超低空飞行的航空拖靶需要高精度的高度控制,而作为试验和训练的消耗性装备,其低成本设计要求使得航空拖靶不能采用常规飞行器的高度控制方法。针对以拖曳力为飞行动力的航空拖靶,研究其基于非姿态控制的定高飞行的运动特性。定高飞行航空拖靶采用高稳定性的气动布局,并基于准直接力控制的升降舵面进行高度调整操纵。通过建立拖靶的纵向运动数学模型,设计非姿态控制定高飞行控制方法,详细分析拖靶气动特性,并进行定高飞行控制的仿真计算。计算结果给出拖靶的高度控制能力及飞行状态,结果表明拖靶具有一定的高度调整能力,可以实现定高飞行。 Air-borne towing targets at very low altitude require high-precision altitude control, and as a costly test and training consumable, their low-cost design requirements make the towing target less capable of using conventional aircraft altitude control methods. Aiming at the dragging force of airborne dragging target, the motion characteristics of the fixed altitude flight based on non-attitude control are studied. Set high flying air drag target with high stability of the pneumatic layout, and based on the collimation direct control of the elevator surface height adjustment operation. By establishing the mathematical model of longitudinal movement of dragging target, the method of non-attitude control flying height control is designed, the aerodynamic characteristics of drag target are analyzed in detail, and the simulation calculation of flying height control is carried out. The result of the calculation shows the height control ability of the towing target and the flight status. The result shows that the towing target has a certain degree of height adjustment and can achieve the high altitude flight.