TWI868447B - Aircraft auxiliary display system for avoiding spatial disorientation - Google Patents

Abstract

The present invention provides an aircraft auxiliary display system for avoiding spatial disorientation, comprising a central processing unit, a sensing module, an activation display unit and an electronic optical visual unit. The central processing unit includes a storage unit and is electrically connected to the activation display unit; the sensing module is electrically connected to the central processing unit and includes a flight data sensing unit; the activation display unit is electrically connected to the electronic optical visual unit.

Description

Aircraft auxiliary display system for avoiding spatial disorientation

The present invention provides an aircraft auxiliary display system, and in particular, relates to an aircraft auxiliary display system which can assist a pilot to quickly obtain various flight information and avoid spatial disorientation without external interference.

Aircraft are a very common means of transportation. Generally speaking, when traveling long distances, many passengers will take an aircraft to fly domestically or internationally for several hours to dozens of hours, so flight safety has become an important issue.

When a pilot is flying an aircraft, he needs to use the windshield and a large number of instruments to correctly judge the aircraft's flight information and its relative relationship with various external terrains and obstacles. However, if there are emergencies such as turbulence, bad weather, or abnormalities in the aircraft itself during flight, the pilot cannot observe the correct external information from the windshield of the aircraft to obtain the three-dimensional reference point, resulting in spatial disorientation, causing the aircraft to temporarily lose control. If the above emergency situation is not resolved, it will be a great flight risk for inexperienced pilots and all passengers.

The inventor then devoted all his efforts to research and developed an aircraft auxiliary display system that can help pilots quickly obtain various flight information and avoid spatial disorientation without external interference, in order to achieve the effect of improving flight safety.

The present invention provides an aircraft auxiliary display system for avoiding spatial disorientation, which comprises a central processing unit, a sensing module, an activation display unit and an electronic optical visual unit. The central processing unit comprises a storage unit and is electrically connected to the activation display unit; the sensing module is electrically connected to the central processing unit and comprises a flight data sensing unit; the flight data sensing unit comprises a pitch angle sensor, a roll angle sensor and a yaw angle sensor to respectively sense a pitch angle, a roll angle and a yaw angle of the aircraft; the activation display unit is electrically connected to the electronic optical visual unit. The display unit and the central processing unit are activated to display a virtual aerial environment image and a virtual ground environment image on the electronic optical visual unit according to at least one of the pitch angle being greater than a pitch angle standard threshold, the roll angle being greater than a roll angle standard threshold, and the yaw angle being greater than a yaw angle standard threshold. The virtual aerial environment image and the virtual ground environment image correspond to the pitch angle, the roll angle, and the yaw angle. The pitch angle standard threshold, the roll angle standard threshold, and the yaw angle standard threshold are stored in the storage unit.

In one embodiment, the display unit and the central processing unit are activated to display a virtual aircraft image on the electronic optical visual unit according to at least one of the pitch angle being greater than a standard pitch angle threshold, the roll angle being greater than a standard roll angle threshold, and the yaw angle being greater than a standard yaw angle threshold. The flight posture of the virtual aircraft image corresponds to the pitch angle, the roll angle, and the yaw angle, and the virtual aircraft image is stored in the storage unit.

In one embodiment, the display unit and the central processing unit are activated to display the flight attitude instrument image on the electronic optical visual unit based on at least one of the pitch angle being greater than the pitch angle standard threshold, the roll angle being greater than the roll angle standard threshold, and the yaw angle being greater than the yaw angle standard threshold. The flight attitude displayed by the flight attitude instrument image corresponds to the pitch angle, the roll angle, and the yaw angle, and the flight attitude instrument image is stored in the storage unit.

In one embodiment, the virtual aerial environment image and the virtual ground environment image are stored in a storage unit; or, the virtual aerial environment image and the virtual ground environment image are acquired by at least one image sensor outside the aircraft, and the image sensor is electrically connected to the central processing unit.

