Atmospheric aerosol characterization with the Dutch–Chinese FAST formation flying mission

Gill, Eberhard; Maessen, D.C.; Laan, E.; Kraft, Stefan; Zheng, Gangtie

doi:10.1016/j.actaastro.2009.09.021

Cited by 6 publications

(5 citation statements)

References 20 publications

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“…A relatively low-cost nanosatellite mission in the 300 km orbit would have a unique potential for providing continuous measurements to different Earth science disciplines and the satellite would remain below the International Space Station. A few examples of research fields where measurement instruments require highaccuracy attitude control and orbit control are magnetic field measurements, gravitational measurements, lower thermosphere studies, and atmospheric re-entry research [1,2,5,[7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Nanosatellite orbit control using MEMS cold gas thrusters

Kvell¹,

Puusepp²,

Kaminski³

et al. 2014

Proc. Estonian Acad. Sci.

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We introduce nanosatellite orbit control using a novel miniaturized cold gas propulsion module based on microelectromechanical systems (MEMS) technology. Firstly, the design and characteristics of the propulsion module suitable for CubeSat class nanosatellites are described. Secondly, mission analyses for in-orbit validation of the propulsion module on a 2-unit CubeSat in 300 km low Earth orbit are presented. The MEMS cold gas propulsion module with 10 cm × 10 cm × 3 cm dimensions and 220 g mass is specifically designed for use in CubeSats. In baseline configuration with a tank for 60 g of butane under 2 to 5 bar pressure, it can provide up to 15 m/s delta-V capability for a 2.66 kg satellite. The module includes four individually controllable thrusters with proportional thrust regulation and closed loop control; maximum thrust is 1 mN per thruster with 5 µN thrust resolution. The fully operational satellite with active orbital control is capable of accommodating a 0.64 kg and 10 cm × 10 cm × 7 cm additional payload. The analysed mission scenarios have potential for different Earth observation applications. Natural deorbiting, controlled orbit lowering, controlled orbit raising, and orbit keeping at 300 km altitude are simulated. Simulations indicate that the natural orbit lifetime can be extended from 63 days to 193 days with the baseline propulsion module and satellite altitude can be increased to 348 km or lowered to 257 km. Orbit keeping at 300 km is possible for up to 76 days; proportional thrust control could provide a further increase to 204 days.

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Section: Introductionmentioning

confidence: 99%

Nanosatellite orbit control using MEMS cold gas thrusters

Kvell¹,

Puusepp²,

Kaminski³

et al. 2014

Proc. Estonian Acad. Sci.

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“…Smaller scale, however, carries higher vulnerability to disturbances and lower power capacity, reinforcing the need for increasingly robust and efficient Attitude Control Systems (ACSs). In 2007, Delft University of Technology and Beijing's Tsinghua University joined efforts and started the Formation for Atmospheric Science and Technology demonstration (FAST) [17,5,6]. The mission consists of the formation flying of two micro-satellites that will use cutting edge technology to collect high atmospheric data.…”

Section: Introductionmentioning

confidence: 99%

Immersion and Invariance Adaptive Backstepping Spacecraft Attitude Control with Modified Rodrigues Parameters

Trigo

Chu

2017

Advances in Aerospace Guidance, Navigation and Control

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An adaptive Backstepping attitude control law based on Immersion and Invariance (I&I) is developed for the TU Delft FAST-D micro-satellite. Tackling both system uncertainties and disturbances, a general additively disturbed rotational dynamics model is considered. In the I&I framework the parameters to be estimated are most commonly constant. Here, however, the family of I&I-Backstepping controllers is shown to be input-to-state stable for a class of strict-feedback systems with time-varying uncertainties. This novel result allows the design of an I&I attitude controller for the spacecraft model considered. The developed control law shows superior performance with respect to Standard (non-adaptive) and Tuning Functions adaptive Backstepping controllers under nominal and heavily perturbed conditions.

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“…Mission objectives exist in the fields of technology, science, and education. Detailed information on the mission can be found in [1][2][3][4]. The following sections focus on the conceptual design of FAST-D that was developed during phase A of the project and on the progress made in the development of the two science payloads of FAST-D.…”

Section: Introductionmentioning

confidence: 99%

Conceptual Design of the FAST-D Formation Flying Spacecraft

Maessen

Guo

Gill

et al. 2009

Small Satellite Missions for Earth Observation

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The paper presents the latest results in the design of FAST-D, the Dutch micro-satellite for the Dutch-Chinese FAST (Formation for Atmospheric Science and Technology demonstration) formation flying mission. Over the course of the 2.5 year mission, the two satellites, FAST-D and FAST-T, will demonstrate various new technologies and perform observations of atmospheric aerosols and seasonal variations of height profiles in the cryosphere using spectropolarimeter and altimeter payloads on both spacecraft. A conceptual design for the Dutch spacecraft, FAST-D, is presented. Special focus is laid on the design of the attitude determination and control subsystem and on the space-based computing experiments to be performed on this spacecraft. Furthermore, new results in the development of the science payloads on FAST-D, the aerosol characterisation instrument SPEX (Spectropolarimeter for Planetary Exploration) and the altimeter SILAT (Stereo Imaging Laser Altimeter), are described. For SPEX, several design changes have been made to make the instrument more compatible with the FAST mission. For SILAT, an instrument re-design for Earth missions is presented, which results in considerable mass savings as compared to the earlier design.

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Atmospheric aerosol characterization with the Dutch–Chinese FAST formation flying mission

Cited by 6 publications

References 20 publications

Nanosatellite orbit control using MEMS cold gas thrusters

Nanosatellite orbit control using MEMS cold gas thrusters

Immersion and Invariance Adaptive Backstepping Spacecraft Attitude Control with Modified Rodrigues Parameters

Conceptual Design of the FAST-D Formation Flying Spacecraft

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