A wireless data transmission method and system for an onboard display device

Abstract

The application discloses a kind of wireless data transmission methods and systems for airborne display device.Method includes: obtaining airborne display data, it is divided into multiple spatial importance slice layers with different priority according to content security correlation;Through airborne inertial navigation data, aircraft real-time spatial attitude parameters are obtained, and the safety transmission quota of application layer can be adjusted in combination with communication hardware rated parameter prediction;According to the proportional relationship of the quota and preset threshold, the bandwidth allocation weight of each slice layer is dynamically adjusted, and encoding and wireless transmission are carried out accordingly.The application uses the geometric situation of fuselage to establish a defensive prediction model, actively sacrifices non-critical background layers in conditions such as bandwidth drop, ensures the absolute real-time and lossless transmission of core command vector data, effectively overcomes the perception lag and link collapse problem of traditional mechanism, and significantly improves the safety of airborne display system under extreme attitude.

Description

Technical Field

[0001] This invention relates to the field of avionics wireless communication technology, specifically to a wireless data transmission method and system for airborne display devices, which utilizes the space attitude of the aircraft to predict wireless transmission quotas and perform data processing based on spatial importance slices. Background Technology

[0002] With the rapid development of modern avionics technology, the amount of information carried by airborne display devices (such as head-up displays (HUDs) and multifunction displays (MFDs) is increasing daily, and wireless links have become an important means of data transmission. During high-dynamic flight missions, the real-time performance and reliability of airborne display data are directly related to the pilot's situational awareness and flight safety.

[0003] Existing wireless transmission technologies are typically based on a signal-to-noise ratio (SNR) feedback mechanism at the receiver. Under this mechanism, the system dynamically adjusts the coding rate by monitoring channel quality in real time. However, airborne environments are highly dynamic. When an aircraft performs severe maneuvers, the stability of the wireless link is drastically affected by the aircraft's spatial attitude, and traditional feedback adjustment modes show significant limitations in dealing with such sudden link fluctuations. Furthermore, in environments with external electronic interference, the effective SNR of the wireless channel is severely compressed. This sudden interference disrupts the orthogonality of subcarriers, leading to a surge in the bit error rate and frequent triggering of the physical layer's redundant retransmission mechanism, rapidly depleting the reserved fading margin.

[0004] In practical airborne applications, existing technologies mainly face the following three technical challenges: Traditional technologies employ a closed-loop "measurement-feedback" mechanism, where adjustment commands always lag behind changes in the channel environment. During rapid rolls or sharp dives, the attenuation of radio signals typically occurs on the order of milliseconds. This feedback lag can lead to display stuttering, screen tearing, or loss of critical parameters before link adjustments are complete, failing to meet the extremely low latency requirements of avionics systems.

[0005] Most existing wireless transmission models treat the communication antenna as an ideal point source, ignoring the physical shielding effect of the aircraft's metallic fuselage on signals under extreme attitudes. When the aircraft's attitude angle changes, causing the fuselage to lie between the antenna and the receiver's line-of-sight (LoS), especially under external electronic interference, the signal can drop sharply or even be interrupted. Due to the lack of prediction of the aircraft's geometric state, current technologies cannot implement effective defensive transmission strategies before the signal is completely blocked.

[0006] Conventional video compression algorithms (such as H.264 or H.265) typically apply uniform pixel processing to the entire frame. Under severely limited bandwidth, these algorithms reduce overall sharpness to maintain transmission stability. This results in critical vector data affecting flight safety (such as altitude, heading, attitude lines, and warning characters) becoming blurred along with non-critical background maps and terrain textures. This "equal-weighted compression" mode can severely interfere with pilots' extraction of core flight parameters in extreme environments, posing a significant safety hazard. Summary of the Invention

[0007] To achieve the above-mentioned objectives, the present invention provides a wireless data transmission method for airborne display devices, comprising: Step S1: Acquire airborne display data and divide the airborne display data into multiple spatial importance slice layers with different priorities according to the security relevance of the displayed content; Step S2: Obtain the real-time spatial attitude parameters of the aircraft through airborne inertial navigation data, and predict the application layer's schedulable safe transmission quota by combining the rated parameters of the wireless communication hardware. Step S3: Dynamically adjust the bandwidth allocation weight of each spatial importance slice layer according to the ratio between the secure transmission quota and the preset threshold; Step S4: Encode the airborne display data according to the adjusted bandwidth allocation weights and perform wireless transmission.