In one embodiment, the sensing module may include an air obstacle sensing unit, which senses a relative distance between an air obstacle and the aircraft, and activates the display unit and the central processing unit to display a virtual aircraft image, a virtual air environment image, a virtual ground environment image, and a relative distance between the air obstacle and the aircraft. An image and a virtual aerial obstacle image are stored in an electronic optical visual unit, the flight attitude of the virtual aircraft image corresponds to the pitch angle, the roll angle and the yaw angle, the relative distance between the virtual aircraft image and the virtual aerial obstacle image corresponds to the relative distance, and the virtual aircraft image, the virtual aerial obstacle image and the relative distance standard threshold are stored in a storage unit.

In one embodiment, the sensing module may include a ground obstacle sensing unit, which senses a relative height between a ground obstacle and the aircraft, and activates the display unit and the central processing unit to display a virtual aircraft image, a virtual air environment image, a virtual ground environment image, and a virtual ground environment image according to the relative height being less than a relative height standard threshold. The image and a virtual ground obstacle image are stored in the electronic optical visual unit. The flight attitude of the virtual aircraft image corresponds to the pitch angle, the roll angle and the yaw angle. The relative height of the virtual aircraft image and the virtual ground obstacle image corresponds to the relative height. The virtual aircraft image, the virtual ground obstacle image and the relative height standard threshold are stored in the storage unit.

In one embodiment, the electronic optical visual unit can be set on the windshield of the aircraft. The electronic optical visual unit can include a projection device electrically connected to the startup display unit. The startup display unit and the central processing unit adjust the luminous flux of the electronic optical visual unit according to at least one of the pitch angle being greater than the pitch angle standard threshold, the roll angle being greater than the roll angle standard threshold, and the yaw angle being greater than the yaw angle standard threshold, so that the projection device projects a virtual aerial environment image and a virtual ground environment image on the electronic optical visual unit.

In one embodiment, the electronic optical visual unit can be set on the windshield of the aircraft, and the display unit and the central processing unit are activated to adjust the luminous flux of the electronic optical visual unit according to at least one of the pitch angle being greater than the standard pitch angle threshold, the roll angle being greater than the standard roll angle threshold, and the yaw angle being greater than the standard yaw angle threshold, so as to display the virtual aerial environment image and the virtual ground environment image on an electronic display layer of the electronic optical visual unit.

In one embodiment, the electronic optical visual unit can be an auxiliary display device, and the electronic optical visual unit can be configured in the cockpit of the aircraft. The display unit and the central processing unit are activated to display the virtual aerial environment image and the virtual ground environment image on the electronic optical visual unit according to at least one of the pitch angle being greater than the pitch angle standard threshold, the roll angle being greater than the roll angle standard threshold, and the yaw angle being greater than the yaw angle standard threshold.

Thus, the aircraft auxiliary display system for avoiding spatial disorientation of the present invention can display a virtual aircraft image, a virtual air environment image, and a virtual ground environment image on an electronic optical visual unit by activating a display unit and a central processing unit according to at least one of a pitch angle greater than a standard pitch angle threshold, a roll angle greater than a standard roll angle threshold, and a yaw angle greater than a standard yaw angle threshold. Therefore, the pilot can quickly obtain various flight information without being disturbed by the outside world, thereby achieving the effect of improving flight safety.

In order to make the above features and advantages of the present invention more clearly understood, embodiments are specifically cited below and described in detail with reference to the accompanying drawings.

The above-mentioned and other technical contents, features and effects of the present invention will be clearly presented in the following detailed description of the preferred embodiments with reference to the drawings. It is worth mentioning that the directional terms mentioned in the following embodiments, such as up, down, left, right, front or back, etc., are only referenced to the directions of the attached drawings. Therefore, the directional terms used are for explanation rather than limitation of the present invention. In addition, in the following embodiments, the same or similar components will be labeled with the same or similar numbers. Furthermore, the display of the sun, moon or clouds, etc. in the virtual aerial environment image 238, the mountains, rivers or trees, etc. in the virtual ground environment image 226, the other aircraft in the virtual aerial obstacle image 216 and the buildings in the virtual ground obstacle image 224 described in the following FIGS. 2 to 4 is only an example and is not limited to being displayed simultaneously.

