HUD (Head Up Display) method for changing aircraft tail spin into aided driving
By embedding the tail rotary modification assisted driving module in the aircraft platform and cross-linking it with the onboard HUD system, the tail rotary state and control guidance are displayed, the problem of misjudgment of the pilot in the tail rotary state is solved, the success rate of tail rotary modification is improved, and the probability of crash is reduced.
Patent Information
- Application Number
- CN202510608211.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-13
- Publication Date
- 2025-07-11
AI Technical Summary
In the tail spin state, pilots find it difficult for modern fighters to accurately judge and mismanage, resulting in a high probability of tail spin crash, especially among high-performance fighters.
The tail rotation is modified into the auxiliary driving module and is embedded in the aircraft platform, cross-linked with the onboard HUD system, and the tail rotation state is judged by analyzing the aircraft's state and displaying the tail rotation state and auxiliary control information on the HUD, including the position guidance of the rudder, pedal and throttle.
It improves the pilot's accurate judgment of the tail spin state, reduces the probability of misjudgment, enhances the success rate of tail spin modification, and reduces the risk of aircraft crashes.
Smart Images
Figure CN120288252A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of aircraft assisted driving, and particularly relates to a HUD display method for aircraft spin recovery assisted driving. Background Art
[0002] Aircraft spin is an extremely dangerous extreme flight state. Currently, the aircraft spin state is basically judged by the pilot himself, and the spin recovery is carried out according to the spin recovery control procedure of the aircraft. However, when the aircraft enters a spin, it will bring great physiological and psychological burdens to the pilot. Coupled with the fact that modern high-performance fighter aircraft often accompany severe three-axis oscillations when entering a spin, it brings great difficulties for the pilot to accurately judge the spin state, and it is extremely easy for the pilot to misjudge. Most modern fighter aircraft are in flat spins, which are even more difficult to recover. If the pilot misjudges the spin state as described above, and then leads to misoperation by the pilot, the spin will be aggravated. Or the aforementioned spin oscillation state causes a delay in the pilot's accurate judgment. Even if the pilot can finally judge the spin state, it also greatly compresses the opportunity for spin recovery, thus ultimately resulting in the inability to recover from the spin and increasing the probability of aircraft crash.
[0003] HUD is a head-up display, which has dynamic image display, and the display content is flexible and rich. It can be used as a carrier for functions such as aircraft spin state display and spin recovery control prompt, etc., to improve the pilot's accurate judgment of the current spin state, assist in prompting the pilot about the control methods of the spin recovery control stick, rudder and throttle combination, and can effectively improve the spin recovery success rate and reduce the spin crash probability. Summary of the Invention
[0004] The purpose of the present invention is: A HUD display method for aircraft spin recovery assisted driving of the present invention embeds the spin recovery assisted driving module into the aircraft platform and cross-links it with the onboard HUD system, which can accurately display the spin state of the aircraft when the aircraft enters a spin for the pilot, and at the same time assist in prompting the pilot about the control range of the control stick, rudder and throttle combination, so as to reduce the pilot's misjudgment and enhance the pilot's spin recovery assisted driving, improve the pilot's spin recovery success rate, and reduce the spin crash probability.
[0005] The technical solution of the present invention: A HUD display method for aircraft spin recovery assisted driving, characterized in that the spin recovery assisted driving module is embedded into the aircraft platform and cross-linked with the onboard HUD system. The spin recovery assisted driving module includes an input module 501, an assisted driving module 502, and an output module 503;
[0006] The input module 501 receives the aircraft flight state quantity 500 and analyzes the angle of attack a, yaw angular velocity r, control stick, rudder pedal and throttle state quantity therein;
[0007] The assisted driving module 502, when the angle of attack α of the aircraft is greater than the stall angle of attack αs and the yaw angular velocity r is greater than the spin yaw angular velocity r s In this case, it is determined that the aircraft enters the spin state, and auxiliary pilot information for recovering from the spin is given;
[0008] The output module 503 gives the spin state and the auxiliary pilot information to the HUD system 504, and the HUD system displays them in the form of a spin state and a HUD interface for auxiliary pilot to recover from the spin.
