Model version | 1.91 |
Author | bpotter |
Last saved | Thu Oct 15 20:57:32 2020 |
Default parameter behavior | inlined |
Block reduction | forced off |
Conditional branch optimization | on |
Analyzed model | ActuatorControl |
Logic block short circuiting | off |
Test# | Started execution | Ended execution | Description |
Test 1 | 15-Oct-2020 23:29:16 | 15-Oct-2020 23:29:34 | This model represents a flight control system for a helicopter that controls pitch attitude, roll attitude and yaw rate based on pilot inputs from the cyclic and pedals. The flight control computer also closes the loop on three hydrualic actuators and has sensor inputs from three Attitude/Heading Reference Systems. |
Model Hierarchy/Complexity | Test 1 | |||||||||||||
Decision | Execution | |||||||||||||
1. ActuatorControl | 16 | 78% |
|
100% |
|
|||||||||
2. . . . Actuator1_loop | 5 | 78% |
|
100% |
|
|||||||||
3. . . . . . . Difference | NA | 100% |
|
|||||||||||
4. . . . Actuator2_loop | 5 | 78% |
|
100% |
|
|||||||||
5. . . . . . . Difference | NA | 100% |
|
|||||||||||
6. . . . Actuator3_loop | 5 | 78% |
|
100% |
|
|||||||||
7. . . . . . . Difference | NA | 100% |
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|