Flight Results of Precise Autonomous Orbit Keeping Experiment on PRISMA Mission

Florio, Sergio De; D’Amico, Simone; Radice, Gianmarco

doi:10.2514/1.a32347

Cited by 14 publications

(4 citation statements)

References 7 publications

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“…This is due to the physics of the problem for which a control of δL λMAX by means of along-and anti-along-track velocity increments implies by itself the control of δa around the null value. 1,2 If δa M AX is not considered Eq. (37) yields…”

Section: A Linear Controlmentioning

confidence: 99%

Precise Autonomous Orbit Control in Low Earth Orbit

Florio

D’Amico

Radice

2012

AIAA/AAS Astrodynamics Specialist Conference

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This paper analyses the problem of the autonomous absolute orbit control of a spacecraft in low Earth orbit using different on-board feedback control systems. Three types of control are compared. The first implements an analytical control algorithm. The second and third controllers considered are the linear and the quadratic optimum regulator from the classical control theory. For the implementation of the linear regulators the problem has been formulated as a two spacecraft formation keeping in which one of the spacecraft is virtual and not affected by non-gravitational orbit perturbations. The relative Earth-fixed elements have been introduced as a set of parameters which can express the relative motion of two spacecraft in an Earth-fixed reference frame. These relative elements allow the general formalization of the requirements of an absolute orbit control system design and its formulation as a particular case of spacecraft formation flying control problem. A direct mapping between the relative Earth-fixed and orbital elements enables the direct translation of absolute to formation control requirements and the straightforward use of classical control theory techniques for the orbit control of distributed spacecraft systems. The validation, performance estimation and comparison of the control algorithms are realized by means of numerical simulations with a high level of realism. NomenclatureA spacecraft reference area [m 2 ] B ballistic coefficient of the spacecraft [kg/m 2 ] C D drag coefficient [-] J 2 geopotential second-order zonal coefficient [-] M mean anomaly [rad] R E Earth's equatorial radius [m] T E mean period of solar day [s] m spacecraft mass [kg] a semi-major axis [m] e j eccentricity [-] e j eccentricity vector component [-] g j gain i inclination [rad] i j inclination vector component [rad] n mean motion [rad/s] s j characteristic root t time [s] u argument of latitude [rad] * PhD Candidate, Space Advanced Research Team, School of Engineering, v spacecraft velocity [m/s] δκ relative orbital elements vector λ longitude [rad] δa relative semi-major axis [-] δe relative eccentricity vector amplitude [-] δh altitude deviation [m] δi relative inclination vector amplitude [rad] κ mean orbital elements vector κ o osculating orbital elements vector δL j phase difference vector component [m] δr relative position vector [m] δr j relative position vector component [m] δu relative argument of latitude [rad] δv relative velocity vector [m/s] δv j relative velocity vector component [m/s] ∆v j maneuver velocity increment component [m/s] ǫ normalized relative orbital elements vector [m] η normalized altitude [-] φ relative perigee [rad] ϕ latitude [rad] µ Earth gravitational coefficient [m 3 /s 2 ] ω argument of periapsis [rad] ω E Earth rotation rate [rad/s] Ω right ascension of the ascending node [rad] Ω secular rotation of the line of nodes [rad/s] ρ atmospheric density [kg/m 3 ] θ relative ascending node [rad] R + set of positive real numbers Z set of integer numbers Subscript d drag E Earth g gravity R re...

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Section: A Linear Controlmentioning

confidence: 99%

Precise Autonomous Orbit Control in Low Earth Orbit

Florio

D’Amico

Radice

2012

AIAA/AAS Astrodynamics Specialist Conference

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“…Earth orbit [48], [49], [50] .The reason this type of trajectory is safe is that the projection on the y-z plane of the LVLH frame can be shaped such that the chaser never comes close to the origin. If the amplitudes of the in-plane and out-ofplane oscillations are equal, the projection on the y-z plane is a circle.…”

Section: A Eccentric Safe Orbits From Generalized Inclination / Eccentricity Vector Separationmentioning

confidence: 99%

Linear Cotangential Transfers and Safe Orbits for Elliptic Orbit Rendezvous

Peters

Noomen

2021

Journal of Guidance, Control, and Dynamics

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“…Space Earth missions often use nearly circular orbits for which changes in radius per revolution do not exceed tenths of a percent. In particular, this applies to satellites of remote Earth sensing for which proximity of trajectories to a circular orbit is important for the observation quality [1][2][3].…”

Section: Introductionmentioning

confidence: 99%

Development of a new form of equations of disturbed motion of a satellite in nearly circular orbits

Pirozhenko¹,

Maslova²,

Khramov³

et al. 2020

EEJET

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The use of simple physical reasoning instead of the method of varying constants has made it possible to elaborate a short scheme of deriving equations of disturbed motion of a satellite in nearly circular orbits. The use of a circular Keplerian orbit as a reference orbit has ensured the nondegeneracy of equations and their simple relation with time. All this taken together has made it possible to propose a form of equations convenient for carrying out numerical and analytical studies with its variables having a simple physical meaning. A relationship between the introduced variables and the Keplerian elements of the orbits was described for undisturbed motion. It was shown that the variables describing the deviation of the orbit radius from the radius of the reference orbit are proportional to eccentricity and deviation of the focal parameter is proportional to the square of the eccentricity. Relationships were constructed that describe the connection between the introduced variables and the Cartesian coordinates of position and velocity in the inertial coordinate system as well as arguments for choosing the radius of the reference orbit. From the condition of equality of energies of motion along circular reference orbit and in elliptical Keplerian orbit, it is expedient to take the radius of the reference orbit equal to the semi-major axis of the Keplerian ellipse. Approaches to the possible development of the proposed equations were presented. They make it possible to describe changes in the argument of the orbit perigee. The proposed change of variables makes it possible to avoid degeneracy of equations at very small eccentricities when studying the change in the orbit perigee. The advantages of using the proposed equations for numerical and analytical studies of satellite motion in nearly circular orbits were shown on concrete calculation examples. It was shown that the results of numerical integration in the proposed variables give almost five orders of magnitude less error than the results of the integration of equations in Cartesian coordinates

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Flight Results of Precise Autonomous Orbit Keeping Experiment on PRISMA Mission

Cited by 14 publications

References 7 publications

Precise Autonomous Orbit Control in Low Earth Orbit

Precise Autonomous Orbit Control in Low Earth Orbit

Linear Cotangential Transfers and Safe Orbits for Elliptic Orbit Rendezvous

Development of a new form of equations of disturbed motion of a satellite in nearly circular orbits

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