To address the challenge of spacecraft navigating multiple dynamic forbidden-pointing zones, this study proposes an attitude trajectory planning method based on a teardrop-shaped repulsive artificial potential function. This paper examines situations where a low-orbiting satellite must avoid light reflections from a high-orbiting satellite and where the surface of a deep space probe must avoid the direction of micrometeoroid impacts, in contrast to the conventional assumption that celestial bodies are static forbidden zones. Based on the high-speed characteristics of micrometeoroids and the angular velocity differences between satellites, a dynamic forbidden zone model is constructed. Building on the traditional uniform repulsive circle potential function, an innovative teardrop potential function is proposed, enabling the potential field to dynamically adapt to the approach angle between the spacecraft and the forbidden zone. A motion trend function is also introduced to characterize the relative motion characteristics. Furthermore, a short-path detour strategy with adjustable repulsive potential function coefficients is designed, enabling the spacecraft to flexibly switch obstacle avoidance directions based on actual needs. According to simulation results, this approach greatly enhances spacecraft predictability and obstacle avoidance performance in complex and dynamic settings, offering significant theoretical and engineering application value for attitude control under dynamic constraints.