Please refer to Figures 1 and 2. As shown in the figures, the aircraft auxiliary display system 1 for avoiding spatial disorientation of the present embodiment is applicable to an aircraft, wherein the aircraft is, for example, a private civil aircraft, a commercial civil aircraft, a military civil aircraft or other aircraft that can fly in the air. The aircraft auxiliary display system 1 of the present embodiment includes a central processing unit 100 (such as a central processor or a processing circuit or processing chip including a central processor), a sensing module 200, an activation display unit 300 (such as an activation display chip or an activation display circuit) and an electronic optical visual unit 2 (such as a display). The central processing unit 100 includes a storage unit 110 (such as a memory or a hard disk) and is electrically connected to the startup display unit 300; the sensing module 200 is electrically connected to the central processing unit 100 and includes a flight data sensing unit 230, the flight data sensing unit 230 includes a pitch angle sensor 2311, a roll angle sensor 2321 and a yaw angle sensor 2331 to respectively sense a pitch angle 231, a roll angle 232 and a yaw angle 233 of the aircraft; the startup display unit 300 is electrically connected to the electronic optical visual unit 2. The display unit 300 and the central processing unit 100 are activated to display a virtual aerial environment image 238 and a virtual aerial environment image 238 according to at least one of the pitch angle 231 being greater than a pitch angle standard threshold 111, the roll angle 232 being greater than a roll angle standard threshold 112, and the yaw angle 233 being greater than a yaw angle standard threshold 113. The virtual ground environment image 226 is in the electronic optical visual unit 2 . The virtual aerial environment image 238 and the virtual ground environment image 226 correspond to the pitch angle 231 , the roll angle 232 , and the yaw angle 233 . The pitch angle standard threshold 111 , the roll angle standard threshold 112 , and the yaw angle standard threshold 113 are stored in the storage unit 110 . In addition, the virtual aerial environment image 238 and the virtual ground environment image 226 are environment images on the flight path of the aircraft. The virtual aerial environment image 238 and the virtual ground environment image 226 can be pre-captured or drawn and then stored in the storage unit 110; or, the virtual aerial environment image 238 and the virtual ground environment image 226 can be obtained by an image sensor 6 outside the aircraft. The image sensor 6 is electrically connected to the central processing unit 100, and the number of the image sensor 6 can be one or more.

Specifically, when the pilot in the cockpit 5 is flying the aircraft normally, the pilot can observe correct external information, such as three-dimensional reference points, weather conditions, relative directions, etc., through the windshield 4 of the aircraft. However, when the flight encounters emergency conditions such as turbulence, bad weather or thick clouds, the pilot cannot observe correct external information through the windshield 4 of the aircraft to obtain three-dimensional reference points, causing the pilot to be spatially disoriented. When the pilot is spatially disoriented, he often improperly operates (or controls) the aircraft, causing the aircraft to exceed the safe angle of flight and temporarily lose control, resulting in danger. At this time, the display unit 300 and the central processing unit 100 are activated to calculate whether the pitch angle 231 is greater than the pitch angle standard threshold 111, whether the roll angle 232 is greater than the roll angle standard threshold 112, and whether the yaw angle 233 is greater than the yaw angle standard threshold 113. If at least one of the pitch angle 231 is greater than the pitch angle standard threshold 111, the roll angle 232 is greater than the roll angle standard threshold 112, and the yaw angle 233 is greater than the yaw angle standard threshold 113 occurs, the display unit 300 and the central processing unit 100 are activated to display the virtual aerial environment image 238 and the virtual ground environment image 226 on the electronic optical visual unit 2. Since the electronic optical visual unit 2 can display the virtual aerial environment image 238 and the virtual ground environment image 226, invalid external information will not interfere with the pilot, and the pilot can obtain external information through the electronic optical visual unit 2 and use the displayed image as a reference point to quickly grasp various flight information of the aircraft, thereby enabling the pilot to perform correct operations and corrections according to the flight conditions to avoid spatial disorientation, thereby achieving the effect of improving flight safety.

In addition, if at least one of the following occurs: the pitch angle 231 is greater than the pitch angle standard threshold 111, the roll angle 232 is greater than the roll angle standard threshold 112, and the yaw angle 233 is greater than the yaw angle standard threshold 113, the display unit 300 and the central processing unit 100 may also display the virtual aircraft image 234 or the flight attitude instrument image 239 on the electronic optical The virtual aircraft image 234 corresponds to the pitch angle 231, the roll angle 232 and the yaw angle 233 in the visual unit 2. The flight attitude displayed by the flight attitude meter image 239 corresponds to the pitch angle 231, the roll angle 232 and the yaw angle 233. The virtual aircraft image 234 or the flight attitude meter image 239 can be stored in the storage unit 110. In this way, the pilot can further achieve the effect of improving the operation safety through the virtual aircraft image 234 or the flight attitude meter image 239.

