The invention provides a spacecraft thermal control design method based on a mechanical-thermal integrated structure. The spacecraft thermal control design method comprises the following steps that 1, a main body structure of a spacecraft is manufactured; and 2, spraying or mounting the main body structure by adopting a thermal control coating with low solar absorptivity and high infrared emissivity. The method has the beneficial effects that the low-solar-absorptivity and high-infrared-emissivity coating is designed at the required position of the spacecraft and is matched with the original conductive oxidation surface, and the equivalent solar absorptivity and infrared emissivity are formed by designing the area proportion and distribution of the low-solar-absorptivity and high-infrared-emissivity coating and the original conductive oxidation surface, so that the temperature level control of the whole spacecraft is realized; the influence of the orbit external heat flow on the spacecraft temperature is weakened; on the premise that an external heat conduction device does not need to be additionally arranged, the situation that the temperature gradient of the side with the large external heat flow and the side with the small external heat flow of the spacecraft is too large is effectively avoided through the high heat conductivity of the machine-heat integrated structure, use of a traditional multi-layer heat insulation assembly can be omitted, and the temperature index requirement of equipment in the spacecraft is met.
本发明提供了一种基于机热一体化结构的航天器热控设计方法,包括如下步骤:步骤1:制造航天器的主体结构;步骤2:通过采用低太阳吸收比、高红外发射率的热控涂层对主体结构进行喷涂或者贴装。本发明的有益效果是:本发明通过在航天器的需要位置设计低太阳吸收比高红外发射率涂层,与原表面导电氧化表面配合,通过设计两者的面积比例和分布形成等效的太阳吸收比和红外发射率,从而实现整星温度水平控制,实现轨道外热流对航天器温度影响减弱;在不需要增加外部导热装置的前提下,利用机热一体化结构较高的热导率有效避免航天器外热流较大一侧和外热流较小一侧的温度梯度过大的情况,可取消传统的多层隔热组件使用,满足航天器内部设备温度指标要求。
Spacecraft thermal control design method based on mechanical-thermal integrated structure
一种基于机热一体化结构的航天器热控设计方法
2024-03-15
Patent
Electronic Resource
Chinese
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