Abstract
This paper presents the vibroimpact dynamics of an in-plane tethered subsatellite caused by sudden braking during deployment or retrieval. The full dynamics of the subsatellite are composed of its free-flight and the instantaneous impacts. At the moment of impact, the reflective angle of the subsatellite is envisioned to be equal to its incident angle such that the impact law is obtained. Then, the stability of the periodic vibroimpacts is analyzed using the composite Poincaré map. Further, the vibroimpact responses that do not exceed a specified region are numerically determined via the cell mapping method.
Highlights
The vibroimpact phenomena of tethered satellites have been observed in experiments since the first on-orbit launch
The Poincaremap will be used to analyze the stability of the periodic vibroimpacts
The study on the parameter domain is divided into two parts
Summary
The vibroimpact phenomena of tethered satellites have been observed in experiments since the first on-orbit launch. Numerical simulations have indicated that vibroimpacts occurred at the end of the free deployment of a flexible tethered satellite system, as shown in Figure 1 [4]. Matunaga et al [5] pointed out that the impact phenomena in a tethered satellite system are caused by a sudden tensioning force in the tether. To avoid the impact due to the slack of the tether, Wen et al [6, 7] designed a nonlinear control law with a positive tension constraint for the deployment. The aim of this paper is to reveal the impact dynamics of a tethered subsatellite system under tether constraint. The periodic vibroimpacts and their stability via the composite Poincaremap are analyzed.
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