[0009] The spin state and the HUD interface for auxiliary pilot to recover from the spin include a HUD display frame 100, a spin horizontal state indicator 200, a spin longitudinal state indicator 201, a control surface and rudder operation boundary 202, an expected control surface and rudder position 203 for recovering from the spin, a current control surface and rudder position 204, an expected left foot pedal position 300 for recovering from the spin, an expected right foot pedal position 301 for recovering from the spin, a current left foot pedal position 302, a current right foot pedal position 303, an expected throttle position 400 for recovering from the spin, a current throttle position 401, as well as a control surface and rudder horizontal scale 205, a control surface and rudder vertical scale 206, a foot pedal scale 304, and a throttle scale 402.
[0010] The spin horizontal state indicator 200 indicates the horizontal rotation direction and rotation speed of the aircraft spin; when the angle of attack α of the aircraft is greater than the stall angle of attack α s and the yaw angular velocity r is greater than the spin yaw angular velocity r s In this case, the solid dot of the spin horizontal state indicator 200 starts to rotate, and its rotation rate is the same as the absolute value of the aircraft yaw angular velocity, so as to indicate the speed of the spin rotation. The rotation direction of the spin horizontal state indicator 200 is the same as the direction of the aircraft spin. Counterclockwise rotation represents a left spin of the aircraft, and clockwise rotation represents a right spin of the aircraft.
[0011] The spin longitudinal state indicator 201 indicates the longitudinal direction of the aircraft spin. The current display state of the spin longitudinal state indicator 201 indicates that the aircraft is in a normal flight spin, and the display state after the spin longitudinal state indicator 201 rotates 180 degrees indicates that the aircraft is in an inverted flight spin.
[0012] The control surface and rudder operation boundary 202 is the maximum control surface and rudder operation boundary of the aircraft, which is circular. At the same time, this circular ring serves as the spin horizontal state indicator 200, that is, the rotation trajectory of the solid dot indicates the spin rate and the horizontal rotation direction state of the aircraft.
[0013] The expected control surface and rudder position 203 for recovering from the spin is the expected control surface and rudder position for recovering from the spin after the aircraft enters the spin state. During the display process, it continuously flashes to improve the pilot's attention and guide the pilot to operate the control surface and rudder to the area of the control surface and rudder position 203 for recovering from the spin.
[0014] The described current control column and rudder position 204 displays in real time the actual position of the control column and rudder manipulated by the current pilot, and is used to display in real time the relative position relationship between the current control column and rudder position 204 and the flashing spin recovery control column and rudder position 203.
[0015] During the display process of the described desired spin recovery left foot pedal position 300 and the desired spin recovery right foot pedal position 301, both the desired spin recovery left foot pedal position 300 and the desired spin recovery right foot pedal position 301 continuously flash, so as to increase the pilot's attention and guide the pilot to operate the left and right foot pedals to the area of the desired spin recovery left foot pedal position 300 and the desired spin recovery right foot pedal position 301.
[0016] The described current left foot pedal position 302 and the current right foot pedal position 303 are used to display in real time the relative position relationship between the current left foot pedal, the current right foot pedal position and the flashing desired spin recovery left foot pedal position 300 and the desired spin recovery right foot pedal position 301.
[0017] The described desired spin recovery throttle position 400 is the desired spin recovery throttle position displayed after the aircraft enters the spin state. During the display process, the desired spin recovery throttle position 400 continuously flashes, so as to increase the pilot's attention and guide the pilot to operate the throttle to the area of the desired spin recovery throttle position 400.
[0018] The described current throttle position 401 displays in real time the actual position of the throttle manipulated by the current pilot, and is used to display in real time the relative position relationship between 401 and the flashing desired spin recovery throttle position 400.
[0019] The described control column and rudder horizontal scale 205, control column and rudder vertical scale 206, foot pedal scale 304, and throttle scale 402 are respectively used to indicate the position scales of the control column and rudder, left and right foot pedals, and throttle.