Please refer to FIG. 1 and FIG. 2 again. As shown in the figure, in one embodiment, the above emergency situation may include other flying objects such as aircraft or birds rapidly approaching the aircraft carrying the aircraft auxiliary display system 1. To this end, the sensing module 200 may include an air obstacle sensing unit 210 (for example, an air obstacle sensor or a Doppler radar and arranged on the nose and wings on both sides), and the data transmitted by the air obstacle sensing unit 210 includes a relative distance and a relative speed between an air obstacle and the aircraft. When the central processing unit 100 receives these data, the display unit 300 and the central processing unit 100 are activated to calculate whether the relative distance is less than a relative distance standard threshold 114. If the relative distance is less than the relative distance standard threshold 114, the display unit 300 and the central processing unit 100 are activated to display the relative distance 212, the relative speed 214, the virtual aircraft image 234, the virtual aerial environment image 238, the virtual ground environment image 226 and the virtual aerial obstacle image 216 on the electronic optical visual unit 2. The flight attitude of the virtual aircraft image 234 corresponds to the pitch angle 231, the roll angle 232 and the yaw angle 233. The relative distance between the virtual aircraft image 234 and the virtual air obstacle image 216 corresponds to the relative distance 212. The relative speed between the virtual aircraft image 234 and the virtual air obstacle image 216 corresponds to the relative speed 214. The virtual aircraft image 234, the virtual air obstacle image 216 and the relative distance standard threshold 114 are stored in the storage unit 110. Thus, when the pilot sees the relative distance 212, the relative speed 214, the virtual aircraft image 234, the virtual air environment image 238, the virtual ground environment image 226, and the virtual air obstacle image 216, he can quickly know the approaching air obstacle and adjust the flight direction of the aircraft to avoid it.

Please refer to FIG. 1 and FIG. 2 again. As shown in the figure, in one embodiment, since the aircraft may be closer to obstacles such as mountains or skyscrapers below the aircraft during flight, in order to prevent these obstacles from affecting flight safety, the sensing module 200 may include a ground obstacle sensing unit 220 (e.g., a ground obstacle sensor or an image sensor disposed at the bottom of the nose and near the landing gear), and the data transmitted by the ground obstacle sensing unit 220 includes a relative height between the ground obstacle and the aircraft. When the central processing unit 100 receives the data, the display unit 300 and the central processing unit 100 are activated to calculate whether the relative height is less than a relative height standard threshold 115. If the relative height is less than the relative height standard threshold 115, the display unit 300 and the central processing unit 100 are activated to display the relative height 222, the virtual aircraft image 234, the virtual aerial environment image 238, the virtual ground environment image 226 and the virtual ground obstacle image 224 on the electronic optical visual unit 2. The flight attitude of the virtual aircraft image 234 corresponds to the pitch angle 231 , the roll angle 232 , and the yaw angle 233 . The relative heights of the virtual aircraft image 234 and the virtual ground obstacle image 224 correspond to the relative height 222 . The virtual aircraft image 234 , the virtual ground obstacle image 224 , and the relative height standard threshold 115 are stored in the storage unit 110 . Thus, when the pilot sees the relative altitude 222, the virtual aircraft image 234, the virtual air environment image 238, the virtual ground environment image 226, and the virtual ground obstacle image 224, he can quickly know whether the aircraft maintains a safe distance from the ground obstacle and dynamically adjust the altitude of the aircraft accordingly.

