Formation and Attitude Control for the CanX-4 and CanX-5 Formation Flying Mission

Roth, Niels; Johnston-Lemke, Bryan; Damaren, Christopher J.; Zee, Robert E.

doi:10.3182/20110828-6-it-1002.02870

Cited by 13 publications

(11 citation statements)

References 3 publications

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“…Similarly, setting P2b = P (ql cos ao -q2 sin ao) (19) in an in-plane ellipse with d = 0 corrects the along-track bias so that y (-ao) = 2p and y (7r -ao) = -2p (this is just one possible bias correction). For an in-plane ellipse with non-zero d, use P2 = P2a + P2b.…”

Section: Characterization Of Relative Motion In Circular or Elliptic mentioning

confidence: 95%

“…[14,[16][17][18][19][20][21]. Most of these arrive at different solutions since they use different cost functions, make simpli fying assumptions about the reference orbit, or use alternate methods to derive the thrust input or optimality conditions.…”

Section: Discrete-time Optimal Control Problemmentioning

confidence: 99%

“…The discrete formulation is analytically solvable with the use of differential orbital elements as state variables. Similar discrete solvable formu lations have been used by Breger and How [17], Roth [19], Saunders [16], Anderson and Schaub [20], and Gaias et al [21], where the problem is broken up into many segments and the overall fuel cost is minimized, but these methods typically allow more impulses than necessary and do not find the true optimal times.…”

mentioning

confidence: 98%

“…They assume a circular or near-circular reference orbit [1][2][3][4]6,9,10,[13][14][15][16] 3. They assume a set of impulse times and do not solve for the optimal ones [15][16][17][18][19][20][21]. 4.…”

mentioning

confidence: 99%

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Formation establishment and reconfiguration using differential elements in J2-perturbed orbits

Roscoe

Westphal

Griesbach

et al. 2014

2014 IEEE Aerospace Conference

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A practical algorithm is developed for on-board plan ning ofn-impulse fuel-optimal maneuvers for establishment and reconfiguration of spacecraft formations. The method is valid in circular and elliptic orbits and includes first-order secular h effects. The dynamics are expressed in terms of differential mean orbital elements, and relations are provided to allow the formation designer to transform these into intuitive geometric quantities for visualization and analysis. The maneuver target ing problem is formulated as an optimal control problem in both continuous and discrete time. The continuous-time formulation cannot be solved directly in an efficient manner, and the discrete time formulation, which has an analytical solution, does not directly yield the optimal thrust times. Therefore, a practi cal algorithm is designed by iteratively solving the discrete time formulation while using the continuous-time necessary conditions to refine the thrust times until they converge to the optimal values.Simulation results are shown for a variety of reconfiguration maneuvers and reference orbits, including simulations with and without navigation errors for the NASA CubeSat Proximity Operations Demonstration mission.

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Section: Characterization Of Relative Motion In Circular or Elliptic mentioning

confidence: 95%

Section: Discrete-time Optimal Control Problemmentioning

confidence: 99%

mentioning

confidence: 98%

mentioning

confidence: 99%

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Formation establishment and reconfiguration using differential elements in J2-perturbed orbits

Roscoe

Westphal

Griesbach

et al. 2014

2014 IEEE Aerospace Conference

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“…GPS relative navigation has been successfully demonstrated numerous times in spacecraft formation-flying on science missions such as NASA/DLR's Gravity Recovery and Climate Experiment (GRACE) [7,8], DLR's TerraSAR-X Add-on for Digital Elevation Measurement (TanDEM-X) [9,10], and NASA's Magnetospheric Multi-Scale (MSS) mission [11,12]. In contrast to the ground-based approach of these missions, GPS relative navigation has also been pushed to high levels of autonomy on technology demonstration missions like the Swedish Space Corporation's Prototype Research Instruments and Space Mission technology Advancement (PRISMA) mission [13,6,14] and Canada's CanX-4/5 [15,16]. By exchanging GPS measurements between cooperatively orbiting spacecraft, these missions have been able to achieve relative navigation solutions with unprecedented precision onboard.…”

Section: Introductionmentioning

confidence: 99%

Distributed Multi-GNSS Timing and Localization for Nanosatellites

Giralo

D’Amico

2018

Proceedings of the 31st International Technical Meeting of the Satellite Division of the Institute of Navigation (ION GNSS+ 201

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Recent advances in distribution and miniaturization among spacecraft and expansion of global navigation satellite systems (GNSS) motivate the Distributed Multi‐GNSS Timing and Localization system. The DiGiTaL system is intended to provide nanosatellite swarms with unprecedented centimeter‐level relative navigation accuracy in real time and nanosecond‐level time synchronization through the integration of a multiconstellation GNSS receiver, a chip‐scale atomic clock, and an intersatellite link. This paper describes DiGiTaL's hardware and software design, architecture, and navigation software in detail. The swarming spacecraft are grouped into subsets, where differential GNSS is performed by a precise orbit determination module with integer ambiguity resolution in real time. The resulting precise orbits are then exchanged and fused by a swarm determination module, creating full‐swarm knowledge. Finally, the DiGiTaL architecture is integrated into CubeSat avionics and tested with key hardware in the loop using Stanford's GNSS navigation testbed. For the first time, this paper shows the capability to perform centimeter‐level precise relative navigation using commercial‐off‐the‐shelf CubeSat hardware for spacecraft swarms.

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Software-in-the-Loop Validation of a Novel Two-Point Optimal Guidance for Perturbed Spacecraft Rendezvous and Formations

Chihabi,

Ulrich

2023

J Astronaut Sci

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Formation and Attitude Control for the CanX-4 and CanX-5 Formation Flying Mission

Cited by 13 publications

References 3 publications

Formation establishment and reconfiguration using differential elements in J2-perturbed orbits

Formation establishment and reconfiguration using differential elements in J2-perturbed orbits

Distributed Multi-GNSS Timing and Localization for Nanosatellites

Software-in-the-Loop Validation of a Novel Two-Point Optimal Guidance for Perturbed Spacecraft Rendezvous and Formations

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