A methodology for constructing the aircraft design schema

Aircraft collaboration design is based on a unified set of schemas containing data and model representations and interfaces across disciplines. The aircraft design schema is a central data model that specifies the paradigm for the representation of a full lifecycle model of aircraft design. The construction of the schema currently lacks theoretical guidance. This paper designs a novel methodology to construct the aircraft design schema, a fully functional, logical, and self-consistent methodology. The methodology defines a schema matrix that includes implementation strategies, principles, processes, meta-object facility, views, scenarios, and products. The aircraft conceptual design schema is constructed according to the methodology, which is a hands-on approach to help understand the concept and implementation. The features of the methodology are analyzed, and the methodology and the aircraft conceptual design schema are presented to address the pain points of multiple solution trade-offs, multiple iterations, and multidisciplinary coupling in aircraft conceptual collaboration design.     

航空发动机典型材料超高周疲劳试验技术研究综述

航空发动机作为飞行器最关键、最核心的部位，长期服役于高温、高载等极端环境，疲劳失效是导致发动机结构破坏的主要原因之一。随着工业的发展，发动机材料的超高周疲劳问题日益凸显。本文总结了发动机典型材料超高周疲劳关注领域的研究现状，对当前超高周疲劳试验技术的应用情况进行了阐述，包括超高周轴向振动疲劳、弯曲振动疲劳、扭转振动疲劳、复合振动疲劳等试验加载技术以及温度控制技术、损伤监测技术，并对我国航空发动机典型材料超高周疲劳试验技术的发展做出展望。     

Martian Buildings: Design loading

Multiplanetary life has been studied by scientists as a way to supply energy or sustain human life in the future. Mars is likely to be man’s first destination, colonization using onsite structural construction would be one of the main options. The first step to designing a reliable building is to know the applied structural loads and to have an accurate design load combination. Due to lack of complete knowledge, short span of recorded data, Martian environment, and hazardous environment that Martian structures face, constructed Martian structures should behave appropriately under the highest likely live, dead and environmental loads either simultaneously or as a worst-case scenario. The present study evaluated and calculated probable Martian structural loads, including live, internal pressure, snow, gravity (dead), dust accumulation, thermal stress, wind, marsquake, asteroid, and meteoroid impact loads and their effects. Information was gathered from previous studies and valid data from Martian landers, rovers and orbiters. Wind loads were calculated based on the over 6.5 years of data recorded by Vikings 1 and 2, temperature and winds for InSight (TWINS) sensor. A wind shear exponent and wind profile have been proposed for a Martian flat terrain construction site. Marsquake lateral loads, frequency content and seismicity were assessed using data from the seismic experiment for interior structure (SEIS) and the Viking 2 seismometer. Considering the high influx of micrometeoroids, their penetration distance, impact loads and their effects on structures were calculated. The annual probability of an asteroid impact on a settlement was assessed for a 30-year mission. A load map for Martian residential buildings that considers the worst-case scenario in which a Martian structure should be designed based on them has been proposed.