Design Methodology for the Airbreathing Second Stage of a Rocket-Scramjet-Rocket Launch Vehicle

Jazra, Thomas; Smart, Michael K.

doi:10.2514/6.2011-2377

Cited by 2 publications

(2 citation statements)

References 17 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Reducing the launch cost of the rocket has always been the pursuit of the aerospace powers engaged in the development of space transportation systems (Deneu et al , 2005). Reusable booster vehicle (RBV) (Qi et al , 2013), vertical takeoff and horizontal landing vehicle (VTHL) (Dumke et al , 2020), vertical takeoff and vertical landing vehicle (VTVL) (Zhang et al , 2018) and reusable second stage rocket (Thoms and Michael, 2011) are widely studied to achieve this goal. However, the above-mentioned launch vehicles can only be partially reused, and the number of reuses is limited.…”

Section: Introductionmentioning

confidence: 99%

Predefined-time control for a horizontal takeoff and horizontal landing reusable launch vehicle

Zhang¹,

Liang

et al. 2021

AEAT

View full text Add to dashboard Cite

Purpose This paper aims to investigate the problem of attitude control for a horizontal takeoff and horizontal landing reusable launch vehicle. Design/methodology/approach In this paper, a predefined-time attitude tracking controller is presented for a horizontal takeoff and horizontal landing reusable launch vehicle (HTHLRLV). Firstly, the attitude tracking error dynamics model of the HTHLRLV is developed. Subsequently, a novel sliding mode surface is designed with predefined-time stability. Furthermore, by using the proposed sliding mode surface, a predefined-time controller is derived. To compensate the external disturbances or model uncertainties, a fixed-time disturbance observer is developed, and its convergence time can be defined as a prior control parameter. Finally, the stability of the proposed sliding mode surface and the controller can be proved by the Lyapunov theory. Findings In contrast to other fixed-time methods, this controller only requires three control parameters, and the convergence time can be predefined instead of being estimated. The simulation results also demonstrate the effectiveness of the proposed controller. Originality/value A novel predefined-time attitude tracking controller is developed based on the predefined-time sliding mode surface (SMS) and fixed-time disturbance observer (FxTDO). The convergence time of the system can be selected as a prior control parameter for SMS and FxTDO.

show abstract

Section: Introductionmentioning

confidence: 99%

Predefined-time control for a horizontal takeoff and horizontal landing reusable launch vehicle

Zhang¹,

Liang

et al. 2021

AEAT

View full text Add to dashboard Cite

show abstract

“…Over the years different design solutions have been proposed to realize reliable and cost-effective systems. Canonical solutions for access-to-space systems based on two-, or multi-stage-to-orbit designs improved efficiency while allowing for some degree of re-usability [1,2]. The technology of combined cycle propulsion (CCP) systems has allowed switching between different propulsion technologies in a way to ensure the most efficient flight path as exemplified by Marquardt's conceptual design of the Supercharged Ejector RamJet (SERJ) engine [3].…”

Section: Introductionmentioning

confidence: 99%

Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

Hoste

Casseau

Fossati

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

View full text Add to dashboard Cite

Two open-source solvers, Eilmer and hyFoam, are here considered for their performance in simulating high-speed flows in different flow conditions and geometric configurations typical of propulsive systems at supersonic speeds. The goal is to identify the open-source platform providing the best compromise between accuracy, flexibility and computational cost to eventually simulate the flow fields inside ramjet and scramjet engines. The differences in terms of discretization and solution methods of the selected solvers are discussed in terms of their impact on solution accuracy and computational efficiency and in view of the aerothermodynamic analysis and design of future transatmospheric propulsive systems. In this work steady state problems are considered. Numerical results of two scramjet type engines demonstrated a similar predictive capability of both codes in non-reacting conditions. These results highlight their potential to be considered for further characterization of overall engine performance. * PhD Candidate, AIAA Student Member. † Lecturer, AIAA Member . ‡ Senior Lecturer.

show abstract

Design Methodology for the Airbreathing Second Stage of a Rocket-Scramjet-Rocket Launch Vehicle

Cited by 2 publications

References 17 publications

Predefined-time control for a horizontal takeoff and horizontal landing reusable launch vehicle

Predefined-time control for a horizontal takeoff and horizontal landing reusable launch vehicle

Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

Contact Info

Product

Resources

About