239000003550 marker Substances 0.000 claims abstract description 70.BERNARD Application granted granted Critical Publication of US5358199A publication Critical patent/US5358199A/en Anticipated expiration legal-status Critical Status Expired - Fee Related legal-status Critical Current Links Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.) Filing date Publication date Application filed by Rockwell International Corp filed Critical Rockwell International Corp Priority to US07/947,026 priority Critical patent/US5358199A/en Assigned to ROCKWELL INTERNATIONAL CORPORATION reassignment ROCKWELL INTERNATIONAL CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST. Original Assignee Rockwell International Corp Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.) Case Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.) Expired - Fee Related Application number US07/947,026 Inventor E.
#AUTOMATIC FLIGHT CONTROL SYSTEM KNOWS WHERE IT IS PDF#
Google Patents Automatic flight control system having unified graphic mistrim indicatorĭownload PDF Info Publication number US5358199A US5358199A US07/947,026 US94702692A US5358199A US 5358199 A US5358199 A US 5358199A US 94702692 A US94702692 A US 94702692A US 5358199 A US5358199 A US 5358199A Authority US United States Prior art keywords flight control mistrim control system aircraft aileron Prior art date Legal status (The legal status is an assumption and is not a legal conclusion. Google Patents US5358199A - Automatic flight control system having unified graphic mistrim indicator Within the scope of certain simplifications the design engineer prescribes eigenvalues of the entire system in a straight forward manner.US5358199A - Automatic flight control system having unified graphic mistrim indicator The structure of the system is characterized by 1 a mixture of feedforward and feedback control thus allowing to separate the design of the command and disturbance characteristics and 2 decoupling speed-and height loop.
This paper describes the structure of an integrated control system and the appropriate parameter design method using the AIRBUS A300 as an example. Nevertheless the appropritate control system design method should be able to incorporate proven structures. With the advent of the Flight Management Computer FMC with its flight profile management capability and accompanying new control modes such as the PROFILE-mode the integrated AFCS becomes a must. In order to obtain optimal flight guidance results one should use an integrated design which should reflect the coupled nature of such variables as airspeed and vertical speed. Abstract: Existing Automatic Flight Control Systems for civil and military aircraft mostly use separate subsystems with a very limited amount of communication between the black boxes.
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