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The Effect of a Buoyancy Gradient on the Longitudinal Flight Dynamics of a Superpressure Airship

机译:浮力梯度对超压飞艇纵向飞行动力学的影响

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Some stratospheric airships have been designed to operate routinely above their pressure height. These superpressure airships are intended to fly at altitudes of 60,000 ft MSL or even higher. One outcome of operating above pressure height is that an airship's weight remains approximately constant while its buoyancy varies with altitude. This effect has not been included in the linearized longitudinal equations of motion that have been applied to airships. In this paper, linearized equations governing the two-degree-offreedom longitudinal motion of a superpressure airship are derived. These equations contain additional terms that involve the rate of change of airship buoyancy with altitude. The characteristic equation of the airship's motion is also provided. Due to the additional buoyancy terms, the degree of the characteristic equation increased from 3 to 4. This means that the airship's motion changed from 1 nonoscillatory mode and 1 oscillatory mode to a more complicated motion. As an example, the roots of the characteristic equation are determined as a function of airspeed for the High Altitude Superpressure Powered Aerostat (HASPA) which was designed, constructed, and tested during the 1970s. Predicted time histories of the airship's vertical displacement, angle of attack, pitch angle, and pitch rate are also presented. At low airspeeds, the airship's motion consisted of 2 oscillatory modes. At higher airspeeds, the motion changed to 2 nonoscillatory modes and 1 oscillatory mode. At all airspeeds, one of the oscillatory modes was nearly identical to the pendulum mode that occurs when the buoyancy gradient is not included. At 63% of the airship's maximum airspeed, one of the nonoscillatory modes became unstable. A formula is derived that can be used to estimate the airspeed at which a superpressure airship will become longitudinally unstable. Also, a controls-fixed longitudinal stability criterion is developed for superpressure airships.
机译:一些平流层飞艇经设计可在其压力高度以上正常运行。这些超压飞艇旨在在60,000英尺MSL甚至更高的高度飞行。在高于压力高度的情况下运行的一个结果是,飞艇的重量保持大致恒定,而其浮力随高度而变化。应用于飞艇的线性运动纵向方程式中未包含此效应。本文推导了控制超压飞艇的两自由度纵向运动的线性方程。这些方程式包含其他术语,这些术语涉及飞艇浮力随高度的变化率。还提供了飞艇运动的特征方程。由于附加的浮力项,特征方程的阶数从3增加到4。这意味着飞艇的运动从1种非振荡模式和1种振荡模式变为更为复杂的运动。例如,对于1970年代设计,建造和测试的高海拔超压动力浮空器(HASPA),将特征方程的根确定为空速的函数。还介绍了飞艇的垂直位移,迎角,俯仰角和俯仰率的预测时间历史。在低空速下,飞艇的运动由2种振荡模式组成。在更高的空速下,运动更改为2种非振荡模式和1种振荡模式。在所有空速下,一种振荡模式几乎与不包括浮力梯度时发生的摆模式相同。在飞艇最大空速的63%时,一种非振荡模式变得不稳定。得出一个可以用来估计超压飞艇将在纵向上变得不稳定的空速的公式。此外,还为超压飞艇开发了一种由控制系统确定的纵向稳定性标准。

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