[0020] Advantages of the present invention: The present invention has rich dynamic display functions through the HUD, and can not only display the spin flight state, but also display the spin recovery auxiliary control of the control column and rudder, foot pedals and throttle. Its significance lies in effectively reducing the probability of the pilot's misjudgment of the spin under high oscillation conditions. At the same time, the displayed spin recovery auxiliary control can guide the pilot to perform correct spin recovery operations, avoid the deterioration of the spin state of the aircraft due to the pilot's misoperation, and further reduce the probability of spin accidents caused by the pilot's misjudgment or even misoperation. Description of the Drawings
[0021] Figure 1 Spin state and spin recovery auxiliary control HUD interface.
[0022] Figure 2 Cross-linking block diagram of the spin recovery auxiliary control module and the HUD system. Detailed implementation manners
[0023] The following will further elaborate on the present invention in conjunction with the accompanying drawings and embodiments. Due to the richness of the HUD interface display solution, embodiments of the present invention have designed a spin state and spin recovery assisted driving module and display method, which concretize the spin recovery assisted driving HUD display method of the present invention. Those skilled in the art should understand that these implementation manners are only used to explain the technical principle of the present invention and are not intended to limit the protection scope of the present invention.
[0024] Embodiment
[0025] S1. The spin recovery assisted driving module includes three sub-modules. As shown in the attached Figure 2 figure, they are an input module 501, an assisted driving module 502, and an output module 503 respectively.
[0026] S11. The input module 501 receives the aircraft flight state quantity 500 and parses state quantities such as the angle of attack α, yaw angular velocity r, control stick and rudder, foot pedals, and throttle.
[0027] S12. The assisted driving module 502 determines that the aircraft has entered the spin state and gives assisted driving information for spin recovery when the angle of attack α of the aircraft is greater than the stall angle of attack α s and the yaw angular velocity r is greater than the spin yaw angular velocity r s .
[0028] S13. The output module 503 outputs the spin state and assisted driving information to the HUD system 504, and the HUD system displays it in the form of the spin state and spin recovery assisted driving HUD interface 100 in the attached Figure 1 figure.
[0029] S2. The spin state and spin recovery assisted driving HUD interface is as shown in the attached Figure 1 figure, and specifically includes a HUD display frame 100, a spin horizontal state indicator 200, a spin longitudinal state indicator 201, a control stick and rudder operation boundary 202, an expected spin recovery control stick and rudder position 203, a current control stick and rudder position 204, an expected spin recovery left foot pedal position 300, an expected spin recovery right foot pedal position 301, a current left foot pedal position 302, a current right foot pedal position 303, an expected spin recovery throttle position 400, a current throttle position 401, as well as a control stick and rudder horizontal scale 205, a control stick and rudder vertical scale 206, a foot pedal scale 304, and a throttle scale 402.
[0030] S21. The HUD display frame 100 is as shown in the attached Figure 1As shown, taking the HUD system 504 that displays the spin state and the spin recovery autopilot as the carrier, when the aircraft meets the conditions described in S12, the HUD display frame will display the spin state and the spin recovery autopilot interface as shown in the appendix. Figure 1 The spin state and the spin recovery autopilot interface are as shown.
[0031] S22. The spin horizontal state indicator 200 and the spin longitudinal state indicator 201 are as shown in the appendix. Figure 1 The 200 indicates the horizontal rotation direction and speed of the aircraft's spin. After the aircraft meets the conditions described in S12, the solid dot of the 200 starts to rotate, and its rotation rate is the same as the absolute value of the aircraft's yaw angular velocity, so as to indicate the speed of the spin rotation. The rotation direction of the 200 is the same as the direction of the aircraft's spin. Counterclockwise rotation represents the aircraft's left spin, and clockwise rotation represents the aircraft's right spin. The 201 indicates the longitudinal direction of the aircraft's spin. The current display state of the 201 indicates that the aircraft is in a normal flight spin, and the display state after the 201 rotates 180 degrees indicates that the aircraft is in an inverted flight spin.
[0032] S23. The stick-rudder control boundary 202 is as shown in the appendix. Figure 1 It is the maximum stick-rudder control boundary of the aircraft, which is circular. At the same time, this ring serves as the spin horizontal state indicator 200, that is, the rotation trajectory of the solid dot, indicating the spin rate and the horizontal rotation direction state of the aircraft.
