Flight Control System Using Backstepping Method for Space Transportation System

Abe, Akio; Shimada, Yusuke

doi:10.2322/tastj.10.pd_85

Cited by 4 publications

(5 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…From eqs. ( 16 ), ( 17 ), and ( 20 ) and the DI method explained in the previous section, command in each hierarchy is obtained by the following equation.…”

Section: Hierarchal Dynamic Inversion Methodology:-dynamic Inversion mentioning

confidence: 99%

Stability Analysis of Nonlinear Control Using Hierarchical Dynamic Inversion for a Winged Rocket.

Yamasaki¹,

Yonemoto²,

Fujikawa³

2017

IJAR

View full text Add to dashboard Cite

This paper presents stability analysis and time response evaluation of nonlinear control based on the hierarchy Dynamic Inversion (DI) and the block strict-feedback form, assuming the application to a winged rocket vehicle. Such vehicles have a wide range of flight conditions, and the associated change in aerodynamic characteristics during the flight leads to highly nonlinear dynamics. Whereas DI theory can cancel the nonlinear dynamics and linearize the input and output maps, it becomes troublesome to construct the control law when a system has high relative degree between the input and output maps. DI theory combined with time-scale separation, on the other hand, can provide a simple control law at the expense of strict linearization, and it has been one of the effective control methods for nonlinear system. However, there is a difficulty in evaluating the stability of such a control law. In order to solve these problems, the hierarchical DI method in the block strict-feedback form is investigated in this paper. This methodology is advantageous in that the control law is simple and its stability can be analyzed via classical eigenvalue analysis. The developed technique is applied to an experimental winged rocket vehicle whose dynamics consist of hierarchical structures of vehicle dynamics and actuator dynamics, and its validity is demonstrated via numerical simulations. …………………………………………………………………………………………………….... Introduction:-In recent years, reusable launch vehicles have been researched and developed around the world in order to reduce the space transportation cost and to facilitate the space development. Among possible concepts of future space transportation system, s winged-type vehicle is advantageous from its reusability, operability, and abort capability. The dynamics of such a vehicle is highly nonlinear, because the aerodynamic characteristics dynamically change along its flight profile. For example, in suborbital flight, flight sequence contains powered-ascent, coasting, apogee flight, reentry, gliding, and landing, where dynamic pressure and Mach number undergo drastic changes. Therefore, there is an increasing demand in developing nonlinear control methodologies for future space transportation system. This paper focuses on the development of dynamic inversion (DI) theory for nonlinear control. DI theory is a control technique that cancels nonlinear dynamics of the system and realizes desirable dynamics via algebraic transformation 1-3) ． Using DI theory, however, it becomes troublesome to construct and implement the control law

show abstract

“…From eqs. ( 16 ), ( 17 ), and ( 20 ) and the DI method explained in the previous section, command in each hierarchy is obtained by the following equation.…”

Section: Hierarchal Dynamic Inversion Methodology:-dynamic Inversion mentioning

confidence: 99%

Stability Analysis of Nonlinear Control Using Hierarchical Dynamic Inversion for a Winged Rocket.

Yamasaki¹,

Yonemoto²,

Fujikawa³

2017

IJAR

View full text Add to dashboard Cite

show abstract

“…In the simulation presented later, the vehicle is shown to function in accordance with the adopted constraints by minimizing the acceleration and adjusting the flight time. [9][10][11][12][13] This section presents the design of the constrained adaptive backstepping control system for the attitude controller based on the state equations given by Eqs. (2) …”

Section: Guidance Systemmentioning

confidence: 99%

“…9,10) The stability of the entire system is thereby guaranteed by eliminating interference based on a backstepping controller. Because this method is an extension of feedback linearization combined with time-scale separation, it shares the above-mentioned advantages.…”

Section: Introductionmentioning

confidence: 99%

Constrained Adaptive Backstepping Control for Re-entry Vehicle

Kanehira

Abe

Sasa

2016

AEROSPACE TECHNOLOGY JAPAN

Self Cite

View full text Add to dashboard Cite

This paper proposes a new guidance and control system for a re-entry vehicle. The vehicle flying through an extensive flight region can be expressed as a nonlinear system which has uncertain dynamic characteristics and physical constraints. In addition, to address considerations of mission abort and changes of landing site during a space transportation mission, sequentially generating flight trajectories from the guidance system is desirable. Therefore, in this study, we attempt to derive an online trajectory generation system by solving a two-point boundary value problem using the concept of flatness as an extension of exact linearization. Moreover, an attitude control system is designed to track a command signal corresponding to a generated trajectory. The system is employed as a constrained adaptive backstepping control method that can accommodate uncertain dynamic characteristics and physical constraints of a re-entry vehicle. The numerical simulations verify the effectiveness of the proposed guidance and control system.

show abstract

“…As a measure against this problem, the authors have proposed a control system in which a newly designed disturbance observer is used in combination with a backstepping method, making it possible to guarantee the stability of the entire system, including an estimation mechanism and a control system. 22) Since the proposed system does not require the assumption of being bound to unknown signals, it is possible to ensure the stability of the entire system without making the control system complicated, while still achieving the desired control performance. The application of the proposed method, however, has been limited to the problem of designing a control system regarding the bank angle, the angle of attack, the sideslip angle (hereinafter referred to as wind axis angles), and the angular velocity of the vehicle.…”

Section: Introductionmentioning

confidence: 99%

Design of Flight Control System Based on Adaptive Backstepping Method for Space Transportation System

Abe¹,

Iwamoto²,

Shimada³

2013

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCE

Self Cite

View full text Add to dashboard Cite

This paper presents a new guidance and control system based on an adaptive backstepping method for a space transportation system. In recent years, many studies of flight control systems using feedback linearization combined with timescale separation have been carried out. Since this type of control system does not depend on the design points along a predetermined trajectory, the designed system can be applied to an extensive flight region. However, in this method, control performance tends to deteriorate with changes in the control gains and parameters because it is difficult to guarantee the stability of the system. Additionally, since it is not easy to obtain prior knowledge about disturbances and aerodynamic characteristics, an estimation mechanism must be added to the system. To solve this problem, we propose an adaptive flight control system combining feedback linearization, the backstepping method, and disturbance observers. A disturbance observer is effective for estimating the effect of extraneous signals. In the proposed system, by appropriately redesigning the disturbance observer, it becomes possible to guarantee the stability of the entire system, including the estimation mechanism. Numerical simulations were performed to verify the effectiveness and robustness of the proposed system when applied to an automatic landing problem.

show abstract

Flight Control System Using Backstepping Method for Space Transportation System

Cited by 4 publications

References 11 publications

Stability Analysis of Nonlinear Control Using Hierarchical Dynamic Inversion for a Winged Rocket.

Stability Analysis of Nonlinear Control Using Hierarchical Dynamic Inversion for a Winged Rocket.

Constrained Adaptive Backstepping Control for Re-entry Vehicle

Design of Flight Control System Based on Adaptive Backstepping Method for Space Transportation System

Contact Info

Product

Resources

About