초록 ▼

The present invention is directed to providing takeoff rotation guidance. A takeoff rotation guidance indicator, including an aircraft reference symbol and a guidance cue, is displayed on a HUD (Head-up Display) of a HGS (Head-up Guidance System). The guidance cue is positioned in relation to the ai

The present invention is directed to providing takeoff rotation guidance. A takeoff rotation guidance indicator, including an aircraft reference symbol and a guidance cue, is displayed on a HUD (Head-up Display) of a HGS (Head-up Guidance System). The guidance cue is positioned in relation to the aircraft reference symbol based on a takeoff rotation pitch guidance and a takeoff rotation roll guidance. Thus, pitch and roll guidance information is simply communicated to the pilot of an aircraft. The takeoff rotation pitch guidance and the takeoff rotation roll guidance are calculated differently at different points during takeoff. In an alternative embodiment, the takeoff rotation guidance indicator includes a slip-skid symbol. The slip-skid symbol is positioned relative to aircraft reference symbol, but is displaced by the lateral acceleration of the aircraft. Thus, slip/skid guidance information is simply communicated to the pilot of an aircraft.

대표청구항 ▼

1. A HGS (Head-up Guidance System) device for displaying suggested pitch and roll command guidance to a pilot of an aircraft during a takeoff roll, a rotation, and an initial climbout, comprising: a HUD (Head-up Display), which includes an aircraft reference symbol and a takeoff rotation guidance cu

