Precise prediction of rocket plume radiative heat flux is critical for reusable launch vehicle design. LandSpace researchers have developed a breakthrough computational method integrating the discrete transfer method (DTM) with wide-band k-distribution modeling. Validated against high-resolution benchmarks with ≤6.0% error, this approach achieves engineering-viable efficiency while quantifying base/sidewall radiative heating throughout flight profiles for nine-engine LOX/CH4 rockets – providing key insights for thermal protection system optimization.

From the precise movements of drone wings to the smooth opening of cabin doors, modern aircraft rely heavily on electro-mechanical actuation. But a hidden challenge – disruptive "multi-source disturbances" – can limit their performance, affecting everything from response time to positioning accuracy and efficiency. New research, focusing on a powerful control strategy called Active Disturbance Rejection Control (ADRC), aims to conquer these disturbances, paving the way for significant advancements in aviation safety and capability.

The number of satellites, especially those operating in Low-Earth Orbit (LEO), has been exploding in recent years. Additionally, the burgeoning development of Artificial Intelligence (AI) software and hardware has opened up new industrial opportunities in both air and space, with satellite-powered computing emerging as a new computing paradigm: Orbital Edge Computing (OEC). Compared to terrestrial edge computing, the mobility of LEO satellites and their limited communication, computation, and storage resources pose challenges in designing task-specific scheduling algorithms.

Shock wave/boundary layer interaction (SWBLI) has long been a challenge in compressible flow simulations due to its complex multi-scale and non-equilibrium characteristics. Particularly, the simulation of multi-scale SWBLI under near-space conditions poses significant challenges to traditional continuum models such as the Navier–Stokes (NS) equations. To address this, researchers employed a mesoscopic Discrete Boltzmann Method (DBM) to investigate the discrete effects and non-equilibrium behaviors in SWBLI which are beyond the NS description. Given that different interfaces such as temperature and density will provide different characteristic scales, correspondingly, will provide local Knudsen (Kn) numbers of different perspectives. From one perspective, the Kn number is increasing, but from another perspective, it may be decreasing. Therefore, the early understanding based on the definition of the Kn number from a single perspective was one-sided or even wrong. Therefore, researchers proposed the concept of the local Kn number vector: each component of it is a Kn number from one perspective. Based on the developed DBM theory and method, they discovered a series of kinetic features and new mechanisms in rarefied laminar SWBLI.

By focusing on adaptive aerodynamics, the ice-tolerance concept with variable drooping leading edge technology could revolutionize how planes handle icing skies. An ice tolerance solution based on the variable camber leading edge of iced wings is proposed, where the leading edge adapts its camber to counter ice effects. Compared with traditional aerodynamic design for ice tolerance, this concept not only strikes a balance between safety and functionality, but also boosts efficiency even under severe icing conditions.