Performance limitations in trajectory tracking control for air-breathing hypersonic vehicles

Chen, Boyi; Liu, Yanbin; Shen, Huiyong; Hao, Lei; Lu, Yuping

doi:10.1016/j.cja.2018.03.023

Cited by 23 publications

(5 citation statements)

References 25 publications

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“…For discussing the efficiency of our method, we set a max range trajectory example based on the PRAHV as described by equations ( 5)∼ (10) in Section II. The whole trajectory of PRAHV, an air-launched vehicle powered by a common rocket, starts at an initial altitude and an initial velocity, and then performs an unpowered maneuver after the fuel has burned out.…”

Section: Resultsmentioning

confidence: 99%

“…Moreover, other path constraints are considered, as follows. (10) where the N load is the vehicle overload, expressed as N load = Lift 2 + Drag 2 /mg, which is constrained by a userspecified parameter N maxload . The q w is the heat flow at the stagnation point of the vehicle and should be smaller than the value of Q max .…”

Section: B the Whole Trajectory Of Discontinuous Aerodynamicsmentioning

confidence: 99%

“…As a consequence, the research significance of trajectory for the aforementioned vehicles is captured in two aspects. First, under the condition of ensuring the controllability of the vehicle and the accessibility of the design target [10], the optimal trajectory of the invasion capability maximization is studied, which includes the maximum range [11], the minimum fuel [12], threat avoidance [13,14], etc. On the contrary, it is still of great significance for air defense systems to estimate the trajectory of these vehicles in the aspect of interception [8,15].…”

Section: Introductionmentioning

confidence: 99%

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Constraints Maintaining Mesh Refinement Method for Solving Whole Trajectory of Discontinuous Aerodynamics

Huang,

Wang,

Qiao

et al. 2023

IEEE Access

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Solving trajectories of multi-phase dynamic advanced vehicles is difficult due to the coexistence of discontinuous aerodynamics, long-range and multi-peak features. Despite traditional phase-by-phase solving method for trajectory is expressive and easy to optimize, it loses global optimality to some extent and the state estimation between phases is cumbersome. In contrast, an all-in-one solution method for the whole trajectory can carry out global search and avoid the inter-phase state estimation, but the expression of the problem formulation is more complicated, and it is difficult to converge to a feasible solution. In this paper, we formulate the whole trajectory solving problem based on a representative vehicle and propose a constraints maintaining mesh refinement method based on the pseudo-spectral method to solve the whole trajectory allin-one. First, the proposed method presets a knot on the trajectory to construct an optimal control problem with a two-phase dynamic constraint, which maintains continuity of variables between the discontinuous aerodynamics. Second, ph-refinement is used to deal with long-range and multi-peak features throughout the trajectory. Third, to make mesh refinement and iterative solution feasible under discontinuous aerodynamics, an interval extending operator is proposed to maintain the consistency of constraints during the process of mesh refinement. Finally, the effectiveness of the proposed method for solving the whole trajectory is verified by 7 comparison experiments. The results show that the proposed method can effectively handle the whole trajectory problem of discontinuous aerodynamics, as evidenced by feasibility, convergence, optimality, and superiority.INDEX TERMS hypersonic vehicles; optimal trajectory; mesh refinement; discontinuous aerodynamics

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Section: Resultsmentioning

confidence: 99%

Section: B the Whole Trajectory Of Discontinuous Aerodynamicsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Constraints Maintaining Mesh Refinement Method for Solving Whole Trajectory of Discontinuous Aerodynamics

Huang,

Wang,

Qiao

et al. 2023

IEEE Access

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“…During the flight, the slide angle is 0, and the trajectory is controlled through the angle of attack and roll angle. The simulation uses a trajectory with three degrees of freedom [46][47][48], and the state variables include velocity, path angle, deflection angle, vehicle position, and mass. The following basic assumptions are made for propulsion codes: (a) the earth's rotation and curvature are neglected; (b) the rotational motion caused by the moment of inertia is neglected; (c) the slide angle is 0; and (d) the aircraft is in transient equilibrium all the time:…”

Section: Trajectory Codesmentioning

confidence: 99%

Multifidelity Multidisciplinary Design Optimization of Integral Solid Propellant Ramjet Supersonic Cruise Vehicles

Sun

Yang

et al. 2019

International Journal of Aerospace Engineering

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Integral solid propellant ramjet (ISPR) supersonic cruise vehicles share the characteristic that they are highly integrated configurations. The traditional design of vehicles cannot achieve a balance between computational expense and accuracy. A multifidelity multidisciplinary design optimization (MDO) platform has been developed in this study. The focus of the platform is on ISPR supersonic cruise vehicles. Firstly, codes of discipline with different levels of fidelity (LoF) were established, such as geometry, aerodynamics, radar cross-section calculations, propulsion, mass, and trajectory discipline codes. Secondly, two MDO frameworks were constructed through discipline codes. A low LoF MDO framework is suitable for conceptual design, and a medium LoF MDO framework is suitable for preliminary design. Finally, taking the optimization problem with the minimum overall detection probability of flight trajectory as an example, the low LoF framework first explores the entire design space to achieve the mission requirements, and then, the medium LoF MDO framework accepts the low LoF framework optimization parameters. Hence, the optimization target is reached with more detailed parameters and higher fidelity. Additionally, an example for a solid propellant missile with minimum total mass is tested by the platform. The study results show that the multifidelity MDO framework not only exploits interactions between the disciplines but also improves the accuracy of optimization results and reduces the iteration time.

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“…Large flight envelopes [1], unstable longitudinal dynamics with input saturation [2], and environmental uncertainty [3] lead to a great of difficulty in flight control system design of hypersonic flight vehicles (HFV). Besides, tracking control for HFV with model uncertainties for prescribed performance is a challenging task [4].…”

Section: Introductionmentioning

confidence: 99%

Guardian Map Approach to Feasible Range of Static Stability Margin of Hypersonic Flight Vehicles with Input Saturation

Hao

Chen

Liu

et al. 2020

International Journal of Aerospace Engineering

Self Cite

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Static stability margin is a critical parameter in flight control design. The feasible range of it must cover the uncertainty through the flight. To reasonably identify the feasible range of static stability margin in advance, an approach based on guardian maps is proposed for flight control of hypersonic flight vehicles with input saturation. First, the model of hypersonic flight vehicle (HFV) is established as a parametric plant. Then, flying quality requirements for the closed-loop system are formulated as inequality constraints using guardian maps. Moreover, by using linear matrix inequality, the saturation of elevators is taken into account in the integrated control of attitude control. The prescribed minimum of static stability margin that ensures the flying quality of hypersonic flight vehicles with input saturation is obtained. Furthermore, from the prospective of integrated control, it is shown that the feasible range of static stability margin can be enlarged by changing aerodynamic characteristics. The effectiveness of the proposed approach is validated by numerical simulation.

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Performance limitations in trajectory tracking control for air-breathing hypersonic vehicles

Cited by 23 publications

References 25 publications

Constraints Maintaining Mesh Refinement Method for Solving Whole Trajectory of Discontinuous Aerodynamics

Constraints Maintaining Mesh Refinement Method for Solving Whole Trajectory of Discontinuous Aerodynamics

Multifidelity Multidisciplinary Design Optimization of Integral Solid Propellant Ramjet Supersonic Cruise Vehicles

Guardian Map Approach to Feasible Range of Static Stability Margin of Hypersonic Flight Vehicles with Input Saturation

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