A satellite formation to display pixel images from the sky: Mission design and control algorithms

Biktimirov, Shamil; Ivanov, Danil; Pritykin, Dmitry

doi:10.1016/j.asr.2022.03.018

Cited by 7 publications

(11 citation statements)

References 26 publications

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“…These errors are mainly caused by the Cartesian coordinates representation of the relative trajectory. As shown in [8], the satellite formation for image demonstration can be as large as several kilometers in size, and in this case, the control calculation using the Cartesian coordinates can lead to significant errors. Due to these errors, the control algorithm for tracking reference trajectories (2) results in divergence in time [9].…”

Section: Problem Statement and Equations Of Motionmentioning

confidence: 99%

“…Relative motion control, however, is required to achieve the selected relative trajectories. A hybrid impulsive-continuous control scheme allowing to converge to the required trajectory using continuous thrust was proposed in [8]. This approach relies on a propulsion system and becomes inappropriate if any of the satellites run out of fuel.…”

Section: Introductionmentioning

confidence: 99%

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Decentralized Differential Aerodynamic Control of Microsatellites Formation with Sunlight Reflectors

Chernov,

Monakhova,

Mashtakov

et al. 2023

Aerospace

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The paper presents a study of decentralized control for a satellite formation flying mission that uses differential lift and drag to enforce the relative positioning requirements. All spacecraft are equipped with large sunlight reflectors so that, given the appropriate lighting conditions, the formation as a whole can be made visible from the Earth as a configurable pixel image in the sky. The paper analyzes the possibility of achieving a pre-defined lineup of the formation by implementing decentralized aerodynamic-based control through the orientation of sunlight reflectors relative to the incoming airflow. The required relative trajectories are so-called projected circular orbits which ensure the rotation of the image with the orbital period. The choice of the reference trajectory for each satellite is obtained by minimizing the total sum of relative trajectory residuals. The control law is based on the linear-quadratic regulator with the decentralized objective function of reducing the mean deviation of each satellite’s trajectory relative to the other satellites. The accuracy of the required image construction and convergence time depending on the initial conditions and orbit altitude are studied in the paper.

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Section: Problem Statement and Equations Of Motionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Decentralized Differential Aerodynamic Control of Microsatellites Formation with Sunlight Reflectors

Chernov,

Monakhova,

Mashtakov

et al. 2023

Aerospace

Self Cite

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show abstract

“…The former is used to reflect sunlight to a point of interest (POI) on Earth. It requires relatively large sunlight reflectors with an area of about 30 square meters [8] for LEO orbits to ensure the required pixel brightness as well as keeping the required reflectors' attitude to illuminate the required region on Earth. The latter gives more flexibility on satellite attitude during image demonstration, but requires additional power supply.…”

Section: Introductionmentioning

confidence: 99%

“…Our prior studies have formed the concept of a formation-flying mission for longterm space advertising [8]. The proposed satellite formation comprises multiple CubeSats equipped with solar reflectors.…”

Section: Introductionmentioning

confidence: 99%

“…Pixel visibility is expressed in terms of its apparent magnitude m and the minimum inter-pixel distance IPD min is defined by the angular resolution of a human eye that is known to be equal to about one arcmin. In [8], the mission design method for selecting target orbits for the mission, solar reflector sizing, and orbital configuration design were proposed. It was shown that the target orbits for the mission should be circular Sun-synchronous and lie close to the terminator plane.…”

Section: Introductionmentioning

confidence: 99%

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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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How are multiple satellites seen from the ground? Relative apparent motion and formation stabilization

Nakajima,

Yoshimura,

Chen

et al. 2024

Astrodyn

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A satellite formation to display pixel images from the sky: Mission design and control algorithms

Cited by 7 publications

References 26 publications

Decentralized Differential Aerodynamic Control of Microsatellites Formation with Sunlight Reflectors

Decentralized Differential Aerodynamic Control of Microsatellites Formation with Sunlight Reflectors

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

How are multiple satellites seen from the ground? Relative apparent motion and formation stabilization

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