Ville Lundén
Current Organizations / Institutes
The organizations/institutes from the scholar's latest article
Research Subjects
Ville Lundén has a total of 52 co-authors. Here are the top co-authors by number of shared publications:
- Jaan Praks
Department of Electronics and Nanoengineering, Aalto University, Espoo, Finland
2 shared publications - Mayank
Department of Electronics and Nanoengineering, Aalto University, Espoo, Finland
2 shared publications Adel Malatinszky
1 shared publication- Adnane Osmane
Department of Physics University of Helsinki Helsinki Finland
1 shared publication - Andris Slavinskis
Tartu Observatory, University of Tartu, Observatooriumi 1, 61602 Tõravere, Estonia
1 shared publication - Anton Fetzer
School of Electrical Engineering, Aalto University, Maarintie 8, 02150 Espoo, Finland
1 shared publication
Latest Publications
- Open Access
- 21 July 2025
- Published by Springer Nature in CEAS Space Journal
- Vol. 18 (5) , 1-11
Deployment and mounting system effects on a Ka-band reflectarray antenna: a sensitivity analysis
Reflectarray antennas are utilized in a wide variety of space missions as they combine benefits of reflector and phased array antennas. Large reflectarrays often require deployment mechanisms to enable their use on smaller satellites. The non-idealities of the reflector deployment system and the reflector mounting interfaces can significantly affect the radio frequency (RF) performance of the antenna. However, with lacking previous analysis on these effects, estimating the RF performance degradation is challenging, particularly at early design stages. This work aims to address this issue by analyzing the effects of mounting and deployment system non-idealities on a large, multipanel Ka-band (30 GHz) reflectarray antenna. The selected simulation analysis approach enables inducing and controlling small inaccuracies with high precision. This work shows that only $$0.10^{\circ }$$ and $$0.20^{\circ }$$ angular panel deployment inaccuracies lead to 1 dB and 3 dB gain loss, respectively. Typical reflector penetrating surface features can lead to more than 2 dB gain loss, and panel position inaccuracy out of the reflector plane starts rapidly degrading the gain performance after exceeding 1 mm. This work provides valuable data for estimating the magnitude of effects of non-ideal reflector mounting and deployment system features on large reflectarray antennas already at the start of the antenna design process.- 21 July 2025
- Published by Springer Nature in CEAS Space Journal
- Vol. 18 (5) , 1-11
Open AccessDeployment and mounting system effects on a Ka-band reflectarray antenna: a sensitivity analysis
Reflectarray antennas are utilized in a wide variety of space missions as they combine benefits of reflector and phased array antennas. Large reflectarrays often require deployment mechanisms to enable their use on smaller satellites. The non-idealities of the reflector deployment system and the reflector mounting interfaces can significantly affect the radio frequency (RF) performance of the antenna. However, with lacking previous analysis on these effects, estimating the RF performance degradation is challenging, particularly at early design stages. This work aims to address this issue by analyzing the effects of mounting and deployment system non-idealities on a large, multipanel Ka-band (30 GHz) reflectarray antenna. The selected simulation analysis approach enables inducing and controlling small inaccuracies with high precision. This work shows that only $$0.10^{\circ }$$ and $$0.20^{\circ }$$ angular panel deployment inaccuracies lead to 1 dB and 3 dB gain loss, respectively. Typical reflector penetrating surface features can lead to more than 2 dB gain loss, and panel position inaccuracy out of the reflector plane starts rapidly degrading the gain performance after exceeding 1 mm. This work provides valuable data for estimating the magnitude of effects of non-ideal reflector mounting and deployment system features on large reflectarray antennas already at the start of the antenna design process. - Open Access
- 19 May 2024
- Published by Elsevier in Acta Astronautica
- Vol. 221, 194-205
Magnetospheric Venus Space Explorers (MVSE) mission: A proposal for understanding the dynamics of induced magnetospheres
- 19 May 2024
- Published by Elsevier in Acta Astronautica
- Vol. 221, 194-205
Open AccessMagnetospheric Venus Space Explorers (MVSE) mission: A proposal for understanding the dynamics of induced magnetospheres
- Open Access
- 19 October 2023
- Published by Springer Nature in Space Science Reviews
- Vol. 219 (8) , 1-32
Foresail-2: Space Physics Mission in a Challenging Environment
Earth’s radiation belts are extremely important for space weather because they can store and accelerate particles to relativistic energies, which can have a potential impact on satellite functionality, communications, and navigation systems. The FORESAIL consortium wants to measure these high-energy particle fluxes to understand the dynamics of the radiation belts with its satellite mission Foresail-2. The mission aims to measure magnetic ultra low frequency waves and the plasma environment in the magnetosphere around Earth. The captured data will help to improve our understanding of space weather, and in particular the dynamics of Earth’s radiation belts during periods of large disturbances inside the magnetosphere. A mission design analysis and several trade-off studies are conducted to find the requirements for the science payloads and spacecraft avionics design. Deducted from these requirements, four different payloads are proposed to gather science data in a highly elliptical orbit such as a geostationary transfer orbit. The precision magnetometer uses flux-gate technology to measure magnetic waves from 1 mHz to 10 Hz. The spin scanning particle telescope is built around a detector stack to measure electron spectra in the range of 30 keV to 10 MeV. Additionally, this mission serves as a technology demonstrator for the Coulomb drag experiment which proposes a new kind of electric solar wind sail utilising the Coulomb drag force imposed onto a 300 m long tether. The fourth payload investigates multilayer radiation shielding and single event effects. All payloads will be supported by a newly developed 6U platform using mostly commercial off-the-shelf components. Its proposed avionics face several unique design requirements rising from the payloads and the preferred highly elliptical orbit for this mission.
- 19 October 2023
- Published by Springer Nature in Space Science Reviews
- Vol. 219 (8) , 1-32
Open AccessForesail-2: Space Physics Mission in a Challenging Environment
Earth’s radiation belts are extremely important for space weather because they can store and accelerate particles to relativistic energies, which can have a potential impact on satellite functionality, communications, and navigation systems. The FORESAIL consortium wants to measure these high-energy particle fluxes to understand the dynamics of the radiation belts with its satellite mission Foresail-2. The mission aims to measure magnetic ultra low frequency waves and the plasma environment in the magnetosphere around Earth. The captured data will help to improve our understanding of space weather, and in particular the dynamics of Earth’s radiation belts during periods of large disturbances inside the magnetosphere. A mission design analysis and several trade-off studies are conducted to find the requirements for the science payloads and spacecraft avionics design. Deducted from these requirements, four different payloads are proposed to gather science data in a highly elliptical orbit such as a geostationary transfer orbit. The precision magnetometer uses flux-gate technology to measure magnetic waves from 1 mHz to 10 Hz. The spin scanning particle telescope is built around a detector stack to measure electron spectra in the range of 30 keV to 10 MeV. Additionally, this mission serves as a technology demonstrator for the Coulomb drag experiment which proposes a new kind of electric solar wind sail utilising the Coulomb drag force imposed onto a 300 m long tether. The fourth payload investigates multilayer radiation shielding and single event effects. All payloads will be supported by a newly developed 6U platform using mostly commercial off-the-shelf components. Its proposed avionics face several unique design requirements rising from the payloads and the preferred highly elliptical orbit for this mission.