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在发射的主动上升段,由于天线罩突出卫星密封舱表面,天线罩将承受气流冲刷作用,为了准确设计天线罩抗力学环境,需要对上升段天线罩的受力情况进行详细计算和分析。根据具体的弹道参数,卫星上升过程中最大动压对应的马赫数约为1.4,基于此选择动压最大的马赫数段(Ma=1.0~1.8),采用数值模拟方法详细计算分析了定常状态下天线罩在不同马赫数、不同迎角下的气动力载荷和力矩载荷。结果表明:随着马赫数的增加,天线罩所承受的气动力载荷和力矩载荷均表现为先增大后减小,最大气动力载荷出现在Ma=1.2,大小约为435.5N,最大力矩载荷出现在Ma=1.4,大小约为14.5Nm;随着迎角的增加,天线罩气动力载荷呈现增大趋势,但增幅较小。在实际飞行中天线罩的局部或全部已经淹没在火箭弹身的边界层中,因此弹身的存在对天线罩的迎角效应会产生影响。
During the active rising stage of launch, the radome will withstand the air scouring effect due to the protruding of the radome over the surface of the satellite ceilometer. In order to accurately design the radome’s resistance environment, the force of the radome in the ascending section needs to be calculated and analyzed in detail. According to the specific ballistic parameters, the Mach number corresponding to the maximum dynamic pressure during satellite ascent is about 1.4. Based on this, the Mach number with the highest dynamic pressure is selected (Ma = 1.0 ~ 1.8), and the numerical simulation is used to calculate and analyze the steady- Aerodynamic loads and moment loads of radome at different Mach numbers and different angles of attack. The results show that with the increase of Mach number, the aerodynamic and moment loads of the radome increase first and then decrease, the maximum aerodynamic load appears at Ma = 1.2, the size is about 435.5N, the maximum moment load Appeared in Ma = 1.4, the size of about 14.5Nm; with the angle of attack increases, the aerodynamic load on the radome shows an increasing trend, but the increase is small. In actual flight, part or all of the radome has already been submerged in the boundary layer of the rocket body, so the existence of the elastic body has an impact on the angle of attack effect of the radome.