Please refer to Figure 2 again. As shown in the figure, in one embodiment, in order to ensure that the aircraft remains on the correct flight route and maintains a stable flight speed and altitude, the flight data sensing unit 230 may also include a direction sensor, a speed sensor, an altitude sensor and a weather sensor, and the data transmitted by the flight data sensing unit 230 also includes a flight direction, a flight speed, a flight altitude and a weather data of the flight environment of the aircraft. When the central processing unit 100 receives these data, the display unit 300 and the central processing unit 100 are activated to assist in displaying a direction information 235 corresponding to the flight direction, a speed 236 corresponding to the flight speed, an altitude 237 corresponding to the flight altitude, and a weather state image formed by the central processing unit 100 according to the weather data on the electronic optical visual unit 2, and the weather state image is stored in the storage unit 110. In this way, the pilot can quickly judge whether the aircraft is navigating on the correct route through the direction information 235, speed 236, altitude 237 and the weather state image, so as to reduce the burden of the pilot. In addition, the electronic optical visual unit 2 can also display a day with sunlight as shown in FIG. 2 or a night with moonlight as shown in FIG. 3 , so that the image displayed by the electronic optical visual unit 2 is more consistent with the pilot's operating environment.

Please refer to FIG. 1 and FIG. 2 again. As shown in the figure, in one embodiment, the electronic optical visual unit 2 can be arranged on the windshield 4 of the aircraft (for example, the electronic optical visual unit 2 can be overlapped on the windshield 4 and located in the cockpit 5 of the aircraft, or the electronic optical visual unit 2 can be arranged in the windshield 4, or the electronic optical visual unit 2 can be arranged as the windshield 4). The electronic optical visual unit 2 can be an electronic display panel that can change the brightness of light and includes a projection device 240 electrically connected to the start display unit 300. The start display unit 3 00 and the central processing unit 100 adjust the luminous flux of the electronic optical visual unit 2 according to at least one of the pitch angle 231 being greater than the pitch angle standard threshold 111, the roll angle 232 being greater than the roll angle standard threshold 112, and the yaw angle 233 being greater than the yaw angle standard threshold 113 (for example, lowering the luminous flux so that the external light of the aircraft will not affect the readability of the image), so that the projection device 240 projects the virtual aircraft image 234, the virtual aerial environment image 238, and the virtual ground environment image 226 onto the electronic optical visual unit 2. Thus, when there is no emergency in the aircraft, the pilot can fly the aircraft through the electronic optical visual unit 2 and the windshield 4, and when there is an emergency in the aircraft, the pilot can fly the aircraft through the electronic optical visual unit 2. In addition, the electronic optical visual unit 2 of this embodiment can also be applied to an emergency in which an aircraft encounters an obstacle in the air or an obstacle on the ground.

Please refer to FIG. 1 and FIG. 3 again. As shown in the figure, in one embodiment, the electronic optical visual unit 2 can be arranged on the windshield 4 of the aircraft (for example, the electronic optical visual unit 2 can be overlapped on the windshield 4 and located in the cockpit 5 of the aircraft, or the electronic optical visual unit 2 can be arranged in the windshield 4, or the electronic optical visual unit 2 can be arranged as the windshield 4). The electronic optical visual unit 2 can be an electronic display panel that can change the brightness of light and includes an electronic display layer 21 (for example, an electronic display film) that is electrically connected to the activation display unit 300. The display unit 300 and the central processing unit 100 adjust the light flux of the electronic optical visual unit 2 (for example, lowering the light flux so that the external light of the aircraft does not affect the readability of the image) according to at least one of the pitch angle 231 being greater than the pitch angle standard threshold 111, the roll angle 232 being greater than the roll angle standard threshold 112, and the yaw angle 233 being greater than the yaw angle standard threshold 113, so as to display the virtual aircraft image 234, the virtual aerial environment image 238, and the virtual ground environment image 226 on the electronic display layer 21 of the electronic optical visual unit 2. Thus, when there is no emergency in the aircraft, the pilot can fly the aircraft through the electronic optical visual unit 2 and the windshield 4, and when there is an emergency in the aircraft, the pilot can fly the aircraft through the electronic optical visual unit 2. In addition, the electronic optical visual unit 2 of this embodiment can also be applied to an emergency in which an aircraft encounters an obstacle in the air or an obstacle on the ground.