1. A HGS (Head-up Guidance System) device for displaying suggested pitch and roll command guidance to a pilot of an aircraft during a takeoff roll, a rotation, and an initial climbout, comprising: a HUD (Head-up Display), which includes an aircraft reference symbol and a takeoff rotation guidance cue; anda processing unit operatively connected to the HUD for calculating and displaying on the HUD the takeoff rotation guidance cue, the takeoff rotation guidance cue indicating a suggested takeoff rotation pitch command and a suggested takeoff rotation roll command to the pilot;wherein, as displayed on the HUD, the aircraft reference symbol has an x position and a y position indicating aircraft current path, the takeoff rotation guidance cue has an x position equal to the reference symbol x position, and a y position equal to the y position of the aircraft symbol plus the suggested takeoff rotation pitch command, the suggested takeoff rotation pitch command based at least on a pitch command limit, a pitch command ramp, and an engine failure factor, and the guidance cue is rotated about the aircraft reference symbol indicating the suggested takeoff rotation roll command, the suggested takeoff rotation roll command based at least on a roll command limit, a track error, a track error gain, a yaw rate, and a yaw rate gain. 2. The HGS device as claimed in claim 1, wherein the HGS device further comprises a lateral acceleration sensor operatively connected to the processing unit for receiving a lateral acceleration for the aircraft, the HUD further includes a slip-skid symbol which is positioned relative to the aircraft reference symbol, and the slip-skid symbol is displaced laterally from the aircraft reference symbol based upon the lateral acceleration of the aircraft. 3. The HGS device as claimed in claim 1, wherein the HGS further comprises an airspeed sensor operatively connected to the processing unit for receiving a computed airspeed for the aircraft and the suggested takeoff rotation pitch command is zero when the computed airspeed is less than a takeoff rotation speed. 4. The HGS device as claimed in claim 1, wherein the HGS further comprises an airspeed sensor operatively connected to the processing unit for receiving a computed airspeed for the aircraft and the suggested takeoff rotation roll guidance is zero when the computed airspeed is less than a takeoff liftoff speed. 5. The HGS device as claimed in claim 1, wherein calculating and displaying the takeoff rotation guidance cue at the y position further comprises: an airspeed sensor operatively connected to the processing unit for receiving a computed airspeed for the aircraft,a pitch sensor operatively connected to the processing unit for receiving a pitch for the aircraft,a pitch rate sensor operatively connected to the processing unit for receiving a pitch rate for the aircraft,an engine failure sensor operatively connected to the processing unit for receiving an engine failure status for the aircraft, andan altitude sensor operatively connected to the processing unit for receiving an altitude for the aircraft above a terrain; andwhen the computed airspeed is greater than a takeoff rotation speed and the altitude of the aircraft above the terrain is approximately less than a climbout altitude the suggested takeoff rotation pitch command is calculated by: generating a suggested pitch rate;multiplying the suggested pitch rate by an engine failure factor to obtain a product;subtracting the pitch of the aircraft from the product to obtain a difference;subtracting the pitch rate of the aircraft from the difference to obtain a y position of the takeoff rotation guidance cue; anddisplaying on the HUD said takeoff rotation guidance cue at the y position. 6. The HGS device as claimed in claim 1, wherein the calculating and displaying the suggested takeoff rotation roll guidance further comprises: an airspeed sensor operatively connected to the processing unit for receiving a computed airspeed for the aircraft,a track error sensor operatively connected to the processing unit for receiving a track error for the aircraft,a yaw rate sensor operatively connected to the processing unit for receiving a yaw rate for the aircraft,a roll angle sensor operatively connected to the processing unit for receiving a roll angle for the aircraft,a roll rate sensor operatively connected to the processing unit for receiving a roll rate for the aircraft, and analtitude sensor operatively connected to the processing unit for receiving an altitude for the aircraft above a terrain; andwhen the computed airspeed is greater than a takeoff liftoff speed and the altitude of the aircraft above the terrain is approximately less than a climbout altitude the suggested takeoff rotation roll guidance is calculated by:subtracting the yaw rate of the aircraft from the track error of the aircraft to obtain a roll command limit;subtracting the actual roll angle of the aircraft from the roll command limit to obtain a roll command;subtracting the actual roll rate of the aircraft from the roll command to obtain the suggested takeoff rotation roll guidance; androtating, as displayed on the HUD, the rotation guidance cue about the aircraft reference symbol at an angle equal to the suggested takeoff rotation roll guidance. 7. A method of displaying suggested pitch and roll command guidance to a pilot of an aircraft during a takeoff roll, a rotation, and an initial climbout, comprising the steps of: receiving a plurality of inputs within a processing unit, the plurality of inputs associated with the aircraft during the takeoff roll;generating guidance symbols within the processing unit, the guidance symbols including at least an aircraft reference symbol and a takeoff rotation guidance cue;presenting, via the processing unit, the aircraft reference symbol on a Head-up display (HUD), the reference symbol includes an x position and a y position, on the HUD;presenting, via the processing unit, the takeoff rotation guidance cue on the HUD, the guidance includes an x position, a y position, and is configured to rotate about the aircraft reference symbol on the HUD;calculating, via the processing unit, a suggested takeoff rotation pitch command, the suggested takeoff rotation pitch command based at least on a pitch command limit, a pitch command ramp, and an engine failure factor;calculating, via the processing unit, a suggested takeoff rotation roll command, the suggested takeoff rotation roll command based at least on a roll command limit, a track error, a track error gain, a yaw rate, and a yaw rate gain;positioning, via the processing unit, the guidance cue on the HUD such that the x position of the guidance cue is equal to the x position of the aircraft reference symbol; andpositioning, via the processing unit, the guidance cue on the HUD such that the y position of the guidance cue is the y position of the aircraft reference symbol plus the suggested takeoff rotation pitch command; androtating, via the processing unit, as positioned on the HUD, the guidance cue about the aircraft reference symbol at an angle equal to the suggested takeoff rotation roll command. 8. The method of claim 7, further comprising the steps of: receiving a lateral acceleration for the aircraft;providing a slip-skid symbol on the HUD;positioning the slip-skid symbol relative to the aircraft reference symbol; anddisplacing the slip-skid symbol laterally from the aircraft reference symbol based on the lateral acceleration of the aircraft. 9. The method of claim 7, wherein positioning the guidance cue on the HUD further comprises the step of: receiving a takeoff rotation speed for the aircraft;receiving a computed airspeed for the aircraft;limiting the suggested takeoff rotation pitch command to zero when the computed airspeed is less than the takeoff rotation speed. 10. The method of claim 7, wherein rotating, as positioned on the HUD, the guidance cue about the aircraft reference symbol further comprises the steps of: receiving a takeoff liftoff speed for the aircraft;receiving a computed airspeed for the aircraft;limiting the suggested takeoff rotation roll guidance to zero when the computed airspeed is less than the takeoff liftoff speed. 