CAJ | 학술논문

在火箭结构的飞行动态载荷响应测量中，受到箭体结构的限制，某些情况下无法采用正交布置的测点来测量截面的弯矩载荷。提出采用非正交测点来测量箭体结构截面载荷的方法，并给出3种载荷标定与灵敏度计算方法。通过地面静力试验标定，表明该方法线性度良好，可以用于结构的测量。最后给出这种方法在实际飞行载荷测量中的应用，确定了3种测量方法的优劣。
재화전결구적비행동태재하향응측량중，수도전체결구적한제，모사정황하무법채용정교포치적측점래측량절면적만구재하。제출채용비정교측점래측량전체결구절면재하적방법，병급출3충재하표정여령민도계산방법。통과지면정력시험표정，표명해방법선성도량호，가이용우결구적측량。최후급출저충방법재실제비행재하측량중적응용，학정료3충측량방법적우렬。
Orthogonal measure points are not available, sometimes, when measuring dynamic load in flight for launch vehicle. In order to obtain sectional load of a launch vehicle, a new kind of strain measure point placing method is proposed. Non-orthogonal measure points are taken to obtain sectional load. Three sensitivity scaling means are presented and the methods of how to calculate the sectional load are given also. Static experiment is done, and linear relationship is clear between load and strain. That is to say that the method is good enough to be used in structural load measurement. The proposed method is applied in load measurement during flight. The difference between the three load calculating methods is analyzed approximately.