Systems and methods for applying a movable notch filter in flight control of EVTOL aircraft

1. An electrical system for an aircraft, comprising:

at least one processor configured to:

receive first sensor data from at least one inertial sensor of the aircraft, wherein the first sensor data is indicative of a state of the aircraft;

receive second sensor data from at least one of an airspeed sensor indicating an airspeed of the aircraft or a propeller speed sensor indicating a propeller speed of at least one propeller of the aircraft;

determine the state of the aircraft based on the first sensor data, wherein:

determining the state of the aircraft comprises filtering aircraft state measurements using at least one filter parameter to lessen influence of propeller vibrations on at least one aircraft signal; and

the at least one filter parameter is dynamically determined based on the second sensor data while the aircraft is in flight; and

control the aircraft based on a pilot input command and the determined state of the aircraft.

2. The electrical system of claim 1 , wherein the inertial sensor comprises at least one of an accelerometer or a gyroscope.

3. The electrical system of claim 1 ,

wherein the second sensor data comprises an airspeed;

wherein the at least one processor is further configured to:

receive third sensor data from an air density sensor, and

determine a propeller speed of the aircraft based on the airspeed and the third sensor data;

wherein determining the propeller speed is based on a predetermined air density and predetermined propeller speed combination corresponding to the airspeed; and

wherein filtering aircraft state measurements is based on the second sensor data and the determined propeller speed.

4. The electrical system of claim 1 ,

wherein the second sensor data comprises a propeller speed; and

wherein filtering the aircraft state measurements is based on the propeller speed.

5. The electrical system of claim 1 , wherein filtering the aircraft state measurements comprises at least one of:

filtering first sensor data based on the second sensor data, or

filtering measurements based on the first sensor data based on the second sensor data, wherein the measurements include at least one of: acceleration of the aircraft or angular rate of the aircraft.

6. The electrical system of claim 1 , wherein the at least one filter parameter comprises at least one of a filter center frequency, filter attenuation, or filter width.

7. The electrical system of claim 6 , wherein determining the at least one filter parameter based on the second sensor data comprises at least one of:

decreasing filter attenuation based on the airspeed indicating a hover phase of the aircraft,

increasing filter attenuation based on the airspeed indicating a transition flight phase of the aircraft, or

decreasing filter attenuation based on a decrease in propeller speed.

8. The electrical system of claim 6 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency based on a number of blades of a propeller of the aircraft and the propeller speed.

9. The electrical system of claim 6 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency at a frequency proportional to the propeller speed.

10. The electrical system of claim 6 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency at a frequency proportional to the number of blades.

11. The electrical system of claim 1 , wherein determining the at least one filter parameter based on the second sensor data comprises at least one of:

increasing filter width based on the airspeed indicating a hover phase of the aircraft; or

decreasing a filter width based on the airspeed indicating the aircraft is not in a hover phase of flight.

12. The electrical system of claim 1 , wherein filtering aircraft state measurements comprises applying a filter that includes at least one stopband edge delineating an edge of a range of frequencies where the aircraft state measurements will be attenuated.

13. The electrical system of claim 1 , wherein filtering aircraft state measurements comprises applying a filter that includes a stopband range delineating a range of frequencies where the aircraft state measurements will be attenuated.

14. The electrical system of claim 13 , wherein the stopband range is a second-order filter that adjusts filter characteristics of a first filter.

15. The electrical system of claim 1 , wherein the at least one processor is further configured to receive third sensor data indicative of a propeller angle, wherein determining the state of the aircraft comprises filtering aircraft state measurements based on the second sensor data and the third sensor data to lessen the influence of propeller vibrations.

16. The electrical system of claim 1 , wherein the second sensor data comprises a propeller speed of each propeller of a plurality of propellers on the aircraft.

17. The electrical system of claim 1 , wherein controlling the aircraft based on the pilot input command and the determined state of the aircraft comprises:

receiving a command comprising at least one of: a roll command, yaw command, or pitch command corresponding to the pilot input command;

determining a moment command based on the received command and the determined aircraft state; and

controlling the aircraft based on the determined moment command.

18. The electrical system of claim 1 , wherein controlling the aircraft based on the pilot input command and the determined state of the aircraft comprises controlling at least one of: a control surface of the aircraft or an electric engine of the aircraft.