[0033] S24. The desired stick-rudder position 203 for spin recovery is as shown in the appendix. Figure 1 It shows the desired stick-rudder position for spin recovery after the aircraft enters the spin state. During the display process, the 203 keeps flashing to increase the pilot's attention and guide the pilot to operate the stick-rudder to the 203 area.
[0034] S25. The current stick-rudder position 204 is as shown in the appendix. Figure 1 It shows the actual position of the stick-rudder actually operated by the current pilot in real time, so as to show the relative position relationship between the 204 and the flashing 203 in real time.
[0035] S26. The desired left foot pedal position 300 for spin recovery and the desired right foot pedal position 301 for spin recovery are as shown in the appendix. Figure 1 The 300 is the desired left foot pedal position for spin recovery, and the 301 is the desired right foot pedal position for spin recovery. During the display process, both the 300 and the 301 keep flashing to increase the pilot's attention and guide the pilot to operate the left and right foot pedals to the 300 and 301 areas.
[0036] S27. The current left foot pedal position 302 and the current right foot pedal position 303 are as shown in the appendix. Figure 1As shown, 302 is the current left foot pedal position, and 303 is the current right foot pedal position. It is used to display in real time the relative position relationship between 302 and 303 and the flashing 300 and 301.
[0037] S28, the desired spin recovery throttle position 400 is as shown in the appendix Figure 1 As shown, it is to display the desired spin recovery throttle position after the aircraft enters the spin state. During the display process, 400 flashes continuously to improve the pilot's attention and guide the pilot to operate the throttle to the 400 area.
[0038] S29, the current throttle position 401 is as shown in the appendix Figure 1 As shown, it displays in real time the actual position of the throttle currently operated by the pilot, and is used to display in real time the relative position relationship between 401 and the flashing 400.
[0039] S210, the aileron-rudder lateral scale 205, the aileron-rudder longitudinal scale 206, the foot pedal scale 304, and the throttle scale 402 are as shown in the appendix Figure 1 As shown, they are respectively used to indicate the position scales of the aileron-rudder, the left and right foot pedals, and the throttle.
[0040] S3, the autopilot assistance module 502, when the angle of attack α of the aircraft is less than the stall angle of attack α s and the yaw angular velocity r is less than the spin yaw angular velocity r s in this case, it is determined that the aircraft has recovered from the spin, and the output module 503 closes the display interface 100 of the spin state and the spin recovery autopilot assistance on the HUD system 504, and exits the spin recovery autopilot assistance.
Claims
1. An aircraft spin recovery assisted driving HUD display method, characterized in that, Embed the spin recovery assist driving module into the aircraft platform and cross-link it with the on-board HUD system. The spin recovery assist driving module includes an input module (501), an assist driving module (502), and an output module (503). The input module (501) receives the aircraft flight state variables (500) and analyzes the angle of attack α, yaw angular velocity r, control column and rudder, pedal, and throttle state variables among them. The auxiliary flight control module (502) determines that the aircraft has entered a spin state and provides auxiliary flight control information for recovering from the spin when the angle of attack α of the aircraft is greater than the stall angle of attack α s and the yaw rate r is greater than the spin yaw rate r s The output module (503) gives the spin state and assist driving information to the HUD system (504), and the HUD system displays them in the form of a spin state and a spin recovery assist driving HUD interface.
2. The method for displaying an aircraft spin recovery assisted driving HUD according to claim 1, wherein The spin state and spin recovery assist driving HUD interface include a HUD display frame (100), a spin horizontal state indicator (200), a spin longitudinal state indicator (201), a control column and rudder operation boundary (202), an expected spin recovery control column and rudder position (203), a current control column and rudder position (204), an expected spin recovery left pedal position (300), an expected spin recovery right pedal position (301), a current left pedal position (302), a current right pedal position (303), an expected spin recovery throttle position (400), a current throttle position (401), as well as a control column and rudder horizontal scale (205), a control column and rudder longitudinal scale (206), a pedal scale 304, and a throttle scale (402).
