Method for assisting a pilot in controlling an aircraft, assistance system for an aircraft pilot, and aircraft
A method for assisting a pilot in controlling an aircraft, an assistance system for an aircraft pilot, and an aircraft are disclosed herein. In one example, a method is disclosed of assisting a pilot in controlling an aircraft having a plurality of lift-generating propulsion devices. The method having steps that include, calculation of momentary control limitations for each control of the aircraft around a roll axis, a pitch axis, a yaw axis, and a total thrust T of the propulsion devices, and display of the calculated control limitations by a display device.
1 . A method for assisting a pilot in controlling an aircraft having a plurality of lift-generating propulsion devices, the method comprising:
receiving, from a flight control computer of the aircraft, current control parameters exchanged with the plurality of lift-generating propulsion devices for the controlling of the aircraft;
calculating, by a computing device, momentary control limitations based on the current control parameters for each of:
controlling the aircraft around a roll axis (x);
controlling the aircraft around a pitch axis (y);
controlling the aircraft around a yaw axis (z); and
controlling a total thrust (T) of the propulsion devices, including dynamically calculating each momentary control limitation by varying an upper control limit and a lower control limit based on a momentary flight state of the aircraft and momentary control inputs conveyed from the current control parameters; and
displaying, within a fixed display area for each of the momentary control limitations, the momentary control limitations by a display device, the displaying includes displaying the upper control limit and the lower control limit for each momentary control limitation as movable graphical indicators that move within the respective fixed display area based on changes to the momentary flight state and momentary control inputs to visually assist the pilot in the controlling of the aircraft within physical capabilities of the aircraft.
2 . The method according to claim 1 , wherein the momentary control limitations are calculated as at least one of a function of a momentary flight state of the aircraft or a momentary control of the aircraft.
3 . The method according to claim 2 , wherein the momentary control limitations are calculated as a function of the momentary control of the aircraft about the roll axis (x), about the pitch axis (y), about the yaw axis (z), and the total thrust (T) of the propulsion devices.
4 . The method according to claim 1 , wherein the momentary control limitations correspond to flight states physically achievable by the aircraft.
5 . The method according to claim 1 , wherein each of the momentary control limitations is displayed separately from each other of the momentary control limitations.
6 . The method according to claim 1 , wherein at least one of the momentary control limitations is displayed by the display device relative to a neutral control value displayed by the display device.
7 . The method according to claim 1 , wherein for at least one of the momentary control limitations, an area within that momentary control limitation is visually displayed differently than an area outside that momentary control limitation.
8 . The method according to claim 1 , wherein for each of the momentary control limitations, an area within that momentary control limitation is visually displayed differently than an area outside that momentary control limitation.
9 . The method according to claim 1 , wherein for at least one of the momentary control limitations, at least one of the upper control limit or the lower control limit is graphically highlighted.
10 . The method according to claim 9 , wherein for each of the momentary control limitations, at least one of the upper control limit or the lower control limit is graphically highlighted by a signal color.
11 . The method according to claim 1 , wherein a momentary control value is displayed for at least one of: controlling the aircraft about the roll axis (x), controlling the aircraft about the pitch axis (y), controlling the aircraft about the yaw axis (z), or controlling the total thrust (T) of the propulsion devices.
12 . The method according to claim 11 , wherein a graphical representation used to display changes to the momentary control value when the momentary control value reaches a respective control limitation.
13 . The method according to claim 1 , wherein a momentary control value is displayed for controlling the aircraft about the roll axis (x), for controlling the aircraft about the pitch axis (y), for controlling the aircraft about the yaw axis (z), and for controlling the total thrust (T) of the propulsion devices.
14 . The method according to claim 1 , wherein calculating the momentary control limitations includes:
describing the controlling of the aircraft by a vector (γ) comprising four components, including three components of a torque (τ) around each aircraft axis (x, y, z) and the total thrust (T), wherein the three components of the torque (τ) are dependent on an arrangement of the propulsion devices and momentary thrust of each individual propulsion device;
determining momentary limitations of the vector γ with respect to each of the four components; and
calculating the momentary control limitations based on the momentary limitations.
15 . An assistance system for assisting a pilot in controlling an aircraft having a plurality of propulsion devices, the assistance system comprising:
a computing device for calculating momentary control limitations for:
control of the aircraft around a roll axis (x);
control of the aircraft around a pitch axis (y);
control of the aircraft around a yaw axis (z); and
control of a total thrust (T) of the propulsion devices, including dynamically calculating each momentary control limitation by varying an upper control limit and a lower control limit based on a momentary flight state of the aircraft and momentary control inputs conveyed from current control parameters exchanged between a flight control computer of the aircraft and the plurality of propulsion devices;
a display device comprising a fixed display area for each of the momentary control limitations for displaying the calculated control limitations, wherein the display device is configured to display the upper control limit and the lower control limit for each momentary control limitation as movable graphical indicators that move within the respective fixed display area based on the momentary flight state and momentary control inputs to visually assist the pilot in the controlling of the aircraft within physical capabilities of the aircraft.
16 . The assistance system according to claim 15 , wherein the computing device and the display device are connected to each other in a signal-communicating manner.
17 . An aircraft comprising:
a plurality of lift-generating propulsion devices; and
an assistance system for assisting a pilot in controlling the propulsion devices, the assistance system comprising:
a calculation device for calculating momentary control limitations for:
control of the aircraft around a roll axis (x);
control of the aircraft around a pitch axis (y);
control of the aircraft around a yaw axis (z); and
control of a total thrust (T) of the propulsion devices, the calculating including dynamically calculating each momentary control limitation by varying an upper control limit and a lower control limit based on a momentary flight state of the aircraft and momentary control inputs conveyed from current control parameters exchanged between a flight control computer of the aircraft and the plurality of propulsion devices; and
a display device comprising a fixed display area for each of the momentary control limitations, for displaying the calculated control limitations, wherein the display device is configured to display the upper control limit and the lower control limit for each momentary control limitation as movable graphical indicators that move within the respective fixed display area based on the momentary flight state and momentary control inputs to visually assist the pilot in the controlling of the aircraft within physical capabilities of the aircraft.
18 . The method according to claim 1 , wherein a momentary control value indicator is displayed for each of the momentary control limitations, and wherein a graphical representation of the momentary control value indicator changes when the momentary control value approaches a respective upper control limit or lower control limit.
19 . The method according to claim 1 , wherein an area within each momentary control limitation between the upper control limit and the lower control limit is displayed in a first color, and an area outside the momentary control limitation is displayed in a second color different from the first color.
20 . The method according to claim 1 , wherein the momentary control limitations are calculated based on interdependencies between control of the aircraft around the roll axis (x), control of the aircraft around the pitch axis (y), control of the aircraft around the yaw axis (z), and control of the total thrust (T), such that a control input relating to one axis affects the control limitations along another axis.