CAJ | 학술논문

在常规测力风洞试验中，测量天平可以测量出飞行器的气动力和对飞行器质心的气动力矩，按照常规的压力中心计算方法，求得的压力中心位置为气动力作用线与飞行器纵轴的交点，而不是飞行器真实压力中心的准确位置。针对再入飞行器风洞试验常规压心测量无法反映压心确切位置的问题，通过攻角连续变化和数据实时采集技术对再入飞行器压力中心进行了研究，得到了飞行器压力中心具体位置的测量与计算方法，以及其随攻角变化的变化规律。结果表明，得到的计算方法可以准确得到再入飞行器的压心位置。同时还导出了 CN 和 CA 分别对飞行器质心产生的俯仰力矩大小的影响：随着攻角的负向增加，CA 对 Cm 的贡献逐渐增加，CN 对 Cm 的贡献逐渐减小，压力中心实际轴向位置和常规计算值中压力中心和纵轴交点位置的差量逐渐增大，而压力中心的法向坐标值并不大；对于再入飞行器，CA 对 Cm 的贡献很大，不能忽略或简化。
재상규측력풍동시험중，측량천평가이측량출비행기적기동력화대비행기질심적기동력구，안조상규적압력중심계산방법，구득적압력중심위치위기동력작용선여비행기종축적교점，이불시비행기진실압력중심적준학위치。침대재입비행기풍동시험상규압심측량무법반영압심학절위치적문제，통과공각련속변화화수거실시채집기술대재입비행기압력중심진행료연구，득도료비행기압력중심구체위치적측량여계산방법，이급기수공각변화적변화규률。결과표명，득도적계산방법가이준학득도재입비행기적압심위치。동시환도출료 CN 화 CA 분별대비행기질심산생적부앙력구대소적영향：수착공각적부향증가，CA 대 Cm 적공헌축점증가，CN 대 Cm 적공헌축점감소，압력중심실제축향위치화상규계산치중압력중심화종축교점위치적차량축점증대，이압력중심적법향좌표치병불대；대우재입비행기，CA 대 Cm 적공헌흔대，불능홀략혹간화。
In conventional force measure wind tunnel test,the balance can get the aerodynamic force of the aircraft and also the directly moment .It is while the pressure center is usually considered as the intersec-tion point between aerocraft's longitudinal axis and its aerodynamic force,which is not the virtually real value of the pressure center of the aircraft.How to obtain the pressure center of re-entry aerocraft accurately with the general method in wind tunnel test remains a difficult problem.In this paper,the position of re-entry ve-hicle’s pressure center was obtained through the technique of attack angle continuous change and real-time data acquisition.Also the pressure center of re-entry module change rule with the change of attack angle was obtained.Experiments demonstrated the feasibility of the proposed method.With the increasing of negatives attack angle,the contribution of axial force to pitch moment becomes great,while the influence of normal force is just the contrary,which results in thickcreased gap between the conventional measured value and the real value of vehicle’s center of pressure.The vertical position of re-entry aircraft’s load center is relatively small in the test.The final CA-Cm curve shows that the axial force CA should not be neglected or simplified in wind tunnel test.