Multi-constrained ascent guidance for solid propellant launch vehicles

Xu, Zhi; Zhang, Qian

doi:10.1016/j.ast.2018.01.032

Cited by 17 publications

(3 citation statements)

References 6 publications

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“…As for the ascent phase of launch systems, the iterative guidance method has been widely and successfully used in the past few decades [5,6]. However, for most rocket engines, the thrust magnitude is uncontrollable, and the time and position of orbital injection cannot be constrained based on the iterative guidance method.…”

Section: Introductionmentioning

confidence: 99%

A Convex Approach for Trajectory Optimization of Super-Synchronous-Transfer-Orbit Large Launch Systems with Time-Position Constraints

Sun

Chen

et al. 2022

International Journal of Aerospace Engineering

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This paper presents a trajectory optimization algorithm for super-synchronous-transfer-orbit (SSTO) large launch systems by convex optimization. The payload of SSTO launch systems is typically a geostationary equatorial orbit (GEO) satellite, and the time and position of orbital injection are constrained, which is quite different from the case of general satellites. In this paper, the optimal control problem of SSTO large launch systems is formulated considering the terminal constraints including orbital elements and the time-position equation. To improve the computational performance of the algorithm, the terminal orbital element constraints are expressed in the perifocal coordinate system with second-order equations. And then, several convexification techniques and their modified strategies are applied to transform the original trajectory optimization problem into a series of convex optimization problems, which can be solved iteratively with high accuracy and computational efficiency. Considering the time-position constraint of the payload, the flight time updater design method is proposed to correct the error of time during the flight, which lays solid foundation for the subsequent flight phase, guaranteeing that the GEO satellite settles into the required position. Finally, simulation results indicate the high efficiency and accuracy and strong robustness of the proposed algorithm in different special situations including engine failure and time delay. The algorithm proposed in this paper has great development potential and application prospect in onboard trajectory optimization of SSTO launch missions and similar situations.

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Section: Introductionmentioning

confidence: 99%

A Convex Approach for Trajectory Optimization of Super-Synchronous-Transfer-Orbit Large Launch Systems with Time-Position Constraints

Sun

Chen

et al. 2022

International Journal of Aerospace Engineering

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“…Reference [18] generates the general energy management (GEM) method according to the relation between the arc and the central angle, in the process of which the velocity increment in the required velocity vector direction is controlled by the closed-loop commands. References [19,20] and [21] use the linear programming method to design an open-loop alternating attitude energy management algorithm (AEM) and spline energy management (SEM) guidance method, which further neutralizes the additional velocity component to strengthen the terminal constraints. Although these classical methods have been reliably and widely applied to the current launch vehicles, there are some limitations of the above methods in the solid rocket with burn-coast-burn flight mode such as the improvement of mission requirements, especially under the characteristics of fast response mission, because the closed-loop guidance method does not have multiterminal constraint capability, and the iterative guidance method is only applicable to the propulsion process.…”

Section: Introductionmentioning

confidence: 99%

Instantaneous Impact Point Guidance with Coast Arcs for Solid Rockets

Jia

Tong

2021

International Journal of Aerospace Engineering

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This paper proposed an analytical iterative guidance method with the desired instantaneous impact point constraint for solid rockets in “burn-coast-burn” trajectory mode. Solid rocket motors expect to remove the thrust termination mechanism to increase the structural strength and launch reliability, which induce new difficulties and challenges to the guidance problems. In terms of the “Hohmann transfer” principle, a pointing algorithm is deduced in depth to establish the theoretical relations among the ignition time, the required velocity vector, and the orbital element constraints and provides the analytical expression of the ignition time. Then, an analytic solution of the required velocity vector is derived based on orthogonal and nonorthogonal velocity vectors, and a complete guidance logic is used to solve the target orbit elements satisfying the desired instantaneous impact point. Finally, the application of the developed theoretical algorithm in this paper is conducted using a two-stage solid rocket. The proposed guidance method is verified by Monte Carlo simulations, and the testing results demonstrate the adaptability, strong robustness, and excellent performance for different desired impact point missions.

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“…Solid-propellant motors are the best choice for unguided rockets as they are simple, lightweight, cost-effective, can remain in storage for long periods and are easily able to deliver required thrust needed during the initial phase of flight (Pallone et al, 2018;Parhi et al, 2015;Xu and Zhang, 2018;Yılmaz et al, 2017). External ballistics is a very important topic in the design of solid-propellant rockets as this deals with ensuring required trajectories.…”

Section: Introductionmentioning

confidence: 99%

Short range rocket-target: research, development and implementation

Fedaravičius

Kilikevičius

Survila

et al. 2019

AEAT

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Purpose The purpose of this paper is to present the aerodynamic analysis and external ballistics modeling used in the development of a rocket-target for short range air defence missile systems. Design/methodology/approach A computational fluid dynamics (CFD) analysis of the airflow around the rocket-target was carried out to estimate the drag, which was needed to develop a mathematical model for external ballistics of the rocket-target. Field-experimental testing was conducted to compare the model results to the data obtained experimentally using various additional measurement techniques such as global positioning system (GPS) coordinates marking of the crash and launch sites, air defence surveillance radar tracking and installing equipment for telemetric data capturing and transmission. Findings Various ballistic parameters such as the velocity and trajectory of the rocket-target were obtained taking into account the CFD analysis results and internal ballistics data. The field-experimental testing showed a good agreement between the model results and the results obtained by the experimental techniques. Practical implications The presented computational models and the experimental techniques could be used in future developments of similar aircraft. Originality/value This paper presents a research approach for developing a rocket-target. The results of the research were used as a basis for developing a rocket-target for short range air defence rocket systems. The developed rocket-target was successfully implemented in practice.

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Multi-constrained ascent guidance for solid propellant launch vehicles

Cited by 17 publications

References 6 publications

A Convex Approach for Trajectory Optimization of Super-Synchronous-Transfer-Orbit Large Launch Systems with Time-Position Constraints

A Convex Approach for Trajectory Optimization of Super-Synchronous-Transfer-Orbit Large Launch Systems with Time-Position Constraints

Instantaneous Impact Point Guidance with Coast Arcs for Solid Rockets

Short range rocket-target: research, development and implementation

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