Systems and methods of generating a selectively limited aircraft static pressure indication
A device includes circuitry configured to, during a first operation mode, generate a static pressure indication independently of a static pressure measurement limit. The circuitry is also configured to, during a second operation mode, generate the static pressure indication based on the static pressure measurement limit. The circuitry is further configured to generate a standby altitude indication based on the static pressure indication.
1. A device comprising:
circuitry configured to:
during a first operation mode, generate a static pressure indication independently of a static pressure measurement limit;
during a second operation mode, generate the static pressure indication based on the static pressure measurement limit; and
generate a standby altitude indication based on the static pressure indication.
2. The device of claim 1 , wherein, during the second operation mode, the static pressure measurement limit corresponds to a static pressure ceiling of the static pressure indication, and wherein the standby altitude indication has an altitude floor corresponding to the static pressure ceiling.
3. The device of claim 1 , wherein the circuitry includes one or more processors.
4. The device of claim 1 , wherein the circuitry includes analog circuitry.
5. The device of claim 1 , wherein the circuitry is integrated in a line replaceable unit (LRU) configured to provide standby flight data indications.
6. The device of claim 1 , wherein the circuitry is configured to, based on determining that an airspeed measurement indicates a greater than an airspeed threshold, transition from the first operation mode to the second operation mode.
7. The device of claim 1 , wherein the circuitry is configured to, based on determining that a condition is satisfied, transition from the second operation mode to the first operation mode.
8. The device of claim 7 , wherein the circuitry is configured to determine that the condition is satisfied based on detecting that a threshold time has elapsed since transitioning to the second operation mode.
9. The device of claim 7 , wherein the circuitry is configured to determine that the condition is satisfied based on a comparison of a threshold and a difference between a static pressure measurement and the static pressure measurement limit.
10. The device of claim 1 , wherein the circuitry is configured to:
obtain one or more static pressure measurements from a static pressure sensor;
obtain one or more airspeed measurements from an airspeed sensor; and
generate the static pressure indication based solely on the one or more static pressure measurements and the one or more airspeed measurements.
11. The device of claim 1 , wherein the circuitry is configured to, during the first operation mode, update the static pressure measurement limit based on a predetermined count of most recent static pressure measurements.
12. The device of claim 1 , wherein the circuitry is configured to, during the second operation mode, select a lower one of the static pressure measurement limit or a static pressure measurement as the static pressure indication.
13. An aircraft comprising:
circuitry configured to:
during a first operation mode, generate a static pressure indication independently of a static pressure measurement limit;
during a second operation mode, generate the static pressure indication based on the static pressure measurement limit; and
generate a standby altitude indication based on the static pressure indication.
14. The aircraft of claim 13 , wherein the circuitry includes one or more processors.
15. The aircraft of claim 13 , wherein the circuitry includes analog circuitry.
16. The aircraft of claim 13 , wherein the circuitry is integrated in a line replaceable unit (LRU) configured to provide standby flight data indications.
17. The aircraft of claim 13 , wherein, during the second operation mode, the static pressure measurement limit corresponds to a static pressure ceiling of the static pressure indication, and wherein the standby altitude indication has an altitude floor corresponding to the static pressure ceiling.
18. A method comprising:
generating, at circuitry, a static pressure indication selectively based on a static pressure measurement limit; and
generating, at the circuitry, a standby altitude indication based on the static pressure indication.
19. The method of claim 18 , wherein, during a first operation mode, the static pressure indication is generated independently of the static pressure measurement limit.
20. The method of claim 18 , wherein, during a second operation mode, the static pressure indication is generated based on the static pressure measurement limit.