CAJ | 학술논문

针对卫星天线承力筒轻质、高轴向模量、低轴向热膨胀的需求，文章开展了承力筒总体成型方案设计、材料基础热力学性能测试及产品试制等工作，并通过了实验考核。结果表明：对于材料的热力学性能，按经纬向比例1︰2编织的M40J炭布层压板在常温下纬向拉伸模量为118GPa，纬向拉伸强度为771MPa；在(-190~150)℃范围内，纬向热膨胀系数为(0.3~1.4)×10-6℃-1，经向热膨胀系数为(0.3~5.3)×10-6℃-1。该复合材料承力筒比铝质承力筒质量减少40%以上。复合材料承力筒经过(-170~120)℃/24h、6.5个循环的高低温循环实验考核，产品无残余变形，内部未出现开裂、分层等现象。
침대위성천선승력통경질、고축향모량、저축향열팽창적수구，문장개전료승력통총체성형방안설계、재료기출열역학성능측시급산품시제등공작，병통과료실험고핵。결과표명：대우재료적열역학성능，안경위향비례1︰2편직적M40J탄포층압판재상온하위향랍신모량위118GPa，위향랍신강도위771MPa；재(-190~150)℃범위내，위향열팽창계수위(0.3~1.4)×10-6℃-1，경향열팽창계수위(0.3~5.3)×10-6℃-1。해복합재료승력통비려질승력통질량감소40%이상。복합재료승력통경과(-170~120)℃/24h、6.5개순배적고저온순배실험고핵，산품무잔여변형，내부미출현개렬、분층등현상。
AbstractAccording to the demands of light-weight, high axial modulus and low axial thermal expansion, a general process project design, thermodynamics properties test of material, and product manufacture have been carried out. And the product has been checked through experiment. As a result, we get the following thermodynamic properties of material. With regard to M40J carbon cloth laminate that is braided as 1︰2 proportion in warp and weft directions, the tension modulus and strength are 118GPa and 771MPa in weft direction in room temperature respectively; thermal expansion coefficients are between 0.3×10-6℃-1 and 1.4×10-6℃-1 respectively direction and between 0.3×10-6℃-1 and 5.3×10-6℃-1 in warp direction in (-190~150)℃, respectively. All-composite bearing cylinder is lighter above 40% than aluminum bearing cylinder. The bearing cylinder experienced the high & low temperature experiment with the conditions of (-170~120)℃/24h and 6.5 cycles. In the end, the product has no residual deformation, no cracking and no delamination.