Design and prototyping of PROBA-3 formation flying system

Peyrard, Julien; Olmos, Diego Escorial; Agenjo, Alfredo; Kron, Aymeric; Cropp, Alexander

doi:10.1504/ijspacese.2014.060110

Cited by 4 publications

(3 citation statements)

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“…(83) If the procedure gives the minimum-fuel 1-impulse solution, there is no guarantee that this solution is optimal when varying the possible number of impulses except when the conditions described in Table I for the cases B 1 and B 2 are fulfilled. The first numerical example is based on the PROBA-3 mission whose main goals are to demonstrate the technologies required for Formation Flying of two spacecraft in highly elliptical orbit [19]. The necessary orbital elements and conditions for the out-of-plane rendezvous definition are given in Table III.…”

Section: Numerical Examplesmentioning

confidence: 99%

Analytical Solutions for Impulsive Elliptic Out-of-Plane Rendezvous Problem via Primer Vector Theory

Serra

Arzelier

Rondepierre

2018

IEEE Trans. Contr. Syst. Technol.

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This paper focuses on the fixed-time minimum-fuel out-of-plane rendezvous between close elliptic orbits of an active spacecraft, with a passive target spacecraft, assuming a linear impulsive setting. It is shown that the out-of-plane elliptic relative dynamics are simple enough to allow for an analytical solution of the problem reviewed. Indeed, the approach relies on the primer vector theory by writing down and directly solving the optimality necessary conditions. After analyzing the characteristics of the dynamics of the optimal primer vector candidates, the complete analytical optimal solution is obtained for arbitrary durations of the rendezvous and arbitrary boundary conditions.

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Section: Numerical Examplesmentioning

confidence: 99%

Analytical Solutions for Impulsive Elliptic Out-of-Plane Rendezvous Problem via Primer Vector Theory

Serra

Arzelier

Rondepierre

2018

IEEE Trans. Contr. Syst. Technol.

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“…The first example is based on the PROBA-3 mission whose main goals are to demonstrate the technologies required for Formation Flying of two spacecraft in highly elliptical orbit Peyrard et al (2013). This mission is made of two independent minisatellites in HEO (Highly-elliptical Earth Orbit) in Precise Formation Flying formation.…”

Section: Numerical Examplementioning

confidence: 99%

Analytical optimal solutions of impulsive out-of-plane rendezvous around elliptic orbits

Serra

Arzelier

Rondepierre

et al. 2014

IFAC Proceedings Volumes

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This paper focuses on the fixed-time minimum-fuel out-of-plane rendezvous between close elliptic orbits of an active spacecraft, with a passive target spacecraft, assuming a linear impulsive setting, and a Keplerian relative motion. It is shown that the out-of-plane Keplerian relative dynamics are simple enough to allow for an analytical solution of the problem reviewed. The different optimal solutions, for different durations of the rendezvous, are obtained via the analysis of the optimal conditions expressed in terms of the primer vector. A numerical example illustrate sthese results.

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“…Contrasting the LEO environment that the PRISMA formation occupies, the PROBA-3 formation uses a highly-elliptical orbit with a considerably large variation in altitude. At perigee, the spacecraft pass below 600 km, and at apogee they pass outside of 60 530 km [95]; this large apogee altitude is selected as a mission requirement for the PROBA-3 observation platform, however simulation of this orbit conĄguration here provides a means to examine both the real-world propagator models and the navigation algorithms proposed later. The two spacecraft of PROBA-3 are scientiĄc platforms designated as the Occulter and the Coronograph, and the orbital elements and spacecraft parameters listed in Tables 2.4 and 2.5 are used for simulating the PROBA-3 formation, as provided by Peters [96].…”

Section: Case 2: Proba-3 Formationmentioning

confidence: 99%

Adaptive Extended Kalman Filtering Strategies for Autonomous Relative Navigation of Formation Flying Spacecraft

Fraser¹

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This research addresses the relative navigation problem for spacecraft formation Ćying missions in near-Earth orbit. Technological and economic inĆuences have expedited the miniaturization of spacecraft systems, popularizing the notion of satellite teamwork due to the potential reductions in overall costs and complexity. It is now feasible to use a coordinated group of close-proximity satellites, known as a formation, to autonomously perform rendezvous, on-orbit servicing and science-based missions for a fraction of the resources a large-scale satellite would require. Despite the growing interest in formation Ćying spacecraft however, only a limited number of applications have been Ćight validated as a result of the difficulties associated with accurately determining the relative motion of the spacecraft within a formation. To enhance the capabilities of onboard autonomous guidance, navigation and control systems, this thesis presents the development of two adaptive extended Kalman Ąlter navigation algorithms for spacecraft formation Ćying. The proposed adaptive Ąlters are capable of updating the internal noise characteristics of the Kalman Ąlter in real time, and are viable in all orbit scenarios, including highly elliptical orbits in the presence of perturbations. The Ąrst Kalman Ąlter approach uses maximum likelihood estimation techniques to derive analytical adaptations laws for the Ąlter, which are then improved through the novel inclusion of an intrinsic smoothing routine. The second approach uses an embedded fuzzy logic system based on a covariancematching analysis of the Ąlter residuals, where the fuzzy system has been speciĄcally designed for the spacecraft navigation problem at hand. Numerical simulations of three spacecraft formations are used to demonstrate that the proposed adaptive navigation algorithms are appreciably more robust to Ąlter initialization errors, dynamics modelling deĄciencies, and measurement noise than the standard Kalman Ąlter. iii To Dr. Steve Ulrich, formally my supervisor, but more importantly my mentor, my professor, and my friend; your steadfast support and leadership have made my studies in Ottawa immensely fulĄlling. Thank you for providing this opportunity to continually learn from your expertise, and for instilling conĄdence and direction throughout the span of our collaboration. The dedication you have shown to me, and all of the members of our research group, is remarkable. It has been an honor to work with you, and a whole lot of fun too. To the professors who have guided me along this journey, including Bruce Burlton, Tarik Kaya, Alex Ellery, Victor Aitken, Howard Schwartz, and many others from Carleton University. The knowledge and wisdom you have shared has been invaluable to my growth as an engineer. And from the days at Dalhousie University, my thanks in particular to Professors Darrel Doman, Jeff Dahn, Timothy Little, and Guy Kember. You managed to imbue a fascination with space elevators, the laws of nature, the rules of mathematics, and the process of learning,...

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Design and prototyping of PROBA-3 formation flying system

Cited by 4 publications

References 1 publication

Analytical Solutions for Impulsive Elliptic Out-of-Plane Rendezvous Problem via Primer Vector Theory

Analytical Solutions for Impulsive Elliptic Out-of-Plane Rendezvous Problem via Primer Vector Theory

Analytical optimal solutions of impulsive out-of-plane rendezvous around elliptic orbits

Adaptive Extended Kalman Filtering Strategies for Autonomous Relative Navigation of Formation Flying Spacecraft

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