The 2026 Europlanet Prize for Public Engagement has been awarded to CosmoAmautas, a Peruvian non-profit association that uses planetary science and astronomy as a gateway to spark curiosity and bring scientific opportunities to children and young students across Peru.

Saturn’s icy moon Enceladus might be more supportive of life than was previously thought. An LMU study reveals that microorganisms could survive in its hidden ocean.

With the increasing scale of space infrastructure such as large space telescopes, antenna arrays, and solar power stations, the payload fairing size of launch vehicles has become a critical bottleneck constraining their development. On-orbit autonomous assembly via deployable modules has emerged as an important technical approach to overcome this limitation. Deployable modules typically exhibit high packaging ratios; however, the geometric deviations caused by residual strain, assembly tolerances, and dynamic coupling effects after deployment can significantly affect docking accuracy and structural stability, and may even lead to assembly failure. Nevertheless, existing studies have mostly focused on post-deployment final configuration accuracy optimization, with insufficient attention paid to the cooperative strategies between real-time deformation control and motion control during the assembly process. Moreover, a dynamic modeling method capable of accurately describing the coupling between variable-length flexible components and rigid bodies is still lacking. Therefore, how to achieve active configuration correction and coordinated position–attitude control of deployable modules on orbit has become a key challenge in the autonomous assembly of large space structures.