Please refer to FIG. 1 and FIG. 4 again. As shown in the figure, in one embodiment, the electronic optical visual unit 2 can be an auxiliary display device (such as an auxiliary display), and the electronic optical visual unit 2 is disposed in the cockpit 5 of the aircraft. The display unit 300 and the central processing unit 100 are activated according to the pitch angle 231 being greater than the pitch angle standard threshold 111, At least one of the roll angle 232 being greater than the roll angle standard threshold 112 and the yaw angle 233 being greater than the yaw angle standard threshold 113 displays the virtual aircraft image 234, the virtual air environment image 238, and the virtual ground environment image 226 on the electronic optical visual unit 2 (e.g., the display method of the electronic optical visual unit 2 in FIG. 3 ). In this way, when the aircraft is not in an emergency, the pilot can fly the aircraft through the windshield 4, and when the aircraft is in an emergency, the pilot can fly the aircraft through the electronic optical visual unit 2. In addition, the electronic optical visual unit 2 of this embodiment can also be applied to emergency situations of air obstacles or ground obstacles in aircraft.

The present invention has been disclosed in the above with preferred embodiments, but those skilled in the art should understand that the above embodiments are only used to describe the present invention and should not be interpreted as limiting the scope of the present invention. It should also be noted that all changes and substitutions equivalent to the above embodiments should be considered to be within the scope of the present invention. Therefore, the protection scope of the present invention shall be based on the scope defined by the patent application.

1: Aircraft auxiliary display system 100: Central processing unit 110: Storage unit 111: Pitch angle standard threshold 112: Roll angle standard threshold 113: Yaw angle standard threshold 114: Relative distance standard threshold 115: Relative height standard threshold 2: Electronic optical visual unit 21: Electronic display layer 200: Sensing module 210: Air obstacle sensing unit 212: Relative distance 214: Relative speed 216: Virtual air obstacle image 220: Ground obstacle sensing unit 222: Relative height 224: Virtual ground obstacle image 226: Virtual ground environment image 230: Flight data sensing unit 231: Pitch angle 2311: Pitch angle sensor 232: Roll angle 2321: Roll angle sensor 233: Yaw angle 2331: Yaw angle sensor 234: Virtual aircraft image 235: Position information 236: Speed 237: Altitude 238: Virtual air environment image 239: Flight attitude instrument image 240: Projection device 300: Start display unit 4: Windshield 5: Cockpit 6: Image sensor

FIG1 is a schematic diagram of a structural block diagram of an embodiment of an aircraft auxiliary display system for avoiding spatial disorientation of the present invention. FIG2 is a schematic diagram of the first embodiment of the aircraft auxiliary display system for avoiding spatial disorientation of the present invention. FIG3 is a schematic diagram of the second embodiment of the aircraft auxiliary display system for avoiding spatial disorientation of the present invention. FIG4 is a schematic diagram of the third embodiment of the aircraft auxiliary display system for avoiding spatial disorientation of the present invention.

1: Aircraft auxiliary display system

100: Central processing unit

110: Storage unit

111: Standard pitch angle threshold

112: Rolling angle standard threshold

113: Yaw angle standard threshold

114: Relative distance standard threshold

115: Relative height standard threshold

2:Electronic optical visual unit

21: Electronic display layer

200:Sensor module

210: Aerial obstacle sensing unit

220: Ground obstacle sensing unit

230: Flight data sensing unit

2311: Pitch angle sensor

2321:Rolling angle sensor

2331: Yaw angle sensor

240: Projection device

300: Start the display unit

6: Image sensor

Claims (9)