[0008] Furthermore, in step S1, the airborne display data is divided into multiple spatial importance slice layers, specifically including: The core vector data affecting flight safety is divided into the first priority layer; The sensor video stream data is divided into a second priority layer; Non-critical electronic maps and terrain texture data are classified as the third priority layer.

[0009] Furthermore, step S2, which predicts the secure transmission quota, specifically includes: The roll and pitch angles of the aircraft are output in real time through the airborne inertial reference system, and the relative radial velocity of the aircraft relative to the receiver is obtained. The secure transmission quota is calculated based on the roll angle, pitch angle, relative radial velocity, and the rated maximum net throughput of the wireless communication hardware under an ideal line-of-sight link.

[0010] Optionally, the calculation process for the secure transmission quota specifically includes: The rated maximum net throughput is multiplied by the cosine of the roll angle and the cosine of the pitch angle, respectively, to describe the directional loss and energy shift caused by the aircraft attitude. By further combining the ratio of relative radial velocity to electromagnetic wave propagation speed, a Doppler frequency shift correction factor is introduced for product operation to obtain the final safe transmission quota.

[0011] Furthermore, step S3 involves dynamically adjusting the bandwidth allocation weights for each spatially important slice layer, specifically including: When the predicted secure transmission quota is lower than the first preset threshold and higher than the second preset threshold, the background space thinning logic is triggered to reduce the bandwidth allocation of the third priority layer in order to ensure the transmission bandwidth of the first and second priority layers. When the predicted secure transmission quota is lower than the second preset threshold, the system enters vector maintenance mode, stops transmission in the second and third priority layers, and concentrates all bandwidth resources in the first priority layer.

[0012] Furthermore, the first preset threshold is 0.7 times the rated maximum net throughput, and the second preset threshold is 0.3 times the rated maximum net throughput.

[0013] Furthermore, to achieve the above objectives, the present invention also provides a wireless data transmission system for airborne display devices, which applies the wireless data transmission method for airborne display devices described above, including: Slicing module: used to acquire airborne display data and divide the airborne display data into multiple spatial importance slice layers with different priorities according to the security relevance of the displayed content; Quota prediction module: used to obtain the real-time spatial attitude parameters of the aircraft through airborne inertial navigation data, and combine them with the rated parameters of wireless communication hardware to predict the application layer's schedulable safe transmission quota. Weighting adjustment module: used to dynamically adjust the bandwidth allocation weight of each spatial importance slice layer according to the ratio between the secure transmission quota and the preset threshold; Data transmission module: used to encode the airborne display data according to the adjusted bandwidth allocation weights and perform wireless transmission.

[0014] The secure transmission quota of this invention specifically refers to the application-layer schedulable secure quota. Its technical essence is to establish a priori service access envelope using geometric space projection. Even if the physical layer retains some capacity through antenna diversity, this invention still tends to reduce the application-layer quota to an extremely low level during moments of dramatic attitude changes. This aims to completely eliminate buffer congestion caused by repeated retransmissions of non-critical data in unstable channels, thereby using all remaining physical bandwidth to ensure lossless transmission of L1-level core vector data. This "over-capacity protection" logic is the key to improving the reliability of situational awareness in highly dynamic environments.

[0015] The technical effects of this invention are as follows: This invention directly acquires the aircraft's real-time attitude parameters (roll, pitch, etc.) from the airborne bus and uses a geometric-physical model to adjust the data compression structure before a substantial degradation in wireless link quality occurs (within milliseconds). This "defensive prediction" mechanism completely solves the perception lag problem caused by traditional "measurement-feedback" closed-loop systems, ensuring that the system has already completed data traffic degradation and protection in advance, even when the aircraft significantly blocks signals.

[0016] This invention addresses the unique business logic of airborne displays by decoupling display content through spatial importance slicing. Under conditions of drastically reduced bandwidth, the system can decisively sacrifice non-critical background maps (L3 layer) and sensor video (L2 layer), concentrating all resources on ensuring lossless transmission of command vectors (L1 layer). Even in extremely low signal-to-noise ratio environments with severe airframe obstruction and bandwidth dropping below 30%, pilots can still obtain core parameters such as altitude, attitude, and alarms in real time, significantly improving flight safety in extreme dynamic environments.

