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为了研究喷管型面对小推力火箭发动机推力性能的影响,设计并建设了双喷管差动式小推力测量装置及其附属设备。在测量装置中,基准喷管和待测喷管同轴反向设置,通过测量结构应变来直接测量两个喷管的推力差。对测量装置进行了简化模型理论分析,导出其灵敏系数理论公式。依据该公式进行关键参数设计,确定合理的灵敏系数,指导试验系统设计,以保证测量精度。验证性试验表明测量装置可以测量牛级推力差,标定曲线线性较好,以基准喷管推力作为比较对象,推力差的相对扩展不确定度为0.5%。推力差与基准喷管推力的比值越小,以基准喷管推力为比较对象的相对测量不确定度越小。测量装置可以用于小推力火箭发动机喷管性能分析及优化的试验研究。
In order to study the influence of nozzle type on the thrust performance of small thrust rocket engine, a double nozzle differential small thrust measurement device and its ancillary equipment were designed and constructed. In the measuring device, the reference nozzle and the nozzle to be tested are arranged in the opposite direction on the same axis, and the thrust difference between the two nozzles is directly measured by measuring the structural strain. The measurement device is simplified model theory analysis, derived its theoretical formula of sensitivity coefficient. According to the formula for the key parameters of the design, to determine a reasonable sensitivity coefficient, guide the design of test systems to ensure measurement accuracy. The confirmatory test shows that the measuring device can measure the difference of the cow-level thrust, and the calibration curve has a good linearity. Compared with the reference nozzle thrust, the relative expansion uncertainty of the thrust difference is 0.5%. The smaller the ratio of the thrust difference to the reference nozzle thrust, the smaller the relative measurement uncertainty with respect to the reference nozzle thrust. The measuring device can be used to analyze the performance of small thrust rocket engine nozzle and optimize the experimental research.