19. An aircraft, comprising:

at least one propeller;

at least one inertial sensor;

a second sensor;

at least one processor configured to:

receive first sensor data from the at least one inertial sensor of the aircraft, wherein the first sensor data is indicative of a state of the aircraft;

receive second sensor data from the second sensor, the second sensor comprising at least one of an airspeed sensor indicating an airspeed of the aircraft or a propeller speed sensor indicating a propeller speed of the at least one propeller of the aircraft;

determine the state of the aircraft based on the first sensor data, wherein:

determining the state of the aircraft comprises filtering aircraft state measurements using at least one filter parameter to lessen influence of propeller vibrations on at least one aircraft signal; and

the at least one filter parameter is dynamically determined based on the second sensor data while the aircraft is in flight; and

control the aircraft based on a pilot input command and the determined state of the aircraft.

20. The aircraft of claim 19 , wherein the inertial sensor comprises at least one of an accelerometer or a gyroscope.

21. The aircraft of claim 19 ,

wherein the second sensor data comprises an airspeed;

wherein the at least one processor is further configured to:

receive third sensor data from an air density sensor, and

determine a propeller speed of the aircraft based on the airspeed and the third sensor data;

wherein determining the propeller speed is based on a predetermined air density and predetermined propeller speed combination corresponding to the airspeed; and

wherein filtering aircraft state measurements is based on the second sensor data and the determined propeller speed.

22. The aircraft of claim 19 ,

wherein the second sensor data comprises a propeller speed; and

wherein filtering the aircraft state measurements is based on the propeller speed.

23. The aircraft of claim 19 , wherein filtering the aircraft state measurements comprises at least one of:

filtering first sensor data based on the second sensor data, or

filtering measurements based on the first sensor data based on the second sensor data, wherein the measurements include at least one of: acceleration of the aircraft or angular rate of the aircraft.

24. The aircraft of claim 19 , wherein the at least one filter parameter comprises at least one of a filter center frequency, filter attenuation, or filter width.

25. The aircraft of claim 24 , wherein determining the at least one filter parameter based on the second sensor data comprises at least one of:

decreasing filter attenuation based on the airspeed indicating a hover phase of the aircraft,

increasing filter attenuation based on the airspeed indicating a transition flight phase of the aircraft, or

decreasing filter attenuation based on a decrease in propeller speed.

26. The aircraft of claim 24 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency based on a number of blades of a propeller of the aircraft and the propeller speed.

27. The aircraft of claim 24 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency at a frequency proportional to the propeller speed.

28. The aircraft of claim 24 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency at a frequency proportional to the number of blades.

29. The aircraft of claim 19 , wherein-determining the at least one filter parameter based on the second sensor data comprises at least one of:

increasing filter width based on the airspeed indicating a hover phase of the aircraft; or

decreasing a filter width based on the airspeed indicating the aircraft is not in a hover phase of flight.

30. The aircraft of claim 19 , wherein filtering aircraft state measurements comprises applying a filter that includes at least one stopband edge delineating an edge of a range of frequencies where the aircraft state measurements will be attenuated.

31. The aircraft of claim 19 , wherein filtering aircraft state measurements comprises applying a filter that includes a stopband range delineating a range of frequencies where the aircraft state measurements will be attenuated.

32. The aircraft of claim 31 , wherein the stopband range is a second-order filter that adjusts filter characteristics of a first filter.

33. The aircraft of claim 19 , wherein the at least one processor is further configured to receive third sensor data indicative of a propeller angle, wherein determining the state of the aircraft comprises filtering aircraft state measurements based on the second sensor data and the third sensor data to lessen the influence of propeller vibrations.

34. The aircraft of claim 19 , wherein the second sensor data comprises a propeller speed of each propeller of a plurality of propellers on the aircraft.

35. The aircraft of claim 19 , wherein controlling the aircraft based on the pilot input command and the determined state of the aircraft comprises:

receiving a command comprising at least one of: a roll command, yaw command, or pitch command corresponding to the pilot input command;

determining a moment command based on the received command and the determined aircraft state; and

controlling the aircraft based on the determined moment command.

36. The aircraft of claim 19 , wherein controlling the aircraft based on the pilot input command and the determined state of the aircraft comprises controlling at least one of: a control surface of the aircraft or an electric engine of the aircraft.

