The use of wing lift spoilers as a means of changing lift without changing angle of attack was studied for use in the landing approach task. The vehicle used was the F-8 type fighter. Automatic glide slope controllers were proposed using £.n elevator glide slope coupler in conjunction with an automatic power compensator for comparison with an automatic direct lift control system. The system gains were optimized for gust disturbances and initial offsets from glide slope. An analog computer simulation program including a manual control phase was used to determine arbitrary measures of effectiveness of the proposed systems.

http://archive.org/details/analogsimulation1094511586

Lieutenant, United States Navy