Analog simulation of automatic glide slope control using wing lift spoilers as direct lift control

摘要

The use of wing lift spoilers as a means of changing liftwithout changing angle of attack was studied for use in thelanding approach task. The vehicle used was the F-8 type fighter.Automatic glide slope controllers were proposed using £.n elevatorglide slope coupler in conjunction with an automatic powercompensator for comparison with an automatic direct lift controlsystem. The system gains were optimized for gust disturbancesand initial offsets from glide slope. An analog computer simulationprogram including a manual control phase was used to determinearbitrary measures of effectiveness of the proposed systems.