Maximum range trajectory optimization for a boost-glide vehicle using adaptive mesh refinement pseudospectral methods

Qiu, Wenjie; Jia, Qingzhong; Meng, Xiuyun; Sun, Yibo

doi:10.1177/0954410016649208

Cited by 5 publications

(4 citation statements)

References 16 publications

(23 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Trajectory optimization is an optimal control problem and is realized by a direct transcription method called hp-adaptive Radau pseudo-spectral method [38][39][40] in this paper. In this method, Legendre-Gauss-Radau collection points and Gaussian quadrature implicit integration are used to transform the continuous-time optimal control problem into a nonlinear programming problem (NLP).…”

Section: Numerical Calculation Methodsmentioning

confidence: 99%

Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle

Zhang

Wang

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The liquid oxygen/methane staged cycle liquid-rocket engine is one of the most potential rocket engines in the future for its higher performance, higher fuel density and reusable capacity. Two working states of this liquid-rocket engine named as full-load state and half-load state are defined in this paper. Based on this liquid-rocket engine, a dual-rocket-basedcombined-cycle propulsion system with liquid oxygen /air/methane as propellants is therefore proposed. The dualrocket-based-combined-cycle system has then five working modes: the hybrid mode, pure ejector mode, ramjet mode, scramjet mode and pure rocket mode. In hybrid mode, the booster and ejector rockets driven by the full-load liquidrocket engine work together with the purpose of reducing thrust demand on ejector rocket. In scramjet mode, the fuelrich burned hot gas generated by the half-load liquid-rocket engine is used as fuel, which is helpful to reduce the technical difficulty of scramjet in hypersonic speed. The five working modes of dual-rocket-based-combined-cycle are highly integrated based on the full-or half-load state of the liquid oxygen/methane staged cycle liquid-rocket engine, and the unified single type fuel of liquid methane is adopted for the whole modes. Then a preliminary design of a horizontal takeoff two-stage-to-orbit launch vehicle is conducted based on the dual-rocket-based-combined-cycle propulsion system. Under an averaged baseline thrust and specific impulse, the launch trajectory to reach a low Earth orbit at 100 km is optimized via the pseudo-spectral method subject to maximizing the payload mass. It is shown that the two-stage-to-orbit vehicle based on the dual-rocket-based-combined-cycle can achieve the payload mass fraction of 0.0469 and 0.0576 for polar mission and equatorial mission, respectively. Conclusively, insights gained in this paper can be usefully applied to a more detailed design of the dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle.

show abstract

Section: Numerical Calculation Methodsmentioning

confidence: 99%

Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle

Zhang

Wang

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…R 2p . This system of dynamical equations beside the initial, boundary and transversality conditions in equations (1), (2) and (8), and/or conditions in equation 9, and the switching condition in equation 12, forms a HBVP which is expressed by…”

Section: Problem Statementmentioning

confidence: 99%

“…In particular, a class of switching optimal control problems, in which control function jumps from one boundary to another and stands in the form of a linear function in the cost functional and the dynamical equations, is considered as a target problem. This class of optimal control problems, which is usually named as bangbang optimal control problems, arises in many aspects of aerospace engineering such as trajectory design of a spacecraft, 1,2 rest-to-rest and rapid attitude maneuvers of a spacecraft. [3][4][5] Regardless of having a simple structure in optimal control, the numerical solution of this family of optimal control problems can be extremely difficult, especially, when any basic information about the optimal control structure is not available.…”

Section: Introductionmentioning

confidence: 99%

A modified pseudospectral method for indirect solving a class of switching optimal control problems

Mehrpouya

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

In the present paper, an efficient pseudospectral method for solving the Hamiltonian boundary value problems arising from a class of switching optimal control problems is presented. For this purpose, based on the Pontryagin's minimum principle, the first-order necessary conditions of optimality are derived. Then, by partitioning the time interval related to the problem under study into some subintervals, the states (and costates) and control functions are approximated on each subintervals with piecewise interpolating polynomials based on Legendre–Gauss–Radau points and a piecewise constant function, respectively. As a result, solution of the problem is turned into solution of a number of algebraic equations, in which the values of the states (and costates) and control functions at Legendre–Gauss–Radau points as well as switching and terminal points are allowed to be unknown. Numerical examples are presented at the end to show the efficiency of the proposed method.

show abstract

“…In Qiu et al., an optimal scheme of a multiphase maximum down range trajectory optimization problem based on adaptive mesh refinement pseudospectral methods for a boost–glide vehicle is proposed. 19 An optimal strategy of the cost function based on dynamic programming has been presented to search free interior points more accurately. Range optimization of an HBGV under near-real condition is addressed in Li et al., wherein the heat rate constraint is imposed as an in-flight constraint along with others to check capability of wall cooling materials.…”

Section: Introductionmentioning

confidence: 99%

Atmospheric vehicle trajectory optimization with minimum dynamic pressure constraint

Kumar

Sarkar

Mangrulkar

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

In this work, a trajectory optimization formulation for hypersonic boost-glide class vehicles to achieve maximum range under various in-flight and terminal constraints is proposed. While most of the published literature has considered maximum dynamic pressure as a constraint, the requirement of a certain minimum dynamic pressure has been addressed in this formulation to ensure aerodynamic controllability throughout the flight envelope for various ranges. The minimum dynamic pressure constraint is imposed as an in-flight inequality constraint and is achieved through a penalty function approach by casting it as a differential equation. Simulations are carried out, and the results are analyzed and presented to demonstrate the efficacy of the proposed formulation.

show abstract

Maximum range trajectory optimization for a boost-glide vehicle using adaptive mesh refinement pseudospectral methods

Cited by 5 publications

References 16 publications

Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle

Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle

A modified pseudospectral method for indirect solving a class of switching optimal control problems

Atmospheric vehicle trajectory optimization with minimum dynamic pressure constraint

Contact Info

Product

Resources

About