Distributed multi‐GNSS timing and localization for nanosatellites

Giralo, Vincent; D’Amico, Simone

doi:10.1002/navi.337

Cited by 24 publications

(4 citation statements)

References 30 publications

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“…The position accuracy (standard deviation errors) was found to have a mean of 2.89 m and a maximum of 4.02 m. The CanX 4&5 mission [21] with similar or worse position accuracy has demonstrated a relative position control with a sub-meter accuracy. Recent developments of DGPS [22] show the promise of providing nanosatellite-based distributed space systems with centimeter-level relative position accuracy. The state estimation accuracy and corresponding control errors demonstrated in the aforementioned missions are within the image demonstration mission requirements, determined by what can be observed as a misalignment of the formation's geometry by a human eye.…”

Section: Lqr-based Continuous Control Algorithmsmentioning

confidence: 99%

Satellite Formation Flying for Space Advertising: From Technically Feasible to Economically Viable

2022

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The paper presents a feasibility study of satellite formation-flying missions for space advertising. To estimate a space advertising mission viability, the global population coverage model is designed and the demonstration schedule with a focus on larger cities is optimized for the formation of small satellites deployed in repeat ground track Sun-synchronous orbits. Monetization of an image demonstration over a city depends on the city population, outdoor advertising cost, and parameters limiting the number of potential advertising observations. Formation lifetime expressed in terms of fuel consumption for image reconfigurations and maintenance is one of the key factors and is analyzed via numerical simulation of satellite formation-flying dynamics and control.

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Section: Lqr-based Continuous Control Algorithmsmentioning

confidence: 99%

Satellite Formation Flying for Space Advertising: From Technically Feasible to Economically Viable

2022

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“…state of the art in GNSS. Precision GNSS yields meter-level accuracy in the absolute Cartesian state and centimeter-level accuracy in the relative Cartesian state [29]. To be consistent with the state representations in this example, the mean and standard deviations must be transformed into the quasi-nonsingular ROE and Keplerian orbit element state representations using the well-known nonlinear transformations.…”

Section: Appendix A: Dynamics Of Relative Motionmentioning

confidence: 99%

New Closed-Form Solutions for Optimal Impulsive Control of Spacecraft Relative Motion

Chernick

D’Amico

2018

Journal of Guidance, Control, and Dynamics

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This paper addresses the spacecraft relative orbit reconfiguration problem of minimizing the delta-v cost of impulsive control actions while achieving a desired state in fixed time. The problem is posed in relative orbit element (ROE) space, which yields insight into relative motion geometry and allows for the straightforward inclusion of perturbations in linear timevariant form. Reachable set theory is used to translate the cost-minimization problem into a geometric path-planning problem and formulate the reachable delta-v minimum, a new metric to assess optimality and quantify reachability of a maneuver scheme. Next, this paper presents a methodology to compute maneuver schemes that meet this new optimality criteria and achieve a prescribed reconfiguration. Though the methodology is applicable to any linear time-variant system, this paper leverages a state representation in ROE to derive new globally optimal maneuver schemes in orbits of arbitrary eccentricity. The methodology is also used to generate quantifiably sub-optimal solutions when the optimal solutions are unreachable. Further, this paper determines the mathematical impact of uncertainties on achieving the desired end state and provides a geometric visualization of those effects on the reachable set. The proposed algorithms are tested in realistic reconfiguration scenarios and validated in a high-fidelity simulation environment.

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“…The inter-satellite range and time difference can be measured using the navigation satellite common view method or the inter-satellite RF autonomous measurement method [3,4]. The inter-satellite RF autonomous measurement method can effectively overcome the problems of the navigation satellite common view method, which has a high measurement accuracy only for low earth orbits and thus a limited scope of application.…”

Section: Introductionmentioning

confidence: 99%

Precision Joint RF Measurement of Inter-Satellite Range and Time Difference and Scalable Clock Synchronization for Multi-Microsatellite Formations

Hou

Jin

Zhou

et al. 2023

Sensors

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The rapid development of multi-satellite formations requires inter-satellite radio frequency (RF) measurement to be both precise and scalable. The navigation estimation of multi-satellite formations using a unified time reference demands the simultaneous RF measurement of the inter-satellite range and time difference. However, high-precision inter-satellite RF ranging and time difference measurements are investigated separately in existing studies. Different from the conventional two-way ranging (TWR) method, which is limited by its reliance on a high-performance atomic clock and navigation ephemeris, asymmetric double-sided two-way ranging (ADS-TWR)-based inter-satellite measurement schemes can eliminate such reliance while ensuring measurement precision and scalability. However, ADS-TWR was originally proposed for ranging-only applications. In this study, by fully exploiting the time-division non-coherent measurement characteristic of ADS-TWR, a joint RF measurement method is proposed to obtain the inter-satellite range and time difference simultaneously. Moreover, a multi-satellite clock synchronization scheme is proposed based on the joint measurement method. The experimental results show that when inter-satellite ranges are hundreds of kilometers, the joint measurement system has a centimeter-level accuracy for ranging and a hundred-picosecond-level accuracy for time difference measurement, and the maximum clock synchronization error was only about 1 ns.

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Distributed multi‐GNSS timing and localization for nanosatellites

Cited by 24 publications

References 30 publications

Satellite Formation Flying for Space Advertising: From Technically Feasible to Economically Viable

Satellite Formation Flying for Space Advertising: From Technically Feasible to Economically Viable

New Closed-Form Solutions for Optimal Impulsive Control of Spacecraft Relative Motion

Precision Joint RF Measurement of Inter-Satellite Range and Time Difference and Scalable Clock Synchronization for Multi-Microsatellite Formations

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