance compensation under high-uncertainty conditions, effectively achieving stable control within the flight envelope.

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Numerical Investigation of Rail Influence on Initial Forces and Moments for Subscale Aerial Drone with Rocket Assisted Take-Off (RATO)

Cited by 3 publications

References 4 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

Addressing Launch and Deployment Uncertainties in UAVs with ESO-Based Attitude Control

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