Forced Landing Flight Test of Compound-Wing UAVs Based on Proportional Guidance

With the development of the low-altitude economy, the demand for low-altitude flight missions has steadily increased. However, such flights often encounter special circumstances requiring emergency landings. To address this, a forced landing guidance law is designed in this paper, using a small compound-wing aircraft as the research object and based on proportional guidance principles. The guidance law calculates lateral and longitudinal acceleration commands using azimuth and elevation angles provided by a seeker, which are then input into the inner-loop control law to generate control surface commands. These commands guide the aircraft toward a nearby landing point. Hardware-in-the-loop simulations demonstrate the effectiveness and robustness of the proposed guidance law, and flight tests further validate its practical applicability.