This article includes the phases of conceptualization and validation of a picosatellite prototype named Simple-2 for remote sensing activities using COTS (Commercial-Off-The-Shelf) components and the modular design methodology. To evaluate its performance and ensure the precision and accuracy of the measurements made by the satellite prototype, a methodology was designed and implemented for the characterization and qualification of CanSats (soda can satellites) through statistical tests and techniques of DoE (Design of Experiments) based on CubeSat aerospace standards and regulations, in the absence of official test procedures for these kinds of satellite form factor. For the above, two experimental units were used, and all the performance variables of the different satellite subsystems were discriminated. For the above, two experimental units were used, and all the performance variables of the different satellite subsystems were discriminated against. These were grouped according to the dependence of the treatments formulated in thermal and dynamic variables. For the tests of the first variables, a one-factor design was established using dependent samples on each of the treatments. Then, hypothesis tests were performed for equality of medians, using nonparametric analysis of the Kruskal-Wallis variance. Additionally, multivariate analysis of variance was carried out for nonparametric samples (nonparametric multivariate tests), and the application of post hoc multiple-range tests to identify the treatments that presented significant differences within a margin of acceptability. To know the dynamic response and ensure the structural integrity of the satellite module, shock, oscillation, and sinusoidal tests were applied through a shaker. Having applied the experimental methodology to the different units, the results of a real experiment are illustrated in which a high-altitude balloon was used through the application of nonparametric regression methods. This experiment’s interest measured thermodynamic variables and the concentration of pollutants in the stratosphere to corroborate the operating ranges planned in the above experiments using on-flight conditions and estimate the TLR (technology readiness level) of future prototypes.

中文翻译：

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以CanSat规格评估卫星模块性能的实验方法，用于现场监测和遥感应用

本文包括概念化和验证阶段的概念，并验证了使用COTS（现成的商用）组件和模块化设计方法进行遥感活动的名为Simple-2的微卫星原型。为了评估其性能并确保由卫星原型进行的测量的准确性和准确性，设计了一种方法，并通过基于统计测试和DoE（实验设计）的技术对CanSat（苏打罐卫星）进行鉴定和鉴定。在没有针对此类卫星外形尺寸的官方测试程序的情况下，遵循CubeSat航空航天标准和法规。对于上述情况，使用了两个实验单元，并区分了不同卫星子系统的所有性能变量。对于以上内容，使用两个实验单元，并区分了不同卫星子系统的所有性能变量。根据在热和动态变量中制定的处理方法的依赖关系将它们分组。对于第一个变量的检验，在每个处理中使用依赖样本建立了一个单因素设计。然后，使用Kruskal-Wallis方差的非参数分析对中位数相等进行假设检验。此外，对非参数样本进行了多变量方差分析（非参数多变量检验），并应用了 对于第一个变量的检验，在每个处理中使用依赖样本建立了一个单因素设计。然后，使用Kruskal-Wallis方差的非参数分析对中位数相等进行假设检验。此外，对非参数样本进行了多变量方差分析（非参数多变量检验），并应用了 对于第一个变量的检验，在每个处理中使用依赖样本建立了一个单因素设计。然后，使用Kruskal-Wallis方差的非参数分析对中位数相等进行假设检验。此外，对非参数样本进行了多变量方差分析（非参数多变量检验），并应用了事后多范围测试以识别在可接受范围内存在显着差异的治疗。为了了解动态响应并确保卫星模块的结构完整性，通过振动器进行了冲击，振动和正弦测试。将实验方法应用于不同的单元后，说明了实际实验的结果，其中通过应用非参数回归方法使用了高空气球。该实验的兴趣是测量平流层中的热力学变量和污染物浓度，以在飞行条件下证实上述实验中计划的工作范围，并估算未来原型的TLR（技术准备水平）。