A5057904728- Spacecraft Design and Technology
- Inertial Sensor and Navigation
- Spacecraft Dynamics and Control
- Space Satellite Systems and Control
- Astro and Planetary Science
- Geophysics and Gravity Measurements
- FinTech, Crowdfunding, Digital Finance
- Solar and Space Plasma Dynamics
- Private Equity and Venture Capital
- Aerospace Engineering and Energy Systems
- Engineering Education and Curriculum Development
- Nuclear reactor physics and engineering
- Higher Education Learning Practices
- Scheduling and Optimization Algorithms
- Planetary Science and Exploration
- Rocket and propulsion systems research
- Nuclear Materials and Properties
- Satellite Communication Systems
- CCD and CMOS Imaging Sensors
- Stellar, planetary, and galactic studies
- Higher Education and Employability
- Infrared Target Detection Methodologies
- Magnetic Field Sensors Techniques
- Radiation Effects in Electronics
- Image Processing and 3D Reconstruction
Tartu Observatory
2015-2023
University of Tartu
2014-2023
Finnish Meteorological Institute
2015
This paper presents the mission analysis, requirements, system design, level test results, as well mass and power budgets of a 1-unit CubeSat ESTCube-1 built to perform first in-orbit demonstration electric solar wind sail (E-sail) technology.The E-sail is propellantless propulsion concept that uses thin charged electrostatic tethers for turning momentum flux natural plasma stream, such wind, into spacecraft propulsion.ESTCube-1 will deploy charge 10 m long tether measure changes in...
In this article, we report on the in-orbit experience - an overview of ESTCube-1 operations from launch until experiment, as well lessons learned five years development and almost two operations. Lessons are identified point view system engineering, electrical mechanical software testing measurements, payload, management. Detailed flight results will be provided in dedicated articles. We hope that other teams can benefit our experience.
Nanosatellites have established their importance in low-Earth orbit (LEO), and it is common for student teams to build them educational technology demonstration purposes. The next challenge the maturity deep-space missions. LEO serves as a relevant environment maturing spacecraft design. Here we present ESTCube-2 mission, which will be launched onboard VEGA-C VV23. satellite was developed demonstrator future mission by Estonian Student Satellite Program. ultimate vision of program use...
This paper presents the characterization and in-orbit validation of ESTCube-1 attitude determination system (ADS). is a one-unit CubeSat built by students launched on May 7, 2013, to Sun-synchronous, 700-km, polar low Earth orbit. Its primary mission centrifugally deploy tether as part first demonstration electric solar wind sail (i.e., E-sail) technology. The ADS uses magnetometers, gyroscopic sensors, Sun an unscented Kalman filter for determination. Here performance commercial...
This paper presents the design, development, and pre-launch characterization of ESTCube-1 Attitude Determination Control System (ADCS).The design driver for ADCS has been mission requirement to spin up satellite 360 deg•s -1 with controlled orientation axis acquire angular velocity attitude during scientific experiment.ESTCube-1 is a one-unit CubeSat launched on 7 May 2013, 2:06 UTC board Vega VV02 rocket.Its primary measure Coulomb drag force exerted by natural plasma stream charged tether...
Here we present the development and qualification of highly integrated satellite avionics stack ESTCube-2, a three-unit CubeSat carrying various in-orbit demonstration payloads. The primary payload is Plasma Brake (PB), which novel deorbiting technology for low Earth orbit (LEO) satellites. observation (EOP) consists two cameras imaging planet in 660 nm 857 spectral bands. Finally, Corrosion Testing Space (CTS) experiment will study behavior nanostructured coating LEO environment. A major...
We propose a distributed close-range survey of hundreds asteroids representing many asteroid families, spectral types and sizes. This can be implemented by fleet nanospacecraft (e.g., 4-5-unit CubeSats) equipped with miniature imaging instruments (from near ultraviolet to infrared). To enable the necessary large delta-v, each spacecraft carries single electric sail tether which taps momentum from solar wind. Data are stored in flash memory during mission downlinked at an Earth flyby. keeps...
Utilization of satellites to meet the needs various missions requires a reliable Attitude Determination and Control System (ADCS). In this paper, we presents robust design ADCS for ESTCube-2 nanosatellite. The primary aim is provide angular momentum deploy 300-meter tether used in plasma brake deorbiting experiment. This achieved by spinning up three-unit CubeSat 360 degrees per second about short axis, deploying repeating spin-up-deployment sequence until whole deployed. system also...
Here we present a successful crowdfunding campaign, which raised more than €38.7k (≈$45.8k) for ESTCube-2 satellite development. Crowdfunding is the practice of funding project or venture by raising money from large number people who each contribute relatively small amount, typically via internet. three-unit CubeSat will tests technologies future interplanetary nanospacecraft missions. The campaign was launched on March 13, 2017 with goal to fundraise €30k. Within first day, €6.1k. Over week...
This article demonstrates the performance of an improved particle swarm optimization (PSO) algorithm with scalar checking and rotation axis fitting objectives using in-orbit data, which is obtained from two CubeSats missions, Aalto-1 ESTCube-1, as well simulation reference. The uses sequential refinement process to combine objectives. improvement addresses some challenges magnetometer calibration when data. First, change in magnetic field vector direction at different points orbit...
This paper presents the design and study of cross product control, Linear-Quadratic Regulator (LQR)optimal control high spin rate algorithms for ESTCube-2/3 missions. The three-unit CubeSat is required to up in order centrifugally deploy a 300-m long tether plasma brake deorbiting experiment. algorithm designed satellite one rotation per second which achieved 40 orbits. LQR optimal controller based on closed-loop step response with controllability stability analysis meet pointing...
This article describes the optical design and analysis of Theia: a miniature, scientific-grade, multispectral Earth observation imager for nanosatellites that can be used quantitative remote sensing. The instrument is designed to take images with 5% radiometric accuracy throughout its three-year lifetime. sustained achieved post-launch calibration module. capture frames at 33-m ground sampling distance an orbit height 650 km. diffraction-limited modulation transfer function least 0.13...