On Relative Position Control between Two Spacecraft

Yamada, Katsuhiko; Yoshikawa, Shoji; Nishiyama, Takehiro

doi:10.1299/kikaic.70.2638

Cited by 2 publications

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“…Let us consider the minimization of the following L to maintain as constant a relative distance as possible (20) Here, Tp = 2'TT/nc-By differentiating L with io under the condition Xo = 0, Yo = 0, Zo = ° and equation (18), we obtain the equation…”

Section: Symmetry Of Trajectorymentioning

confidence: 99%

“…By differentiating L in equation (20) by to under the conditions Xo = 0, Yo = 0, Zo = 0, and equation (19) …”

Section: Casementioning

confidence: 99%

“…Here, we attempt to obtain the control forces fi that translate the state vector x(to) into x(tf) [20]. By using equation (53), the state vector x(t f ) is expressed as…”

Section: -Minimal Solutionmentioning

confidence: 99%

“…Next, let us attempt to realize the formation trajectory by a discrete impulse control of the deputy [20]. We define the reference trajectory of the deputy at time t as x(t).…”

Section: Control Of Formation Trajectorymentioning

confidence: 99%

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Spacecraft Formation Design and Control in Keplerian Elliptic Orbits

et al. 2011

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In this paper, formation flying between a chief spacecraft moving in an elliptic orbit and a deputy spacecraft is studied. First, by using a state transition matrix (STM) of the Tschauner-Hempel equations, which describe the relative motion between the chief and deputy spacecraft, two formation trajectories that suppress relative distance variations are obtained. These trajectories are extensions of an along-track formation and a general circular orbit wherein the chief spacecraft moves in a circular orbit. The effects of the 12 perturbation on the trajectories are considered in the initial conditions. Further, the solution of the formation reconfiguration that minimizes the ~-norm of the deputy control forces is derived. A control law that realizes the reconfiguration trajectory by using a finite number of impulses is also derived. Finally, numerical examples of the construction of the formation trajectories are shown.

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Section: Symmetry Of Trajectorymentioning

confidence: 99%

“…By differentiating L in equation (20) by to under the conditions Xo = 0, Yo = 0, Zo = 0, and equation (19) …”

Section: Casementioning

confidence: 99%

“…Here, we attempt to obtain the control forces fi that translate the state vector x(to) into x(tf) [20]. By using equation (53), the state vector x(t f ) is expressed as…”

Section: -Minimal Solutionmentioning

confidence: 99%

“…Next, let us attempt to realize the formation trajectory by a discrete impulse control of the deputy [20]. We define the reference trajectory of the deputy at time t as x(t).…”

Section: Control Of Formation Trajectorymentioning

confidence: 99%

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Spacecraft Formation Design and Control in Keplerian Elliptic Orbits

et al. 2011

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Relative Position Change of Spacecraft During Formation Flight by Two Impulses (Second Report: Decrease in Formation Size)

Yokoyama

Yamada

Jikuya

2009

JSDD

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This paper proposes a basic method for designing a formation flight using Hill's equations of motion. This method involves a trajectory design for minimum fuel consumption during relative position change of spacecraft controlled by two impulses. The condition for minimum fuel consumption when the formation size is increased has already been examined. In this study, we consider the optimization problem to obtain the time and phase of the second impulse when the phase of the first impulse is given, during the decrease in formation size. In contrast to the optimum condition examined earlier, the optimum condition in this case is complicated. We have described the procedure to obtain the optimal solution. The results of our study show that the optimum condition determined previously is applicable to calculate the optimal cost in many simulation cases, whereas the new optimum condition is helpful to compensate the difference between them.

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On Relative Position Control between Two Spacecraft

Cited by 2 publications

References 0 publications

Spacecraft Formation Design and Control in Keplerian Elliptic Orbits

Spacecraft Formation Design and Control in Keplerian Elliptic Orbits

Relative Position Change of Spacecraft During Formation Flight by Two Impulses (Second Report: Decrease in Formation Size)

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