Gemini rendezvous program

Chamberlin, James Allen; Rose, James T.

doi:10.2514/3.27585

Cited by 24 publications

(11 citation statements)

References 2 publications

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“…Vernal equinox is referred as x-axis similarly y axis shows a right hand of coordinate system and z axis represent allied in Earth rotation. According to Chamberlin the x axis is represent a radial direction, y axis represents in-track or along-track direction, and z direction represent the cross-track or out-of-plane direction (Chamberlin, 2012, Bevilacqua et al, 2008. The coordinate frames are well designed for the study of relative motion analysis through the reference of Schweighart and Sedwick.…”

Section: Co-ordinate Framementioning

confidence: 99%

“…(Schweighart et al, 2002). The relative motion equation has been used extensively since 1960s for spacecraft close proximity operation modelling, with the heritage on the manned Gemini, Apollo, and Shuttle mission (Chamberlin et al, 2012, Goodman et al, 2006.…”

Section: Co-ordinate Framementioning

confidence: 99%

“…Therefore, to determine the drag effect by using the equation as given below. [3] Noteworthy, the spacecraft characteristics as well as local atmospheric density are not necessarily the same. Generally, differential drag in the dynamical model is more challenge for arbitrary formation.…”

Section: Equation Of Motionmentioning

confidence: 99%

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Study the Influence of Atmospheric Drag and J2 Effect in a Close-proximity Operation at LEO

Sanjeeviraja¹,

Santhanakrishnan²,

Lakshmi³

2018

IJET

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In this paper is to assess the mission stability and the influence of J2 effect and aerodynamic forces. To maintain the relative motion of satellites by using a feedback control law for tracking error bound in the presence of J2 perturbation. A constant relative orbit under the effect of earth oblateness and conservative forces is referred as J2 and targeting the presence of atmospheric drag. Although, Schweighart and Sedwick control strategy for satellite relative motion is considering both lift and drag forces. The simulation result shows a better performance with high accuracy than an elliptical orbit under J2 perturbation and atmospheric drag along in-track formation. The algorithm and control strategies is useful tools for analysing a future space mission.

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Section: Co-ordinate Framementioning

confidence: 99%

Section: Co-ordinate Framementioning

confidence: 99%

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Study the Influence of Atmospheric Drag and J2 Effect in a Close-proximity Operation at LEO

Sanjeeviraja¹,

Santhanakrishnan²,

Lakshmi³

2018

IJET

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“…This STM has flight heritage on numerous programs including Gemini, Apollo, the Space Shuttle, and many others. [10][11][12] While the initial HCW model employed rectilinear relative position and velocity, other authors have found that an identical STM can be used to propagate a relative state defined through curvilinear coordinates with orders-of-magnitude better accuracy. 13 Taking a slightly different approach, Lovell and Tragesser used nonlinear combinations of the relative position and velocity to define a state based on the HCW invariants.…”

Section: Introductionmentioning

confidence: 99%

New State Transition Matrices for Relative Motion of Spacecraft Formations in Perturbed Orbits

Koenig

Guffanti

D’Amico

2016

AIAA/AAS Astrodynamics Specialist Conference

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This paper presents new state transition matrices that model the relative motion of two spacecraft in arbitrarily eccentric orbits perturbed by J2 and differential drag for three state definitions based on relative orbital elements. These matrices are derived by first performing a Taylor expansion on the equations of relative motion including all considered perturbations and subsequently computing an exact, closed-form solution of the resulting linear differential equations. Both density-model-specific and density-model-free differential drag formulations are included. Density-model-specific formulations require a-priori knowledge of the atmosphere, while density-model-free formulations remove this requirement by augmenting the relative state with a set of parameters which are estimated in flight. The resulting state transition matrices are used to generalize the geometric interpretation of the effects of J2 and differential drag on relative motion in near-circular orbits provided in previous works to arbitrarily eccentric orbits. Additionally, this paper harmonizes current literature by demonstrating that a number of state transition matrices derived by previous authors using various techniques can be found by subjecting the models presented in this paper to more restrictive assumptions. Finally, the presented state transition matrices are validated through comparison with a high-fidelity numerical orbit propagator. It is found that the models including density-model-free differential drag exhibit much better performance than their density-model-specific counterparts. Specifically, these state transition matrices are able to reduce propagation errors by at least an orderof-magnitude when compared to models including only J2 and are able to match or exceed the accuracy of comparable models in literature over a broad range of orbit scenarios.

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“…An interest in space missions based on the relative position, orientation, and/or dynamics of multiple spacecraft has existed since the Gemini program [1]. After the completion of the Apollo program interest waned in relative motion research as the U.S. space program focused heavily on mission architectures centered on large monolithic spacecraft with a multitude of capabilities, e.g., the Space Transportation System (shuttle) platform [2].…”

Section: Introductionmentioning

confidence: 99%

Position Extrema in Keplerian Relative Motion: A Gröbner Basis Approach

2012

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This paper analyzes the relative motion between two spacecraft in orbit. Specifically, the paper provides bounds for relative spacecraft position-based measures which impact spacecraft formation-flight mission design and analysis. Previous efforts have provided bounds for the separation distance between two spacecraft. This paper presents a methodology for bounding the local vertical, horizontal, and cross track components of the relative position vector in a spacecraft centered, rotating reference frame. Three metrics are derived and a methodology for bounding them is presented. The solution of the extremal equations for the metrics is formulated as an affine variety and obtained using a Gröbner basis reduction. No approximations are utilized and the only assumption is that the two spacecraft are in bound Keplerian orbits. Numerical examples are included to demonstrate the efficacy of the method. The metrics have utility to the mission designer of formation flight architectures, with relevance to Earth observation constellations.

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Gemini rendezvous program

Cited by 24 publications

References 2 publications

Study the Influence of Atmospheric Drag and J2 Effect in a Close-proximity Operation at LEO

Study the Influence of Atmospheric Drag and J2 Effect in a Close-proximity Operation at LEO

New State Transition Matrices for Relative Motion of Spacecraft Formations in Perturbed Orbits

Position Extrema in Keplerian Relative Motion: A Gröbner Basis Approach

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