3. The method for assisting in pulling out of an aircraft spin and displaying on a HUD for an autopilot according to claim 2, characterized in that, The spin horizontal state indicator (200) indicates the horizontal rotation direction and rotation speed of the aircraft spin; when the angle of attack α of the aircraft is greater than the stall angle of attack α s and the yaw angular velocity r is greater than the spin yaw angular velocity r s in this case, the solid dot of the spin horizontal state indicator (200) starts to rotate, and its rotation rate is the same as the absolute value of the aircraft yaw angular velocity, so as to indicate the speed of the spin rotation rate. The rotation direction of the spin horizontal state indicator (200) is the same as the direction of the aircraft spin. Counterclockwise rotation represents the left spin of the aircraft, and clockwise rotation represents the right spin of the aircraft.
4. The method for displaying an aircraft spin recovery assisted driving HUD according to claim 2, wherein, The spin longitudinal state indicator (201) indicates the longitudinal direction of the aircraft spin. The current display state of the spin longitudinal state indicator (201) indicates that the aircraft is in a normal flight spin, and the display state after the spin longitudinal state indicator (201) rotates 180 degrees indicates that the aircraft is in an inverted flight spin.
5. The method for assisting in recovering from an aircraft spin by using a head-up display (HUD) according to claim 2, characterized in that, The control column and rudder operation boundary (202) is the maximum control column and rudder operation boundary of the aircraft, which is circular. At the same time, this circle serves as the spin horizontal state indicator (200), that is, the rotational movement trajectory of the solid dot indicates the aircraft spin rate and horizontal rotation direction state.
6. The method for aircraft spin recovery assisted driving HUD display according to claim 2, wherein The expected spin recovery control column and rudder position (203) is the expected spin recovery control column and rudder position displayed after the aircraft enters the spin state. It continuously flashes during the display process to improve the pilot's attention and guide the pilot to operate the control column and rudder to the area of the spin recovery control column and rudder position (203).
7. The method for the aircraft spin recovery assisted driving HUD display according to claim 2, wherein The current control column and rudder position (204) real-time displays the actual position of the control column and rudder currently operated by the pilot, so as to real-time display the relative position relationship between the current control column and rudder position (204) and the flashing spin recovery control column and rudder position (203).
8. The method for assisting in recovering from an aircraft spin by using a HUD display according to claim 2, characterized in that, During the display process of the expected spin recovery left pedal position (300) and the expected spin recovery right pedal position (301), both the expected spin recovery left pedal position (300) and the expected spin recovery right pedal position (301) continuously flash to improve the pilot's attention and guide the pilot to operate the left and right pedals to the areas of the expected spin recovery left pedal position (300) and the expected spin recovery right pedal position (301).
9. The method for assisting in recovering from an aircraft spin by using a head-up display (HUD) according to claim 2, wherein The current left pedal position (302) and the current right pedal position (303) are used to display in real time the relative position relationship between the current left pedal and right pedal positions and the flashing desired spin recovery left pedal position (300) and desired spin recovery right pedal position (301).
10. The method for assisting in recovering from an aircraft spin and displaying on a HUD according to claim 2, characterized in that, The desired spin recovery throttle position (400) is the desired spin recovery throttle position displayed after the aircraft enters the spin state. During the display process, the desired spin recovery throttle position (400) flashes continuously to increase the pilot's attention and guide the pilot to operate the throttle to the area of the desired spin recovery throttle position (400).
11. The method for aircraft spin recovery assisted driving HUD display according to claim 2, wherein The current throttle position (401) displays in real time the actual position of the throttle manipulated by the current pilot, and is used to display the relative position relationship between the real-time display (401) and the flashing desired spin recovery throttle position (400).
12. The method for aircraft spin recovery assisted driving HUD display according to claim 2, characterized in that The lateral control stick and rudder scale (205), the longitudinal control stick and rudder scale (206), the pedal scale (304), and the throttle scale (402) are respectively used to indicate the position scales of the control stick and rudder, the left and right pedals, and the throttle.