Next Article in Journal
Control of a Supersonic Inlet in Off-Design Conditions with Plasma Actuators and Bleed
Next Article in Special Issue
Verification Approaches for Nano- and Micro-Satellites
Previous Article in Journal
Aircraft Mode S Transponder Fingerprinting for Intrusion Detection
Previous Article in Special Issue
Implementation and Hardware-In-The-Loop Simulation of a Magnetic Detumbling and Pointing Control Based on Three-Axis Magnetometer Data
Open AccessArticle

A Dynamic Testbed for Nanosatellites Attitude Verification

Department of Industrial Engineering, University of Bologna, Via Fontanelle 40, I-47121 Forlì (FC), Italy
Author to whom correspondence should be addressed.
Aerospace 2020, 7(3), 31;
Received: 18 December 2019 / Revised: 12 March 2020 / Accepted: 15 March 2020 / Published: 18 March 2020
(This article belongs to the Special Issue Verification Approaches for Nano- and Micro-Satellites)
To enable a reliable verification of attitude determination and control systems for nanosatellites, the environment of low Earth orbits with almost disturbance-free rotational dynamics must be simulated. This work describes the design solutions adopted for developing a dynamic nanosatellite attitude simulator testbed at the University of Bologna. The facility integrates several subsystems, including: (i) an air-bearing three degree of freedom platform, with automatic balancing system, (ii) a Helmholtz cage for geomagnetic field simulation, (iii) a Sun simulator, and (iv) a metrology vision system for ground-truth attitude generation. Apart from the commercial off-the-shelf Helmholtz cage, the other subsystems required substantial development efforts. The main purpose of this manuscript is to offer some cost-effective solutions for their in-house development, and to show through experimental verification that adequate performances can be achieved. The proposed approach may thus be preferred to the procurement of turn-key solutions, when required by budget constraints. The main outcome of the commissioning phase of the facility are: a residual disturbance torque affecting the air bearing platform of less than 5 × 10−5 Nm, an attitude determination rms accuracy of the vision system of 10 arcmin, and divergence of the Sun simulator light beam of less than 0.5° in a 35 cm diameter area. View Full-Text
Keywords: ADCS verification; CubeSat ADCS verification; CubeSat
Show Figures

Figure 1

MDPI and ACS Style

Modenini, D.; Bahu, A.; Curzi, G.; Togni, A. A Dynamic Testbed for Nanosatellites Attitude Verification. Aerospace 2020, 7, 31.

Show more citation formats Show less citations formats
Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Article Access Map by Country/Region

Search more from Scilit
Back to TopTop