This paper proposes an innovative structural system for deep-space spacecraft, which breaks through the traditional compact integrated design paradigm of aerospace vehicles. Aiming at the critical pain points of insufficient thermal control efficiency, high safety risks, poor impact resistance and high construction cost existing in conventional spacecraft for long-term deep-space residence and cislunar transportation missions, this research designs a three-layer nested hollow-interlayer spacecraft structure combining a modular cubic cage skeleton and a free-form multi-curved outer protective shell. The core innovation lies in adopting a square-framed inscribed circular standard unit to construct the rigid load-bearing cage skeleton, realizing high-standardization and high-stiffness structural assembly; the large-scale hollow interlayer is set to realize multi-functional integration of impact energy buffering, thermal zoning, pipeline layout and maintenance space; the high-heat and high-risk power components are arranged externally near the outer shell, achieving efficient direct radiative heat dissipation to deep-space vacuum and complete safety decoupling from core payloads. In addition, the multi-layer inclined curved thin-shell protection scheme and the impact-adaptive convex shape evolution mechanism are proposed, which greatly improve the spacecraft's survivability under constrained mass, and the system also has high feasibility of lunar in-situ resource utilization and construction. This research provides a brand-new theoretical basis and engineering design scheme for the development of long-life, high-safety and low-cost deep-space and cislunar transportation spacecraft, and has important reference significance for the design of next-generation aerospace vehicles.
Min Li (Wed,) studied this question.