The “cubesat” form factor (multiples of 10 × 10 × 10 cm³ volume and 1.33 kg mass) has been adopted as the defacto standard for a cost effective and modular, nano-satellite platform. Many commercial options exist for nearly all components required to build such satellite; however, there is a limited range of thruster options that suit the power and size restrictions of a cubesat. This work presents the design, implementation and direct thrust measurements of a proof of concept cubesat cold gas thruster system using naphthalene (C₁₀H₈) as the propellant. The proposed design is optimized for simplicity to match the requirement of entry level cubesat missions, yet, due to the properties of naphthalene, it can achieve a total impulse in the order of tens of newton-seconds.

“立方体”形状因数（10×10×10的倍数 厘米³卷和1.33公斤质量）已被用作事实上的标准，用于具有成本效益的模块化纳米卫星平台。建造这种卫星所需的几乎所有组件都有许多商业选择；但是，推进器选件的范围有限，无法满足cubesat的功率和大小限制。这项工作介绍了使用萘的冷气推进器系统的概念验证立方的设计，实施和直接推力测量（C₁₀H₈）作为推进剂。提议的设计经过优化，以简化操作，以适应入门级立方体任务的要求，但是，由于萘的性能，它可以实现数十牛顿秒量级的总脉冲。