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导弹以超音速飞行时,结构外表面的温度可达几百度,因此在正式飞行前,一定要做模拟飞行时表面温度的地面热试验。这种试验可以采用三种方法来进行。一是温度控,即是用飞行时结构表面的真实温度T_1曲线作为地面热试验的控制参数。二是热流控,即是用飞行时结构表面所接受的热流q曲线作为地面热试验的控制参数。三是公式控,即是用飞行时结构表面处的绝热壁温T_(AW)曲线和对流换热系数α曲线作为地面热试验的控制参数(T_1、q、T_(AW)和α通过外热源计算可以得到)。温度控简单、方便、容易实现,对物性参数稳定、受热后不分层的材料适用。热流控对物性参数稳定、具有烧蚀性的材料适用。公式控对物性参数不稳定、受热后易分层的材料适用。但此方法调试复杂、不易实现。天线罩的材料是玻璃钢,它的物性参数是温度的函数、不稳定、受热时易分层,采用公式控进行地面热试验较合适,从而使试验成功。
Missile supersonic flight, the structure of the outer surface of the temperature up to several hundred degrees, so before the official flight, must be done to simulate the surface temperature of the ground flight thermal test. This test can be carried out using three methods. First, the temperature control, that is, the real structure of the flight surface temperature T_1 curve as the ground thermal control test parameters. The second is the heat flow control, that is, the heat flux q curve accepted by the structure surface during flight as the control parameter of the ground thermal test. The third is the formula control, that is to say, using the T_ (AW) curve of the adiabatic wall temperature and the α curve of the convection heat transfer coefficient as the control parameters of the ground thermal test (T_1, q, T_ (AW) Calculation can be obtained). Temperature control is simple, convenient, easy to implement, the stability of the physical parameters, the material is not stratified after heating apply. Heat flow control of the physical parameters of stability, with ablative material applicable. Formula control of the physical parameters are unstable, easy to delaminate after heating materials apply. However, this method of debugging complex and difficult to achieve. Radome material is FRP, its physical parameters is a function of temperature, unstable, easily delaminated when heated, the use of formula control of the ground thermal test is more appropriate, so that the test was successful.