Control Design for the Autonomous Horizontal Takeoff Phase of the Reusable Launch Vehicles

Shuaibin An,Jian Guo,Kai Liu,Yazhuo Fan,Zhiyong She

doi:10.1109/access.2020.3001186

Shuaibin An, Jian Guo + Show 3 more

Open Access

https://doi.org/10.1109/access.2020.3001186

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Journal: IEEE Access	Publication Date: Jan 1, 2020
Citations: 4	License type: CC BY 4.0

Affiliation: Dalian University of Technology

Abstract

The control system design for the reusable launch vehicles (RLVs), especially in the autonomous horizontal takeoff phase, is a highly challenging task. Significant issues arise due to the high nonlinearity, large uncertainties of aerodynamic coefficients as well as strong coupling among axes of the airframe. This paper studies autonomous takeoff control problem of the RLVs by the means of trajectory linearization control (TLC) and model predictive control (MPC) theory. The six degree of freedom dynamic model is firstly established, and the flight strategy of takeoff and climb stage is provided through the characteristic analysis of RLVs. Furthermore, the guidance law for the climbing phase is proposed via the TLC method against the high nonlinearity, and a speed based gain-schedule strategy is given under the consideration of both aerodynamic force and friction force. In order to eliminate the ground effect interference, an improved model predictive control approach is presented by introducing the online parameter estimation of the ground effect interaction coefficient, and a coupled model predictive controller is designed by introducing the feedback of sideslip angle into the roll control channel to eliminate the coupling effect. Finally, the performance of the design method for autonomous takeoff control of RLVs is demonstrated through the comparison simulation analysis.

Highlights

Aiming at the development of more affordable, convenient and reliable access to space, the reusable launch vehicles (RLVs) [1]–[9], such as space rider [10] and Skylon [11] have become a hot spot and received sustained attention during the last few decades
In order to meet the needs of high and low-speed, the design of a combined power engine is usually poor at subsonic speeds, so the horizontal takeoff and landing process will face the problem of insufficient lift performance and thrust performance, and the autonomous takeoff control technology will face new challenges
2) MPC MODELING Considering the strong coupling effect between the yaw channel and roll channel, a coupled model predictive controller is designed by introducing the feedback of sideslip angle into the roll control channel to eliminate the coupling effect

Summary

Introduction

Aiming at the development of more affordable, convenient and reliable access to space, the reusable launch vehicles (RLVs) [1]–[9], such as space rider [10] and Skylon [11] have become a hot spot and received sustained attention during the last few decades. Compared with the hypersonic cruise vehicle [12], [13], the RLVs should adapt to the near space flight environment, and meet the technical requirements of the airport Horizontal takeoff and landing. The small wing area of the aircraft is beneficial to reduce the drag when the aircraft is flying at high speed. Compared with aircraft such as fighter and airliner, its low-speed lift performance is poor. In order to meet the needs of high and low-speed, the design of a combined power engine is usually poor at subsonic speeds, so the horizontal takeoff and landing process will face the problem of insufficient lift performance and thrust performance, and the autonomous takeoff control technology will face new challenges

Methods

Results

Conclusion