Trajectory optimization for hypersonic boost‐glide missile considering aeroheating

Li, Yu; Cui, Naigang; Rong, Siyuan

doi:10.1108/00022660910926854

Cited by 20 publications

(12 citation statements)

References 12 publications

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“…The optimal control, launch and re-entry problem, is solved to find the optimal state vector and the corresponding control deflections that minimise the cost function, subject to the dynamic constraints of Equations (6)- (12), the initial and terminal flight path constraints of Equations (18) and (19), respectively, and the path constraints of Equation (20). The non-linearity in this optimal control problem is solved using an hp-adaptive method implemented in open source Gauss Pseudospectral Optimization Software (GPOPS) version 4.0.…”

Section: Methodsmentioning

confidence: 99%

“…Jorris (11) carried out trajectory optimisation of a CAV using waypoint and no-fly zone as a constraint. Li (12,13) carried out trajectory optimisation of a Hypersonic Boost-Glide (HBG) waverider CAV configuration by modelling the boost phase. He computed the foot print of the CAV boosted from a Minuteman III boost vehicle to a speed of approximately 6.5 km/s and a burn-out angle of nearly 0° under a constrained heat rate environment.…”

Section: Introductionmentioning

confidence: 99%

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Trajectory optimisation for a rocket-assisted hypersonic boost-glide vehicle

Rizvi

et al. 2017

Aeronaut. j.

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In this work, trajectory optimisation has been performed for a wing-body rocket assisted vehicle to compute the bestset of performance parameters including burn-out angle, angle-of-attack, bank-angle and throttle command that would result in optimal down-range and cross-range performance of the re-entry vehicle. An hp-adaptive Pseudospectral method has been used for the optimisation by combining the launch and rocket rocket-assisted re-entry stages. The purpose of the research is to compute optimal burn-out condition, angle-of-attack, bank-angle and optimal thrust segments that would maximise the down-range and cross-range performance of the hypersonic boost glide vehicle, under constrained heat rate environments. The variation of down-range/cross-range performance of rocket rocket-assisted hypersonic boost glide vehicle with bounds on diminishing heat rate has also been computed.

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Section: Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Trajectory optimisation for a rocket-assisted hypersonic boost-glide vehicle

Rizvi

et al. 2017

Aeronaut. j.

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“…There are path constraints [4][5][6][7] in the entry guidance, hence an accurate aerodynamic model is needed to calculate a correct trajectory.…”

Section: Introductionmentioning

confidence: 99%

Constrained predictor corrector entry guidance for common aero vehicle

Wang

Hua

et al. 2015

2015 34th Chinese Control Conference (CCC)

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The path constraints play determinative roles in the entry guidance, hence an aerodynamic model of Common Aero Vehicle (CAV) is established by means of CFD to facilitate the guidance. In the case that the attack angle profile is determined, the bank angle is the only parameter which can be used to control the trajectory in guidance. If the quasi-equilibrium glide condition (QEGC) is used, an entry flight corridor can be obtained by analyzing the path constraints in the entry guidance, and the corridor is transformed into the constraints of the bank angle for the convenience of designing the bank angle profile. Furthermore, a strong robust baseline predictor-corrector algorithm is presented to calculate the value of the bank angle in time. Simulations are provided to verify the effectiveness of the proposed method.

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“…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. 20 The trajectory optimization problem is treated as a boost phase followed by a glide phase and has been solved by the direct method using an NLP-based solver and direct shooting method. Recently, Zhang et al carried out trajectory optimization of a long range hypersonic glide vehicle subjected to terminal impact angle and time constraints.…”

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:

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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.

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Trajectory optimization for hypersonic boost‐glide missile considering aeroheating

Cited by 20 publications

References 12 publications

Trajectory optimisation for a rocket-assisted hypersonic boost-glide vehicle

Trajectory optimisation for a rocket-assisted hypersonic boost-glide vehicle

Constrained predictor corrector entry guidance for common aero vehicle

Atmospheric vehicle trajectory optimization with minimum dynamic pressure constraint

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