We present a satellite attitude control system design using low-cost hardware and software for a 1U CubeSat. The attitude control system architecture is a crucial subsystem for any satellite mission since precise pointing is often required to meet mission objectives. The accuracy and precision requirements are even more challenging for small satellites where limited volume, mass, and power are available for the attitude control system hardware. In this proposed embedded attitude control system design for a 1U CubeSat, pointing is obtained through a two-stage approach involving coarse and fine control modes. Fine control is achieved through the use of three reaction wheels or three magnetorquers and one reaction wheel along the pitch axis. Significant design work has been conducted to realize the proposed architecture. In this paper, we present an overview of the embedded attitude control system design; the verification results from numerical simulation studies to demonstrate the per...

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 pr...

The importance of space robots in satellite servicing, in EVA assistance, in removing orbital debris and in space exploration is growing driven by space commercialization and exploration efforts. A successful deployment of such robots requires analytical and experimental task validation. With this aim, we present the main characteristics of the software and hardware space robot simulator developed at the NTUA.

The importance of space robots in satellite servicing, in EVA assistance, in removing orbital debris and in space exploration is growing driven by space commercialization and exploration efforts. A successful deployment of such robots requires analytical and experimental task validation. With this aim, we present the main characteristics of the software and hardware space robot simulator developed at the NTUA. 1.

Solar sailing has become a viable and practical option for current satellite missions. A spinning solar sail has a number advantages above a 3-axis stabilised sail. A spinning sail is more resistant to disturbance torques and the misalignment of the centre of mass and centre of pressure. The spinning sail generates a constant centrifugal force, which reduces sail billowing and makes it possible to use wire booms. The new tri-spin solar sail and tri-spin Gyro satellite configurations are proposed that combines the advantages of the spinning and 3-axis stabilised sail designs. This study focuses on the deployment control of the sail and the orientation control of the satellite. Different deployment methods of a rotating structure are studied. The active deployment method makes use of a separate module with an actuator on the rotating system to deploy the structure. The passive deployment method, deploys the structure by using centrifugal force generated by continually spinning the dep...

The increasing presence of additive manufacturing (AM) in the space sector prompted us to investigate the feasibility of a single degree of freedom (DoF) pointing system (PS) made by means of a compound planetary gear train system (C-PGTS) integrating a dynamic balancing system (DBS) and entirely realized in AM. We analyzed in detail the dynamics of the system dealing with the design and the realization of the prototype. Of fundamental importance for this paper is the careful selection of materials for AM suitable for the prohibitive conditions of space. The results, deriving from the comparison between the experimental part and the simulations, underline the correct dimensioning of the PS and the fundamental importance of DBS in maintaining the satellite attitude. The results also confirm the capabilities of AM in the production of complex mechanical systems, allowing high precision, combined with interesting mechanical properties and low weight.This suggests the potential of AM in...

ABSTRACT The importance of space robots in satellite servicing, in EVA assistance, in removing orbital debris and in space exploration is growing, driven by space commercialization and exploration efforts. A successful deployment of such robots requires analytical and experimental task validation. With this aim, we present the main characteristics of the software and hardware space robot emulator developed at the NTUA.

This paper presents some approaches to the design and some experimental results for a reaction wheel (RW) current and speed control loops. Reaction wheels are largely employed in satellite attitude control due to its large range of torque capability, small power consumption and high reliability. However, to achieve such performance the RW design shall deal with several restrictions, such as to support the space environment hazards (radiation, vacuum, high and fast temperature variation), and launch requirements (vibration, noise and choke). In this work some experimental results of an air-bearing table attitude control equipped with a Fiber Optics Gyro (FOG), a reaction wheel and a small fan will be presented. The RW is controlled by speed reference, and a second speed mode control similar to the first one was implemented in an external computer. Both were then compared by means of the airbearing attitude control performance during the wheel zero-speed crossing. The results showed t...