37. A method for controlling an aircraft, comprising:

receiving first sensor data from at least one inertial sensor of the aircraft, wherein the first sensor data is indicative of a state of the aircraft;

receiving second sensor data from at least one of an airspeed sensor indicating an airspeed of the aircraft or a propeller speed sensor indicating a propeller speed of at least one propeller of the aircraft;

determining the state of the aircraft based on the first sensor data, wherein:

determining the state of the aircraft comprises filtering aircraft state measurements using at least one filter parameter to lessen influence of propeller vibrations on at least one aircraft signal; and

the at least one filter parameter is dynamically determined based on the second sensor data while the aircraft is in flight; and

controlling the aircraft based on a pilot input command and the determined state of the aircraft.

38. The method of claim 37 , wherein the inertial sensor comprises at least one of an accelerometer or a gyroscope.

39. The method of claim 37 ,

wherein the second sensor data comprises an airspeed;

wherein the to the method further comprises:

receiving third sensor data from an air density sensor, and

determine a propeller speed of the aircraft based on the airspeed and the third sensor data;

wherein determining the propeller speed is based on a predetermined air density and predetermined propeller speed combination corresponding to the airspeed; and

wherein filtering aircraft state measurements is based on the second sensor data and the determined propeller speed.

40. The method of claim 37 ,

wherein the second sensor data comprises a propeller speed; and

wherein filtering the aircraft state measurements is based on the propeller speed.

41. The method of claim 37 , wherein filtering the aircraft state measurements comprises at least one of:

filtering first sensor data based on the second sensor data, or

filtering measurements based on the first sensor data based on the second sensor data, wherein the measurements include at least one of: acceleration of the aircraft or angular rate of the aircraft.

42. The method of claim 37 , wherein the at least one filter parameter comprises at least one of a filter center frequency, filter attenuation, or filter width.

43. The method of claim 42 , wherein determining the at least one filter parameter based on the second sensor data comprises at least one of:

decreasing filter attenuation based on the airspeed indicating a hover phase of the aircraft,

increasing filter attenuation based on the airspeed indicating a transition flight phase of the aircraft, or

decreasing filter attenuation based on a decrease in propeller speed.

44. The method of claim 42 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency based on a number of blades of a propeller of the aircraft and the propeller speed.

45. The method of claim 42 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency at a frequency proportional to the propeller speed.

46. The method of claim 42 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency at a frequency proportional to the number of blades.

47. The method of claim 37 , wherein-determining the at least one filter parameter based on the second sensor data comprises at least one of:

increasing filter width based on the airspeed indicating a hover phase of the aircraft; or

decreasing a filter width based on the airspeed indicating the aircraft is not in a hover phase of flight.

48. The method of claim 37 , wherein filtering aircraft state measurements comprises applying a filter that includes at least one stopband edge delineating an edge of a range of frequencies where the aircraft state measurements will be attenuated.

49. The method of claim 37 , wherein filtering aircraft state measurements comprises applying a filter that includes a stopband range delineating a range of frequencies where the aircraft state measurements will be attenuated.

50. The aircraft of claim 49 , wherein the stopband range is a second-order filter that adjusts filter characteristics of a first filter.

51. The method of claim 37 , wherein the at least one processor is further configured to receive third sensor data indicative of a propeller angle, wherein determining the state of the aircraft comprises filtering aircraft state measurements based on the second sensor data and the third sensor data to lessen the influence of propeller vibrations.

52. The method of claim 37 , wherein the second sensor data comprises a propeller speed of each propeller of a plurality of propellers on the aircraft.

53. The method of claim 37 , wherein controlling the aircraft based on the pilot input command and the determined state of the aircraft comprises:

receiving a command comprising at least one of: a roll command, yaw command, or pitch command corresponding to the pilot input command;

determining a moment command based on the received command and the determined aircraft state; and

controlling the aircraft based on the determined moment command.

54. The method of claim 37 , wherein controlling the aircraft based on the pilot input command and the determined state of the aircraft comprises controlling at least one of: a control surface of the aircraft or an electric engine of the aircraft.

