噪声与振动控制
譟聲與振動控製
조성여진동공제
NOISE AND VIBRATION CONTROL
2014年
3期
34-41
,共8页
李太平%姚煜中%李霖圣%程世祥
李太平%姚煜中%李霖聖%程世祥
리태평%요욱중%리림골%정세상
振动与波%动不平衡%静不平衡%转动%扰动%姿态
振動與波%動不平衡%靜不平衡%轉動%擾動%姿態
진동여파%동불평형%정불평형%전동%우동%자태
vibration and wave%dynamic imbalance mass%static imbalance mass%rotation%disturbance%attitude
高精度航天器对指向精度有极高的要求，飞轮是卫星姿态控制环节中不可或缺的执行部件，在研制和装备过程中，不可避免地具有微量的偏心或动不平衡，在姿态机动和稳定控制的过程中，飞轮的旋转会产生干扰力。将动静不平衡质量作为航天器的一部分，推导出完整航天器动力学姿态方程，进行动力学仿真，并根据完整的姿态动力学方程简化分析仿真结果。研究发现动静不平衡质量在飞轮高速转动时，对姿态均有影响，动不平衡质量对姿态的影响与安装位置关系很小，而静不平衡质量呈现线性关系，且两者对姿态的影响满足线性叠加。单轴转动时，指向精度的长周期变化只与飞轮的固有特性有关，与转速的大小无关。多轴转动时，姿态会振荡或发散，与初始相位有关；但对姿态的影响不满足单轴转动的叠加。
高精度航天器對指嚮精度有極高的要求，飛輪是衛星姿態控製環節中不可或缺的執行部件，在研製和裝備過程中，不可避免地具有微量的偏心或動不平衡，在姿態機動和穩定控製的過程中，飛輪的鏇轉會產生榦擾力。將動靜不平衡質量作為航天器的一部分，推導齣完整航天器動力學姿態方程，進行動力學倣真，併根據完整的姿態動力學方程簡化分析倣真結果。研究髮現動靜不平衡質量在飛輪高速轉動時，對姿態均有影響，動不平衡質量對姿態的影響與安裝位置關繫很小，而靜不平衡質量呈現線性關繫，且兩者對姿態的影響滿足線性疊加。單軸轉動時，指嚮精度的長週期變化隻與飛輪的固有特性有關，與轉速的大小無關。多軸轉動時，姿態會振盪或髮散，與初始相位有關；但對姿態的影響不滿足單軸轉動的疊加。
고정도항천기대지향정도유겁고적요구，비륜시위성자태공제배절중불가혹결적집행부건，재연제화장비과정중，불가피면지구유미량적편심혹동불평형，재자태궤동화은정공제적과정중，비륜적선전회산생간우력。장동정불평형질량작위항천기적일부분，추도출완정항천기동역학자태방정，진행동역학방진，병근거완정적자태동역학방정간화분석방진결과。연구발현동정불평형질량재비륜고속전동시，대자태균유영향，동불평형질량대자태적영향여안장위치관계흔소，이정불평형질량정현선성관계，차량자대자태적영향만족선성첩가。단축전동시，지향정도적장주기변화지여비륜적고유특성유관，여전속적대소무관。다축전동시，자태회진탕혹발산，여초시상위유관；단대자태적영향불만족단축전동적첩가。
High-precision spacecraft has very serious demands on pointing accuracy. The flywheel is an integral part of the execution units for satellite attitude control. In the research and development process, small eccentricity or dynamic imbalance is unavoidable. So, in the attitude maneuver and stability control process, rotation of the flywheel can cause interference forces. In this paper, taking the imbalance mass as a part of the spacecraft, the spacecraft attitude dynamic equations are conducted and the simulation is carried out. The simulation results are analyzed and illustrated. It is found that when the flywheel is rotating at high speed, the attitude of the spacecraft is essentially independent of the dynamic unbalance mass and its installation location, while it is linearly related to the static unbalance mass. When a single flywheel rotates, the long-period pointing accuracy depends on the inherent characteristics of the flywheel only, instead of its rotating speed. While multi-flywheels rotate, the attitude will oscillate or diverge, depending on the initial phase. Furthermore, effect of the multi-flywheels rotating does not mean the superposition of the influences of single-flywheel’s rotating.