An aircraft auxiliary display system for avoiding spatial disorientation comprises: A central processing unit, including a storage unit; A sensing module, electrically connected to the central processing unit and comprising: A flight data sensing unit, including a pitch angle sensor, a roll angle sensor and a yaw angle sensor to respectively sense a pitch angle, a roll angle and a yaw angle of the aircraft; An activation display unit, electrically connected to the central processing unit; and An electronic optical visual unit, electrically connected to the activation display unit; The activation display unit and the central processing unit display a virtual aerial environment image and a virtual ground environment image on the electronic optical visual unit according to at least one of the pitch angle being greater than a pitch angle standard threshold, the roll angle being greater than a roll angle standard threshold, and the yaw angle being greater than a yaw angle standard threshold. The virtual aerial environment image and the virtual ground environment image correspond to the pitch angle, the roll angle, and the yaw angle. The pitch angle standard threshold, the roll angle standard threshold, and the yaw angle standard threshold are stored in the storage unit. An aircraft auxiliary display system as described in claim 1, wherein the activation display unit and the central processing unit display a virtual aircraft image on the electronic optical visual unit based on at least one of the pitch angle being greater than the pitch angle standard threshold, the roll angle being greater than the roll angle standard threshold, and the yaw angle being greater than the yaw angle standard threshold, the flight posture of the virtual aircraft image corresponds to the pitch angle, the roll angle, and the yaw angle, and the virtual aircraft image is stored in the storage unit. An aircraft auxiliary display system as described in claim 1, wherein the startup display unit and the central processing unit display a flight attitude instrument image on the electronic optical visual unit based on at least one of the pitch angle being greater than the pitch angle standard threshold, the roll angle being greater than the roll angle standard threshold, and the yaw angle being greater than the yaw angle standard threshold, the flight attitude displayed by the flight attitude instrument image corresponds to the pitch angle, the roll angle, and the yaw angle, and the flight attitude instrument image is stored in the storage unit. An aircraft auxiliary display system as described in claim 1, wherein the virtual aerial environment image and the virtual ground environment image are stored in the storage unit; or, the virtual aerial environment image and the virtual ground environment image are obtained by at least one image sensor outside the aircraft, and the image sensor is electrically connected to the central processing unit. The aircraft auxiliary display system as described in claim 1, wherein the sensing module includes an air obstacle sensing unit, the air obstacle sensing unit senses a relative distance between an air obstacle and the aircraft, the activation display unit and the central processing unit display a virtual aircraft image, the virtual air environment image, the virtual A ground environment image and a virtual air obstacle image are stored in the electronic optical visual unit. The flight attitude of the virtual aircraft image corresponds to the pitch angle, the roll angle and the yaw angle. The relative distance between the virtual aircraft image and the virtual air obstacle image corresponds to the relative distance. The virtual aircraft image, the virtual air obstacle image and the relative distance standard threshold are stored in the storage unit. The aircraft auxiliary display system as described in claim 1, wherein the sensing module includes a ground obstacle sensing unit, the ground obstacle sensing unit senses a relative height between a ground obstacle and the aircraft, the activation display unit and the central processing unit display a virtual aircraft image, the virtual air environment image, the virtual A ground environment image and a virtual ground obstacle image are stored in the electronic optical visual unit. The flight attitude of the virtual aircraft image corresponds to the pitch angle, the roll angle and the yaw angle. The relative height of the virtual aircraft image and the virtual ground obstacle image corresponds to the relative height. The virtual aircraft image, the virtual ground obstacle image and the relative height standard threshold are stored in the storage unit. An aircraft auxiliary display system as described in claim 1, wherein the electronic optical visual unit is arranged on the windshield of the aircraft, and the electronic optical visual unit includes a projection device electrically connected to the activation display unit, and the activation display unit and the central processing unit adjust the luminous flux of the electronic optical visual unit according to at least one of the pitch angle being greater than the pitch angle standard threshold, the roll angle being greater than the roll angle standard threshold, and the yaw angle being greater than the yaw angle standard threshold, so that the projection device projects the virtual aerial environment image and the virtual ground environment image onto the electronic optical visual unit. An aircraft auxiliary display system as described in claim 1, wherein the electronic optical visual unit is arranged on the windshield of the aircraft, and the activation display unit and the central processing unit adjust the luminous flux of the electronic optical visual unit according to at least one of the pitch angle being greater than the pitch angle standard threshold, the roll angle being greater than the roll angle standard threshold, and the yaw angle being greater than the yaw angle standard threshold, so as to display the virtual aerial environment image and the virtual ground environment image on an electronic display layer of the electronic optical visual unit. An aircraft auxiliary display system as described in claim 1, wherein the electronic optical visual unit is an auxiliary display device, and the electronic optical visual unit is configured in the cockpit of the aircraft, and the startup display unit and the central processing unit display the virtual aerial environment image and the virtual ground environment image on the electronic optical visual unit according to at least one of the pitch angle being greater than the pitch angle standard threshold, the roll angle being greater than the roll angle standard threshold, and the yaw angle being greater than the yaw angle standard threshold.

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