Preliminary Design of Winged Experimental Rocket by University Consortium

Wakita, Masashi; Yonemoto, Koichi; Akiyama, T.; Aso, Shigeru; Kohsetsu, Yuji; Nagata, Harunori

doi:10.2322/tstj.7.tg_21

Cited by 3 publications

(5 citation statements)

References 2 publications

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“…Block diagrams of a system in block-strict feedback form with controller And also, equations of each subsystem of block-strict feedback form are eqs. ( 18 ), and ( 19 )…”

Section: Hierarchal Dynamic Inversion Methodology:-dynamic Inversion mentioning

confidence: 99%

“…denote the values at a specific point ( 19 ) The relative degree of the ith hierarchy i r is defined as follows.…”

Section: Hierarchal Dynamic Inversion Methodology:-dynamic Inversion mentioning

confidence: 99%

“…Vehicle model utilized in this paper is that of WIRES#015 (WInged REusable Sounding rocket), which is an experimental winged rocket developed in Kyushu Institute of Technology [19][20][21][22][23] . Figure 1 and Table 1 show the overview and specifications of WIRES#015, respectively.…”

Section: …………………………………………………………………………………………………… Introduction:-mentioning

confidence: 99%

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

Yamasaki¹,

Yonemoto²,

Fujikawa³

2017

IJAR

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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

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“…Block diagrams of a system in block-strict feedback form with controller And also, equations of each subsystem of block-strict feedback form are eqs. ( 18 ), and ( 19 )…”

Section: Hierarchal Dynamic Inversion Methodology:-dynamic Inversion mentioning

confidence: 99%

“…denote the values at a specific point ( 19 ) The relative degree of the ith hierarchy i r is defined as follows.…”

Section: Hierarchal Dynamic Inversion Methodology:-dynamic Inversion mentioning

confidence: 99%

Section: …………………………………………………………………………………………………… Introduction:-mentioning

confidence: 99%

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

Yamasaki¹,

Yonemoto²,

Fujikawa³

2017

IJAR

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“…The PD (Proportional and Derivative) controller is used for controlling the parafoil line. The equation of PD controller is shown below in equation(1)and(2).…”

mentioning

confidence: 99%

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mentioning

confidence: 99%

Recent Developments of Experimental Winged Rocket: Autonomous Guidance and Control Demonstration Using Parafoil

Surendra

Yonemoto

Matsumoto

et al. 2015

Procedia Engineering

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Since 2005, Space system laboratory of Kyushu Institute of Technology has been studying experimental unmanned rockets called WIRES (WInged REusable Sounding rocket) [1][2][3]. WIRES are test beds and demonstration platforms for future reusable space transportation system to reduce space transportation cost. In this paper, design, development, ground combustion test and flight test of the winged rocket named WIRES#012IA are presented. WIRES#012IA aims to demonstrate autonomous guidance and control using parafoil.

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Digital adaptive control of a winged rocket applicable to abort flight

Shimozawa

Sagara

2011

Artif Life Robotics

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Preliminary Design of Winged Experimental Rocket by University Consortium

Cited by 3 publications

References 2 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.

Recent Developments of Experimental Winged Rocket: Autonomous Guidance and Control Demonstration Using Parafoil

Digital adaptive control of a winged rocket applicable to abort flight

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