The Mathworks, Inc.

Honeywell G.m.b.h.

Honeywell International Inc.

William F Potter

Larry James Yount

Jesung Kim

Ebrahim Mehran Mestchian

William James Aldrich

Xiaocang Lin

Justin Scott Shriver

Kai Tuschner

Partha Biswas

Jeffrey W Hegg

Byron F Birkedahl

Dale D Davidson

Zsolt Kalmar

Willard Ahart Blevins

Chirag Gupta

Alan Bruce Hickman

Yuchen Zhang

Anjali Dattatray Joshi

Mario Bambagini

Aaron Hughes

Dixin Zhou

Systems and methods determine tight Worst Case Execution Time (WCET) for a simulation model or code generated for a model. Composite code blocks may be constructed from basic code blocks of an in-memory representation of the model. Information on the model and its elements may be obtained and utilized to construct the composite code blocks. The composite code blocks may be instrumented and execution times may be measured for the composite code blocks. The execution times for the composite code blocks along paths through the model may be summed and the highest total execution time may be presented as the WCET for the model and/or the code generated for the model.

Systems and methods for performing worst-case execution time analysis of simulation models

Systems and methods for coverage analysis using context information are described. The systems and methods can be used to obtain program code and test information for testing the program code, the test information associated with context information for providing context for testing the program code. Coverage information can be generated by testing the program code according to the test information. A first association can be generated between the context information and the test information. A second association can be generated between the context information and the program code. A third association can be generated between the coverage information and the test information. A subset of the coverage information can be determined based on the third association and a fourth association between the test information and the program code determined based on the first and second associations. An indication of the subset of the coverage information can be displayed.

Refining coverage analyses using context information

A system associates at least one review indicator with at least one of multiple elements of a model, where the at least one review indicator indicates whether a corresponding element of the model has or has not been reviewed by a reviewer. The system further displays a status of the at least one review indicator in a user interface.

Marking up objects in code generation

A computer-readable medium and method may include instructions for providing a graphical model in a computing environment, where the graphical model includes a plurality of graphical affordances. Generated code may be provided based on the graphical model, where the generated code includes a plurality of code segments. A traceability report may be generated based on the graphical model and the generated code, wherein the traceability report includes a mapping of the plurality of code segments to corresponding ones of the plurality of graphical affordances. The traceability report may be stored.

Traceability in a modeling environment

Methods and apparatus are provided for more reliably transferring operational control for various aircraft flight control surfaces from a first sub-system to a second sub-system. The present invention provides an Actuator Control Electronics (ACE) wrap-back module that monitors the output of the normal mode control module and switches control to the direct control module based upon the detection of an error condition. The switching function is controlled by a monitoring system that monitors the output from an integrated heartbeat module that emits a pre-programmed signal. The pre-programmed signal is encoded and sent over a communication bus where it is then decoded and validated by comparing the decoded signal to the expected results. Any irregularity in the heartbeat signal automatically triggers a change of control from the first flight control sub-system to the second flight control sub-system.

Methods and apparatus for error-tolerant wrap-back ACE monitor

A self adaptive limiter for use in aircraft control systems during approach and landing is disclosed. Estimated flight path angle is continuously computed during the glidepath tracking phase until a predetermined lock altitude above ground when a nominal flight path angle is latched. Nominal vertical speed is continuously computed below the lock altitude as a function of the latched nominal flight path angle and ground speed of the aircraft. A vertical speed limit function is generated as a function of the nominal vertical speed and radio altitude. During approach and landing a pitch limit is computed from the vertical speed limit, vertical speed, ground speed, and pitch. When a pitch command to the autopilot exceeds the pitch limit(i.e. commands excessive pitch down attitude), it is limited to the pitch limit thus preventing the aircraft from descending below a safe altitude. The invention is self-adaptive since the pitch limit varies in response to changes in the ground speed of the aircraft, wind, and ILS beam angles.

Self adaptive limiter for automatic control of approach and landing

A hand controller system which provides the proper feel of the hand controller during aircraft operation. In both non-redundant and redundant embodiments, torque, and position measurements are made from the hand controller movements and processed to provide a feedback to a control motor in mechanical connection with the hand controller. The system includes self-monitoring of the motor, as well as the signals provided by the position, and torque sensors. Connections are provided from the hand controller system so that cross-coupling may be provided between the pilot's and copilot's hand controllers.

Active hand controller redundancy and architecture

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Glendale, AZ, United States of America

William F Potter