Novel Expressions of Equations of Relative Motion and Control in Keplerian Orbits

Yoon, Hyungjoo; Agrawal, Brij N.

doi:10.2514/1.38210

Cited by 36 publications

(26 citation statements)

References 17 publications

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“…Remark While the derivation and form of show the expression similar to those in the works of Yoon et al the definition of LOS coordinate frame associated with ECQ coordinate frame is different and the origin is located on the chaser, thus the expression of gravity difference term

normalΔ g^{l}

is different and corresponding relative motion equation look similar but in fact differ in detail. Moreover, the computation of spherical coordinates

bold-italicq = {([], ρ, β, ε)}^{T}

does not need the orbit state of target and can be measured directly via the suite of onboard sensor, thus the LOS‐based relative motion model has the advantages that it can be applied to the noncooperative target, even the maneuvering target.…”

Section: Spacecraft Dynamics and Problem Formulationmentioning

confidence: 58%

“…Remark Although some research works have been done based on the primary form of LOS‐based relative motion model, the system does not satisfy the physical property . With the transformation matrix

bold-italicB ((), q)

, the transformed system satisfies the physical property , which can be viewed as a matrix expression of energy conservation and is very useful for the design of control law …”

Section: Spacecraft Dynamics and Problem Formulationmentioning

confidence: 99%

See 1 more Smart Citation

Adaptive sliding‐mode control for spacecraft relative position tracking with maneuvering target

Zhang

Duan

2018

Intl J Robust & Nonlinear

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Summary This paper considers the adaptive sliding‐mode control (ASMC) problem of spacecraft relative position tracking with maneuvering target in the presence of external disturbance and unknown mass property. Integrated with the spacecraft absolute orbit dynamics, the line‐of‐sight–based relative position motion model is established; further, the problem is formulated in the general mechanical second‐order form with unknown mass parameter and matching disturbance, which makes it convenient to use some useful physical properties in the control law design. As a stepping‐stone, the traditional ASMC law is proposed without prior knowledge of uncertainty/disturbance bound. Then, incorporated with the smooth‐projection algorithm and equivalent‐control‐dependent gain method, the modified control law is proposed, which can force the mass estimate to remain in a desired domain and efficiently overcome the drawback of the overestimation of the disturbance in the traditional ASMC law. Within the Lyapunov frame, the bounded stability is presented in the real case that the sign function is replaced by the hyperbolic tangent function. Finally, three different simulation cases are presented to show fine performance of the modified ASMC law.

show abstract

normalΔ g^{l}

is different and corresponding relative motion equation look similar but in fact differ in detail. Moreover, the computation of spherical coordinates

bold-italicq = {([], ρ, β, ε)}^{T}

Section: Spacecraft Dynamics and Problem Formulationmentioning

confidence: 58%

bold-italicB ((), q)

, the transformed system satisfies the physical property , which can be viewed as a matrix expression of energy conservation and is very useful for the design of control law …”

Section: Spacecraft Dynamics and Problem Formulationmentioning

confidence: 99%

Adaptive sliding‐mode control for spacecraft relative position tracking with maneuvering target

Zhang

Duan

2018

Intl J Robust & Nonlinear

View full text Add to dashboard Cite

show abstract

“…Therefore, more accurate models, usually nonlinear, are necessary. Different nonlinear techniques have been applied to control the relative motion, such as adaptive control [3], sliding mode [4] and computed-torque [5]. However, these solutions do not satisfy any optimality condition.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear H-infinity control of relative motion in space via the state-dependent Riccati equations

Franzini

Innocenti

2015

2015 54th IEEE Conference on Decision and Control (CDC)

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Relative guidance algorithms for space applications were identified by several space agencies as an enabling technology for future missions development. Whenever two or more space vehicles must coordinate their motion, or a terminal rendezvous has to be performed, a robust control of the relative motion occurring between the objects is necessary. Control must guarantee operation safety, and minimize fuel consumption, since refueling operations are currently too expensive. In this context, the paper proposes an extended linearization technique to design a nonlinear H-infinity controller for the relative motion. The developed controller is designed to minimize propellant consumption and to attenuate disturbances due to typical perturbations of low Earth orbits, such as atmospheric drag and J2 perturbation. Terminal rendezvous and formation control simulations were performed using data from realistic missions.

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“…Because the cross-track motion is a simple undamped oscillatory motion that is decoupled from the rest of the system, pure derivative control can be applied on this axis to provide adequate damping [41]. Equivalently, the cross-track position weighting can be set to zero in Eq.…”

Section: Simulationsmentioning

confidence: 99%

“…A number of docking maneuvers have been simulated using the nonlinear formation flying model (41)(42)(43)(44), which includes the PPT model, in combination with the observation model in Fig. 2 and the LMPC control law.…”

Section: B Docking Maneuver Simulationmentioning

confidence: 99%

Explicit Model Predictive Control Approach for Low-Thrust Spacecraft Proximity Operations

Leomanni

Rogers

Gabriel

2014

Journal of Guidance, Control, and Dynamics

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The key role of autonomous systems in future space missions has made model predictive control a very attractive guidance and control technique. However, the capability of low-power spacecraft processors to handle the real-time computational load of this technique still needs to be fully established, especially for complex control problems. This paper introduces a method to improve the computational efficiency of model predictive control when applied to the problem of autonomous rendezvous and proximity maneuvering using low-thrust propulsion. To ensure safe trajectories in this scenario, a long control horizon is required and the control problem must be solved at a relatively fast sampling rate. The proposed design addresses such requirements by parameterizing the thrust profile with a set of Laguerre functions. In this setting, the number of control variables can be made significantly smaller than the length of the control horizon, as opposed to standard design methods. By exploiting this property, in combination with multiparametric programming techniques, an explicit control law is derived that is suitable for real-time implementation on simple hardware. The performance of this approach is demonstrated on a small spacecraft mission and compared with that of other control techniques.

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Novel Expressions of Equations of Relative Motion and Control in Keplerian Orbits

Cited by 36 publications

References 17 publications

Adaptive sliding‐mode control for spacecraft relative position tracking with maneuvering target

Adaptive sliding‐mode control for spacecraft relative position tracking with maneuvering target

Nonlinear H-infinity control of relative motion in space via the state-dependent Riccati equations

Explicit Model Predictive Control Approach for Low-Thrust Spacecraft Proximity Operations

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