11. The method of claim 7, wherein positioning of the guidance cue on the HUD further comprising the steps of: receiving a computed airspeed for the aircraft;receiving a pitch for the aircraft;receiving a pitch rate for the aircraft;receiving an engine failure status for the aircraft; andreceiving a track error for the aircraft;receiving a yaw rate for the aircraft;receiving a roll angle for the aircraft;receiving an roll rate for the aircraft; andreceiving an altitude for the aircraft above a terrain;when the computed airspeed is greater than a takeoff rotation speed and the altitude of the aircraft above the terrain is approximately less than a climbout altitude the calculation of the displayed position of the suggested takeoff rotation pitch command as displayed on the HUD is based on a suggested pitch rate, the engine failure status of the aircraft, the pitch of the aircraft, and the pitch rate of the aircraft; and when the computed airspeed is greater than a takeoff liftoff speed and the altitude of the aircraft above the terrain is approximately less than the climbout altitude the calculation of the angle of rotation of the guidance cue about the aircraft reference symbol as displayed on the HUD is based on the track error of the aircraft, the yaw rate of the aircraft, the roll angle of the aircraft, and the roll rate of the aircraft;displaying, on the HUD, the guidance cue at the calculated x axis position, at the calculated y axis position, and rotating the guidance cue about the aircraft reference symbol at an angle equal to the calculated angle of rotation of the guidance cue. 12. The method of claim 7, wherein calculating and display of the y axis position of the guidance cue further comprising the steps of: receiving a computed airspeed for the aircraft;receiving a pitch for the aircraft;receiving a pitch rate for the aircraft;receiving an engine failure status for the aircraft; andreceiving an altitude for the aircraft above a terrain;when the computed airspeed is greater than a takeoff rotation speed and the altitude of the aircraft above the terrain is approximately less than a climbout altitude the step of calculating and display of the y axis position of the guidance cue comprises the steps of:generating a suggested pitch rate;multiplying the suggested pitch rate by an engine failure factor to obtain a product;subtracting the pitch of the aircraft from the product to obtain a difference;subtracting the pitch rate of the aircraft from the difference to obtain a y position of the takeoff rotation guidance cue; anddisplaying on the HUD said takeoff rotation guidance cue at the y position. 13. The method of claim 7, wherein the calculation and display of the suggested takeoff rotation roll guidance further comprising the steps of: receiving a computed airspeed for the aircraft;receiving a track error for the aircraft;receiving a yaw rate for the aircraft;receiving a roll angle for the aircraft;receiving an roll rate for the aircraft; andreceiving an altitude for the aircraft above a terrain;when the computed airspeed is greater than a takeoff liftoff speed and the altitude of the aircraft above the terrain is approximately less than a climbout altitude the step of calculating and display of the suggested takeoff rotation roll guidance comprises the steps of:subtracting the yaw rate of the aircraft from the track error of the aircraft to obtain a roll command limit;subtracting the actual roll angle of the aircraft from the roll command limit to obtain a roll command;subtracting the actual roll rate of the aircraft from the roll command to obtain the suggested takeoff rotation roll guidance; androtating, as displayed on the HUD, the guidance cue about the aircraft reference symbol at an angle equal to the suggested takeoff rotation roll guidance. 14. A system for displaying suggested pitch and roll command guidance to a pilot of an aircraft during a takeoff roll, a rotation, and an initial climbout, comprising: a Head-up display (HUD), the HUD configured for installation on board the aircraft, the HUD including, an aircraft reference symbol and a guidance cue; anda processing unit for calculating a suggested takeoff rotation pitch command and a suggested takeoff rotation roll command;wherein the aircraft reference symbol has an x position and a y position, the guidance cue has an x position, a y position, and is configured to rotate about the aircraft reference symbol on the HUD, the x position of the guidance cue is equal to the x position of the aircraft reference symbol, the y position of the guidance cue is the y position of the aircraft reference symbol plus the suggested takeoff rotation pitch command, the suggested takeoff rotation pitch command based at least on a pitch command limit, a pitch command ramp, and an engine failure factor, and the guidance cue is rotated about the aircraft reference symbol based upon the suggested takeoff rotation roll command, the suggested takeoff rotation roll command based at least on a roll command limit, a track error, a track error gain, a yaw rate, and a yaw rate gain. 15. The system as claimed in claim 14, wherein the system further comprises a lateral acceleration sensor for receiving a lateral acceleration for the aircraft, the display further includes a slip-skid symbol which is positioned relative to the aircraft reference symbol, and the slip-skid symbol is displaced laterally from the aircraft reference symbol based upon the lateral acceleration of the aircraft. 16. The system as claimed in claim 14, wherein the system further comprises an airspeed sensor for receiving a computed airspeed for the aircraft and the suggested takeoff rotation pitch command is zero when the computed airspeed is less than a takeoff rotation speed. 17. The system as claimed in claim 14, wherein the system further comprises an airspeed sensor for receiving a computed airspeed for the aircraft and the suggested takeoff rotation roll guidance is zero when the computed airspeed is less than a takeoff liftoff speed. 18. The system as claimed in claim 14, wherein the system further comprises an airspeed sensor for receiving a computed airspeed for the aircraft,a pitch sensor for receiving a pitch for the aircraft,a pitch rate sensor for receiving a pitch rate for the aircraft,an engine failure sensor for receiving an engine failure status for the aircraft, andan altitude sensor for receiving an altitude for the aircraft above a terrain; andwhen the computed airspeed is greater than a takeoff rotation speed and the altitude of the aircraft above the terrain is approximately less than a climbout altitude the suggested takeoff rotation pitch command is calculated by:generating a suggested pitch rate;multiplying the suggested pitch rate by an engine failure factor to obtain a product;subtracting the pitch of the aircraft from the product to obtain a difference;subtracting the pitch rate of the aircraft from the difference to obtain a y position of the takeoff rotation guidance cue; anddisplaying on the HUD said takeoff rotation guidance cue at the y position. 19. The system as claimed in claim 14, wherein the system further comprises an airspeed sensor for receiving a computed airspeed for the aircraft, a track error sensor for receiving a track error for the aircraft, a yaw rate sensor for receiving a yaw rate for the aircraft, a roll angle sensor for receiving a roll angle for the aircraft, a roll rate sensor for receiving a roll rate for the aircraft, and an altitude sensor for receiving an altitude for the aircraft above a terrain; and when the computed airspeed is greater than a takeoff liftoff speed and the altitude of the aircraft above the terrain is approximately less than a climbout altitude the suggested takeoff rotation roll guidance is calculated by: subtracting the yaw rate of the aircraft from the track error of the aircraft to obtain a roll command limit;subtracting the actual roll angle of the aircraft from the roll command limit to obtain a roll command;subtracting the actual roll rate of the aircraft from the roll command to obtain the suggested takeoff rotation roll guidance; androtating, as displayed on the HUD, the guidance cue about the aircraft reference symbol at an angle equal to the suggested takeoff rotation roll guidance.