Digital automatic flight control system with disparate function monitoring

• US 4,799,159 A
• Filed: 05/30/1985
• Issued: 01/17/1989
• Est. Priority Date: 05/30/1985
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Endrud, Douglas G., Davidson, Dale D.
• Primary Examiner(s): Lall, Parshotam S.
• Assistant Examiner(s): Black, Thomas G.
• Application Number:
  US06/739,583
• Time in Patent Office: 1,328 Days
• Field of Search: 364/550, 364/551, 364/434, 364/131, 364/138, 364/186, 364/184, 371/9, 371/36, 371/68
• US Class Current: 701/14
• CPC Class Codes: G05D 1/0077 using redundant signals or controls
• CPC Class Codes: G06F 11/16 Error detection or correction of the data by redundancy in hardware

Abstract

A channel of an automatic flight control system utilizes dual identical digital processors. Active task modules and monitor modules therefor are included in the processors. The active task modules and the monitor modules are arranged so that an active task module in one processor has a corresponding monitor module in the other processor where the corresponding modules perform disparate functionality over disjoint computation paths with respect to each other. The monitor module tests to determine if the aircraft is performing in a manner prohibited by the functionality controlled by the associated task module.

Claims

1. An automatic flight control system for aircraft having sensor means for providing sensor signals in accordance with flight conditions experienced by said aircraft and having aircraft control means responsive to aircraft control command signals for controlling said flight conditions of said aircraft and for providing flight condition control signals to control aircraft functions affecting said flight conditions, one channel of said automatic control system comprising:

digital computer means having computer input means responsive to said sensor signals and said flight condition control signals, program memory means, and computer output means;

computer input coupling means for coupling said sensor signals and said flight condition control signals to said computer input means;

computer output coupling means for coupling said computer output means to said aircraft control means for providing aircraft control command signals thereto;

said digital computer means having a program stored in said program memory means comprising a plurality of first program segments for execution by said digital computer means such that said digital computer means operates responsively to said sensor signals by performing a plurality of tasks to provide said aircraft control command signals, which control said aircraft functions, to said computer output means;

said program further including a plurality of second program segments, correspondingly associated with said first program segments and responsive to said sensor signals, for respectively monitoring performance of said first program segments;

each said second program segment performing a disparate task over mutually disjoint computation paths with respect to said corresponding first program segment, said disparate tasks are arranged to test if said aircraft is performing in a manner prohibited by said aircraft functions controlled by said corresponding first program segment;

means for controlling repeated iterations of said program; and

means for assuring that all of said second program segments are executed during each iteration of said program.

2. The system of claim 1 in which said computer means comprises first and second digital computers, each having computer input means responsive to said sensor signals, program memory means and computer output means,

each said first program segment being executed by one of said first and second digital computers with the corresponding second program segment being executed by the other of said first and second digital computers.

3. The system of claim 2 in which said assuring means comprises first and second assuring means for assuring that all of said second program segments stored in the program memory means of said first and second digital computers, respectively, are executed during each said iteration of said program.

4. The system of claim 3 further including disabling means, coupled to said first and second digital computers and to said first and second assuring means for disabling said aircraft control means in response to either said first digital computer, said second digital computer, said first assuring means or said second assuring means.

5. The system of claim 1 further including disabling means coupled to said computer means and to said assuring means for disabling said aircraft control means in response to either said computer means or to said assuring means.