Aircraft stability detection using fluid motion for flight-control feedback
Disclosed is a stability-detecting angle of attack (AoA) system for aircraft, enhancing flight safety by monitoring and managing stability. The system includes an AoA sensor for measuring angle of attack, multiple liquid-level senders with sensors for local fluid levels and kinematics, and processors for compensating fluid motion and temperature. An avionics controller receives data from the senders and AoA sensor, calculating combined tank levels and aircraft stability. It generates flight-control information for feedback mechanisms, including cockpit warnings (audible, haptic, visual) and auto flight process changes. The system aims to prevent loss of control at low speeds by alerting pilots to performance issues and structural risks.
1 . A stability assessment system for an aircraft, comprising:
an angle of attack (AoA) sensor configured to measure the angle of attack and generate AoA information;
a plurality of liquid-level senders positioned within a wing-mounted liquid system, each configured to measure fluid levels and generate fluid data indicative of rapid fluid motion within the wing-mounted liquid system, the rapid fluid motion being correlated with real-time aircraft stability;
a plurality of accelerometers associated with the wing-mounted liquid system and configured to generate kinematics data; and
circuitry configured to:
determine real-time aircraft stability based on the fluid data, the kinematics data, and the AoA information; and
trigger a pilot alert or automated flight-control action based on the real-time aircraft stability.
2 . The stability assessment system of claim 1 , in which each liquid-level sender of the plurality of liquid-level senders is associated with a respective accelerometer and a processor configured to apply motion and temperature compensation to local fluid level measurements and generate local tank levels.
3 . The stability assessment system of claim 2 , in which the circuitry is included in an avionics system controller communicatively coupled to a plurality of liquid-level senders and the AoA sensor, the avionics system controller configured to:
receive local tank levels and local kinematics measurements;
generate local fluid motion data; and
compute a stability score based on the local kinematics measurements, the local fluid motion data, and the AoA information.
4 . The stability assessment system of claim 3 , in which the avionics system controller is further configured to generate the pilot alert or automated flight-control action based on the stability score.
5 . The stability assessment system of claim 1 , in which determining real-time aircraft stability includes analyzing phase or amplitude variation in the fluid data and the kinematics data from, respectively, different sets of liquid-level senders and accelerometers.
6 . The stability assessment system of claim 1 , in which the real-time aircraft stability is determined based on a coherence measurement derived from comparing fluid data from different sensor locations.
7 . The stability assessment system of claim 6 , in which the coherence measurement includes at least one of a phase offset or amplitude variation between a first fluid sensor and a second fluid sensor, each with a corresponding accelerometer.
8 . The stability assessment system of claim 1 , in which the plurality of liquid-level senders includes float-based fuel sensors.
9 . The stability assessment system of claim 1 , in which the automated flight-control action is an auto flight process change.
10 . The stability assessment system of claim 1 , in which the trigger causes a flight-control feedback system to generate the pilot alert or automated flight-control action.
11 . The stability assessment system of claim 10 , in which the pilot alert is a cockpit warning.
12 . The stability assessment system of claim 11 , in which the cockpit warning is one or more of an audible alarm, haptic feedback in a seat, haptic feedback in a flight control stick, or a visual indicator on cockpit instrumentation.
13 . The stability assessment system of claim 1 , in which the AoA sensor includes a leading-edge lift transducer or a fuselage-mounted airflow sensor.
14 . The system of claim 1 , in which the circuitry is further configured to detect stall independently for each wing based on the fluid data generated by the plurality of liquid-level senders positioned within the wing-mounted liquid system.
15 . The system of claim 1 , in which the fluid data generated by the plurality of liquid-level senders positioned within the wing-mounted liquid system provides localized stability information specific to each wing, and the circuitry is further configured to determine stall as a wing-localized aerodynamic condition.
16 . The system of claim 1 , in which the circuitry is further configured to evaluate aircraft motion across multiple stability axes including pitch, roll, and yaw based on the fluid data and the kinematics data when determining the real-time aircraft stability.
17 . The system of claim 1 , in which the circuitry is further configured to identify asymmetric wing behavior by comparing the fluid data or the kinematics data generated by liquid-level senders positioned in different wings of the wing-mounted liquid system.
18 . A method for assessing real-time aircraft stability and generating flight-control feedback, comprising:
receiving angle of attack (AoA) information from an AoA sensor;
receiving fluid data from a plurality of liquid-level senders positioned within a wing-mounted liquid system, the fluid data being indicative of rapid fluid motion within the wing-mounted liquid system at respective sender locations, the rapid fluid motion being correlated with real-time aircraft stability;
receiving kinematics data from a plurality of accelerometers associated with the wing-mounted liquid system;
determining real-time aircraft stability based on the fluid data, the kinematics data, and the AoA information; and
triggering a pilot alert or automated flight-control action based on the determined real-time aircraft stability.
19 . The method of claim 18 , in which each liquid-level sender includes an embedded accelerometer and a processor configured to locally generate the fluid data and kinematics data.
20 . The method of claim 18 , further comprising transmitting the fluid data and kinematics data from the liquid-level senders to an avionics system controller for determining real-time aircraft stability.
21 . The method of claim 18 , in which determining real-time aircraft stability comprises computing a stability score based on the fluid data, the kinematics data, and the AoA information.
22 . The method of claim 21 , in which computing the stability score includes applying a threshold comparison to trigger the pilot alert or automated flight-control action.
23 . The method of claim 18 , in which determining real-time aircraft stability includes analyzing inter-sensor coherence among the fluid data.
24 . The method of claim 23 , in which the inter-sensor coherence comprises a phase offset or amplitude variation between fluid data from different sender locations.
25 . The method of claim 18 , in which triggering the pilot alert comprises activating a visual display, an audible indicator, or a haptic control surface response.
26 . The method of claim 18 , in which triggering the automated flight-control action comprises modifying a control surface, initiating an envelope protection routine, or engaging a spin-recovery procedure.
27 . The method of claim 18 , in which the AoA sensor comprises a leading-edge lift transducer or a fuselage-mounted airflow sensor.
28 . The method of claim 18 , further comprising detecting stall independently for each wing based on the fluid data received from the plurality of liquid-level senders positioned within the wing-mounted liquid system.
29 . The method of claim 18 , in which the fluid data received from the plurality of liquid-level senders positioned within the wing-mounted liquid system provides localized stability information specific to each wing, and determining the aircraft stability includes determining stall as a wing-localized aerodynamic condition.
30 . The method of claim 18 , in which determining the aircraft stability includes evaluating aircraft motion across multiple stability axes including pitch, roll, and yaw based on the fluid data and the kinematics data.