Development of reaction wheels housing for micro‐satellites

Abstract

Purpose

Nowadays, many micro‐satellites rely on three‐axis stabilization using at least three reaction wheels (RWs) for attitude control. Typically, RWs are mounted separately within the satellite and leads to long wires from each RW to the associated electronics. Placement and other constraints may also arise during integration. Furthermore, the large number of mounting holes required for mounting the RWs directly on the structural panels may weaken the integrity of the structure. This paper highlights a need for a special housing to be designed for mounting three to four RWs as a group at one location for simple and easy three‐axis stabilization of typical micro‐satellites.

Design/methodology/approach

Details about the development of the design methodology for such housing are discussed. The basic idea is to place the RWs onto the proposed housing, which will be then mounted on to one of the honeycomb panels used for the satellite structure. Requirements analysis, design, validation, and manufacturing process are covered.

Findings

The outcome is a dimensionally optimized housing structure for four RWs with a frequency safety factor of three.

Originality/value

In summary, the designed product satisfied all requirements. In addition, the exercise set out a planned procedure for designing similar housings for other satellite components.

Citation

Yeong Yong, S. and Chandrakant Joshi, S. (2005), "Development of reaction wheels housing for micro‐satellites", Aircraft Engineering and Aerospace Technology, Vol. 77 No. 2, pp. 114-121. https://doi.org/10.1108/00022660510585947