55. A non-transitory computer readable storage medium storing instructions which, when executed by at least one processor, cause the at least one processor to:

receive first sensor data from at least one inertial sensor of an aircraft, wherein the first sensor data is indicative of a state of the aircraft;

receive second sensor data from at least one of an airspeed sensor indicating an airspeed of the aircraft or a propeller speed sensor indicating a propeller speed of at least one propeller of the aircraft;

determine the state of the aircraft based on the first sensor data, wherein:

determining the state of the aircraft comprises filtering aircraft state measurements at least one filter parameter to lessen influence of propeller vibrations on at least one aircraft signal; and

the at least one filter parameter is dynamically determined based on the second sensor data while the aircraft is in flight; and

control the aircraft based on a pilot input command and the determined state of the aircraft.

56. The computer readable storage medium of claim 55 , wherein the inertial sensor comprises at least one of an accelerometer or a gyroscope.

57. The computer readable storage medium of claim 55 ,

wherein the second sensor data comprises an airspeed;

wherein the at least one processor is further configured to:

receive third sensor data from an air density sensor, and

determine a propeller speed of the aircraft based on the airspeed and the third sensor data;

wherein determining the propeller speed is based on a predetermined air density and predetermined propeller speed combination corresponding to the airspeed; and

wherein filtering aircraft state measurements is based on the second sensor data and the determined propeller speed.

58. The computer readable storage medium of claim 55 ,

wherein the second sensor data comprises a propeller speed; and

wherein filtering the aircraft state measurements is based on the propeller speed.

59. The computer readable storage medium of claim 55 , wherein filtering the aircraft state measurements comprises at least one of:

filtering first sensor data based on the second sensor data, or

filtering measurements based on the first sensor data based on the second sensor data, wherein the measurements include at least one of: acceleration of the aircraft or angular rate of the aircraft.

60. The computer readable storage medium of claim 55 , wherein the at least one filter parameter comprises at least one of a filter center frequency, filter attenuation, or filter width.

61. The computer readable storage medium of claim 60 , wherein determining the at least one filter parameter based on the second sensor data comprises at least one of:

decreasing filter attenuation based on the airspeed indicating a hover phase of the aircraft,

increasing filter attenuation based on the airspeed indicating a transition flight phase of the aircraft, or

decreasing filter attenuation based on a decrease in propeller speed.

62. The computer readable storage medium of claim 60 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency based on a number of blades of a propeller of the aircraft and the propeller speed.

63. The computer readable storage medium of claim 60 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency at a frequency proportional to the propeller speed.

64. The computer readable storage medium of claim 60 , wherein determining the at least one filter parameter based on the second sensor data comprises determining a filter center frequency at a frequency proportional to the number of blades.

65. The computer readable storage medium of claim 55 , wherein-determining the at least one filter parameter based on the second sensor data comprises at least one of:

increasing filter width based on the airspeed indicating a hover phase of the aircraft; or

decreasing a filter width based on the airspeed indicating the aircraft is not in a hover phase of flight.

66. The computer readable storage medium of claim 55 , wherein filtering aircraft state measurements comprises applying a filter that includes at least one stopband edge delineating an edge of a range of frequencies where the aircraft state measurements will be attenuated.

67. The computer readable storage medium of claim 55 , wherein filtering aircraft state measurements comprises applying a filter that includes a stopband range delineating a range of frequencies where the aircraft state measurements will be attenuated.

68. The aircraft of claim 67 , wherein the stopband range is a second-order filter that adjusts filter characteristics of a first filter.

69. The computer readable storage medium of claim 55 , wherein the at least one processor is further configured to receive third sensor data indicative of a propeller angle, wherein determining the state of the aircraft comprises filtering aircraft state measurements based on the second sensor data and the third sensor data to lessen the influence of propeller vibrations.

70. The computer readable storage medium of claim 55 , wherein the second sensor data comprises a propeller speed of each propeller of a plurality of propellers on the aircraft.

71. The computer readable storage medium of claim 55 , wherein controlling the aircraft based on the pilot input command and the determined state of the aircraft comprises:

receiving a command comprising at least one of: a roll command, yaw command, or pitch command corresponding to the pilot input command;

determining a moment command based on the received command and the determined aircraft state; and

controlling the aircraft based on the determined moment command.

72. The computer readable storage medium of claim 55 , wherein controlling the aircraft based on the pilot input command and the determined state of the aircraft comprises controlling at least one of: a control surface of the aircraft or an electric engine of the aircraft.