Performance improvement-oriented reentry attitude control for reusable launch vehicles with overload constraint

Gu, Xiyu; Guo, Jianguo; Guo, Zhishan; Qiu, Likuan; Zhao, Yang; Wang, Guoqing

doi:10.1016/j.isatra.2021.10.034

Cited by 10 publications

(5 citation statements)

References 28 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Therefore, t f = ∞. Note that the work [24] also employs funnel control techniques to solve the tracking problem with prescribed transient behavior for RVs. However, the controller there requires additional design parameters which need to be sufficiently large, but it is not known a priori how large they must be chosen.…”

Section: Proofmentioning

confidence: 99%

“…If the error tends towards the funnel boundary, the gain increases so that the error is kept inside the performance funnel. Both PPC and FC have already been investigated for the control algorithm design for RVs with a focus on the transient performance [24]- [26]. Notice that almost all funnel boundaries selected in works on funnel control are monotonically decreasing functions, although the theory guarantees the stability of the closed-loop system for a vast variety of non-monotonic funnel boundaries.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint

Zheng-yu

Wang²,

Qian³

et al. 2020

西北工业大学学报

View full text Add to dashboard Cite

A distributed multi-missile cooperative guidance law based on the finite time theory is proposed to solve the terminal guidance problem of three-dimensional multi-missiles cooperative interception of large maneuvering target. According to the finite time consistency theory, an adaptive guidance law based on the integral sliding mode is designed to ensure that all missiles can reach the target at the same time in the terminal guidance process. The longitudinal and lateral acceleration of the line of sight are based on the guidance law of the fast terminal sliding mode surface. The terminal attack angle is constrained, so that the terminal attack Angle can reach the expected value in finite time. The simulation results show that the designed guidance law can achieve the cooperative attack on the maneuvering targets.

show abstract

Section: Proofmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint

Zheng-yu

Wang²,

Qian³

et al. 2020

西北工业大学学报

View full text Add to dashboard Cite

show abstract

“…With the improvement of technology and the rapid growth of space transportation demand, reusable launch vehicle (RLV), as a cheap and convenient delivery vehicle travelling between outer space and earth, has always been the unremitting pursuit of aerospace technology development for various countries (Gu et al, 2022;Li and Hu, 2018;Su et al, 2021). Compared with expendable launch vehicles, RLV has a shorter prefiring cycle and requires more simple maintenance, which greatly reduces the launch cost (Li et al, 2020;Tian et al, 2015).…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A novel predefined performance barrier function based adaptive sliding mode control method for RLV under mismatched disturbance

Wang,

Yang,

Bai

2024

AEAT

View full text Add to dashboard Cite

Purpose This paper aims to present a novel adaptive sliding mode control (ASMC) method based on the predefined performance barrier function for reusable launch vehicle under attitude constraints and mismatched disturbances. Design/methodology/approach A novel ASMC based on barrier function is adopted to deal with matched and mismatched disturbances. The upper bounds of the disturbances are not required to be known in advance. Meanwhile, a predefined performance function (PPF) with prescribed convergence time is used to adjust the boundary of the barrier function. The transient performance, including the overshoot, convergence rate and settling time, as well as the steady-state performance of the attitude tracking error are retained in the predetermined region under the barrier function and PPF. The stability of the proposed control method is analyzed via Lyapunov method. Findings In contrast to conventional adaptive back-stepping methods, the proposed method is comparatively simple and effective which does not need to disassemble the control system into multiple first-order systems. The proposed barrier function based on PPF can adjust not only the switching gain in an adaptive way but also the convergence time and steady-state error. And the efficiency of the proposed method is illustrated by conducting numerical simulations. Originality/value A novel barrier function based ASMC method is proposed to fit in the amplitude of the mismatched and matched disturbances. The transient and steady-state performance of attitude tracking error can be selected as prior control parameters.

show abstract

“…The retirement of space shuttle does not mean that people all over the world stop the research on reusable spacecraft with both aviation and aerospace capabilities. In order to find an economical and safe space shuttle or system, Britain, the United States, Germany, France, Japan, and other countries have launched reusable space shuttle transportation system schemes, and Aerospaceplane research has quietly emerged [12][13][14][15]. It is generally believed that the main difference between the Aerospaceplane and the space shuttle is that the space shuttle is an aircraft that takes off vertically like a rocket and lands horizontally like a plane.…”

Section: Introductionmentioning

confidence: 99%

Impact Analysis of Different Trajectory Shapes on Optimization Based on Original Natural Algorithm

Chen,

Nan,

2024

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

In this paper, the reentry phase of the Aerospaceplane is taken as the research object, and the performance parameters of the reusable rocket of a private company are analyzed. Aiming at the guidance and control scheme of the spacecraft returning to the reentry trajectory in the real environment, the original natural algorithm is optimized by considering various reentry flight constraints, and the improved original natural algorithm is used to optimize the reentry trajectory of the Aerospaceplane. We obtained two types of reentry trajectories in the presence of large flight-restricted areas, the “S-type” trajectory and the “spiral-type” trajectory, and obtained data on various influencing factors. The results showed that the basic state parameters of the spiral trajectory optimized using the improved original natural algorithm after adding constraints met the constraint conditions. The aerodynamic heating rate and overload of the spiral reentry trajectory were to some extent greater than those of the S-type trajectory. Under the increasingly stringent requirements of the aerospace environment, new requirements were put forward for the thermal protection system to meet the wider environmental situation. This paper uses the improved original natural algorithm for the first time and applies it to the field of aerospace reentry and entry and adds more constraints to this algorithm for computation. Besides, for the first time, the macroscopic nature of trajectory types is used as a comparative element for parameter comparison, providing a reference basis for selecting trajectory optimization directions from the macroscopic perspective of trajectory types.

show abstract

Performance improvement-oriented reentry attitude control for reusable launch vehicles with overload constraint

Cited by 10 publications

References 28 publications

Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint

Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint

A novel predefined performance barrier function based adaptive sliding mode control method for RLV under mismatched disturbance

Impact Analysis of Different Trajectory Shapes on Optimization Based on Original Natural Algorithm

Contact Info

Product

Resources

About