Computer simulation of a pilot in V/STOL aircraft control loops. Appendix II, The optimal control model of a pilot in V/STOL aircraft control loops

Original publisher: Cleveland, OH : NASA Lewis Research Center, [1989] OCLC Number: (OCoLC)67142666 Excerpt: ... PLOT LISTINGS-continued Plot B. 1.-16.-Roll angle perturbation of the Harrier AV-8B due to an impulse of the lateral stick 187 Plot B. 1.-17.-Lateral acceleration of the Harrier AV-8B due to an impulse of the 187 rudder pedals. Plot B. 1.-18.-Yaw rate response of the Harrier AV-8B due to an impulse of the 188 rudder pedals.in a near hover. Plot B. 2.-1.-Short period dynamics of the Harrier AV-8B pitch rate response due 188 to an impulse of the longitudinal stick in a near hover. Plot B. 2.-2.-Short period dynamics of the Harrier AV-8B forward velocity due to 189 a 5 degree impulse of the nozzle angle at a near hover. Plot B. 2.-3.-Short period response of the Harrier AV-8B vertical rate due to an 189 unpulse of the throttle at a near hover. Plot B. 2.-4.-Short period response of the Harrier AV-8B en_ne speed due to an L 190 Impulse of the throttle. Plot B. 2.-5.-Short period dynamics of the Harrier AV-8B roll rate due to an 190 u'npulse of the lateral stick at a near hover. Plot B. 2.-6.-Short period dynamics of the Harrier AV-8B yaw rate due to an 191 _mpulse of the lateral stick at a near hover. m Plot B. 2.-7.-Short period response of the Harrier AV-8B yaw rate due to an 191 _mpulse of the rudder pedals at a near hover. Plot B. 2.-8.-Short period response of the Harrier AV-8B roll rate due to an 192 impulse of the rudder pedals at a near hover. xiv