CAJ | 학술논문

为了满足空间载荷在发射阶段的复杂动力学特性要求,并满足入轨之后的解锁分离,设计了一种爆炸螺栓驱动的包带式解锁支座,并对其进行了受力分析和爆炸螺栓拧紧力矩加载分析。建立了包带与支座的接触有限元模型,进行了预紧力加载分析和轴向拉伸载荷分析。由分析结果可知,包带上的应力分布沿着远离夹紧区域的方向逐渐减小,同时啮合区域的摩擦因数越大,包带的最大应力越小。分析了两种故障模式及其处理措施。振动试验表明：3个方向的均方根加速度放大倍率都很小,其一阶模态全部大于200 Hz,满足刚度和承载能力要求；同时该装置解锁可靠性高,具有良好的冲击响应衰减特性。
위료만족공간재하재발사계단적복잡동역학특성요구,병만족입궤지후적해쇄분리,설계료일충폭작라전구동적포대식해쇄지좌,병대기진행료수력분석화폭작라전녕긴력구가재분석。건립료포대여지좌적접촉유한원모형,진행료예긴력가재분석화축향랍신재하분석。유분석결과가지,포대상적응력분포연착원리협긴구역적방향축점감소,동시교합구역적마찰인수월대,포대적최대응력월소。분석료량충고장모식급기처리조시。진동시험표명：3개방향적균방근가속도방대배솔도흔소,기일계모태전부대우200 Hz,만족강도화승재능력요구；동시해장치해쇄가고성고,구유량호적충격향응쇠감특성。
In order to meet the requirements of complicated kinetics during the launch phase of space payload,and to realize separation between payload and satellite after in orbit,a separable clamp-band supporting structure was designed.The separation was driven by explosive bolts,and the rela-tion between axial force of the bolts and tightening torque was analyzed.The contact model of finite-element for the structure was established and then the analyses for pre-tightening force and axial load-ing were conducted respectively.The analyses show that the stress in the bands decreases gradually a-way from the tightened bolts,the larger the coefficient of friction of the contact region,the smaller with maximum stress of clamp band.Two failure modes were analyzed.The results of the vibration show RMS acceleration magnification in three directions is very small,all of the first-order modes are greater than 200 Hz,which meets the requirements of stiffness and load capacity,the device is un-locked with high reliability,and have good attenuation characteristics of impulse response.