Digital adaptive control of a winged rocket applicable to abort flight

Shimozawa, Tomoaki; Sagara, Shinichi

doi:10.1007/s10015-011-0947-3

Cited by 3 publications

(3 citation statements)

References 5 publications

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“…From eq. ( 10 ), an manipulated variable u can be calculated from the r th order derivative of controlled variable by ( 12 ) control command can be generated using eq. ( 13 ) below.…”

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

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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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“…From eq. ( 10 ), an manipulated variable u can be calculated from the r th order derivative of controlled variable by ( 12 ) control command can be generated using eq. ( 13 ) below.…”

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

“…Therefore, most conventional research evaluates flight simulation results or linear stability analyses with a short-period model based on linearized motion equations. 3,4) The flight simulation results are meaningful, but they cannot ensure rigorous stability. Since very little research has focused on the stability of DI, it is important to study the stability of the DI control law on a nonlinear system.…”

Section: Introductionmentioning

confidence: 99%

Stability Analysis of Nonlinear Dynamic Inversion Controller Applied to Winged Rocket

Yamasaki

Yonemoto

Itakura

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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Space transportation systems have recently become an active area of development all over the world. Future reusable space transportation systems must possess good stability performance to compensate for the variations in flight conditions. One of the key technologies used for the development of a high performance controller for nonlinear dynamics systems is a dynamic inversion that transforms a nonlinear system into a linear one with pseudo inputs and outputs. It is quite an effective method to control nonlinear systems, and justifies the reason why many advanced aerospace vehicles employ a dynamic inversion controller. In this paper, vector analysis, state trajectory, Lyapunov exponent, and time series analyses results of the Proportional-Derivative (PD) and Dynamic Inversion (DI) control laws will be compared.

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“…A very robust control system is required for a reusable space transportation system that can be used in a wide range of flight environments and for subsonic and hypersonic speeds. For this purpose, WIRES#014 employs H Control in the ascent phase and Adaptive Control 5) in the gliding phase.…”

Section: Introductionmentioning

confidence: 99%

Development and Ground Combustion Test of a Subscale Reusable Winged Rocket

Itakura

Sasaki

Miyamoto

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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is developing a fully reusable sounding rocket named WIRES (WInged REusable Sounding rocket). The winged rocket incorporates many novel technologies, including a full composite structure and a navigation, guidance, and control system. It is also equipped with an innovative hybrid rocket engine named CAMUI (CAscaded MUltistage Impinging-jet). In such a complex rocket, system integration is difficult to achieve and innovation is imperative. The laboratory is therefore also developing a subscale model of the rocket named WIRES#014 to assess the new navigation, guidance, and control system. This paper describes the procedure and results of a trial and error approach, comprising three ground combustion tests, to integrating the systems of the rocket. In the first and second try of the combustion test, the tests had some troubles mainly about ground support system and avionics. Authors eliminated these errors after the cause analysis; the third combustion test was finally succeeded.

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Digital adaptive control of a winged rocket applicable to abort flight

Cited by 3 publications

References 5 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.

Stability Analysis of Nonlinear Dynamic Inversion Controller Applied to Winged Rocket

Development and Ground Combustion Test of a Subscale Reusable Winged Rocket

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