[0017] This invention breaks away from the blind approach of traditional whole-frame pixel compression, achieving deep coupling between service content and physical link status. The system can automatically perform a smooth switch from "background space thinning" to "vector multipath redundancy" based on predicted quotas. This not only effectively suppresses latency jitter caused by link fluctuations, but also ensures the continuous smoothness of critical navigation data at the perception layer through a "bandwidth for reliability" strategy.

[0018] The first-order linear geometric projection model employed in this invention avoids complex logarithmic operations and the experimental antenna gain coefficients specific to certain aircraft models, resulting in extremely low computational overhead. This approach allows the algorithm to be perfectly embedded in resource-constrained airborne mission computers, supporting millisecond-level real-time responses, and is independent of specific aircraft architectures or wireless communication protocols, making it highly valuable for engineering application. Attached Figure Description

[0019] Figure 1 This is a flowchart illustrating a wireless data transmission method for airborne display devices according to the present invention. Figure 2 This is a schematic diagram of the architecture of a wireless data transmission system for airborne display devices as described in this invention. Detailed Implementation

[0020] The present invention will now be described in detail with reference to the specific embodiments shown in the accompanying drawings. However, these embodiments do not limit the present invention, and any structural, methodological, or functional modifications made by those skilled in the art based on these embodiments are included within the scope of protection of the present invention.

[0021] If the present invention involves orientation (e.g., up, down, left, right, front, back, outside, inside, etc.) when described, then the orientations involved need to be defined.

[0022] The scope of the embodiments described herein includes the entire scope of the claims and all available equivalents thereof. Throughout this document, the terms “first,” “second,” etc., are used only to distinguish one element from another without requiring or implying any actual relationship or order between the elements. Indeed, a first element can also be referred to as a second element, and vice versa. Furthermore, the terms “comprising,” “including,” or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure, apparatus, or device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a structure, apparatus, or device. Without further limitations, an element defined by the phrase “comprising one…” does not exclude the presence of other identical elements in the structure, apparatus, or device that includes said element. The various embodiments described herein are presented in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably.

[0023] The terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer" used in this document to indicate orientation or positional relationships are based on the orientation or positional relationships shown in the accompanying drawings and are used only for the convenience of describing this document and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the invention. In the description herein, unless otherwise specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to mechanical or electrical connections, or internal connections between two elements, or direct connections or indirect connections through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms according to the specific circumstances.

[0024] The following is in conjunction with the appendix Figures 1 to 2 The wireless data transmission method and system for airborne display devices provided in the embodiments of this application will be described in detail.

[0025] This embodiment provides a wireless data transmission method for airborne display devices. This scheme breaks away from the traditional "measurement-feedback" lag mechanism of wireless transmission, actively predicting link loss by acquiring the aircraft's real-time attitude, and dynamically allocating bandwidth based on the spatial importance of the data content. The method specifically includes the following steps: Step S1: Obtain airborne display data and divide the airborne display data into multiple spatial importance slice layers with different priorities according to the security relevance of the displayed content.

[0026] In this step, the present invention breaks away from the traditional "equal-weight compression" mode of uniform pixel processing for the entire frame of an image. In existing technologies, bandwidth limitations can lead to synchronized blurring of all data, severely interfering with the pilot's extraction of core flight parameters. To solve this technical problem, this embodiment decouples the display content according to spatial coordinates and business logic, specifically dividing it into: First Priority Layer (L1): This layer contains core vector data that affects flight safety, including but not limited to altitude, airspeed, attitude guidance, heading, and system warning characters. This type of data is small in volume but has extremely high real-time requirements, serving as the baseline for maintaining pilot situational awareness.

[0027] The second priority layer (L2) involves sensor video stream data, such as infrared photoelectric sphere images and real-world video generated by synthetic vision systems (SVS). This type of data occupies a large proportion of bandwidth and is used to assist pilots in providing visual references in complex environments.

[0028] The third priority layer (L3) involves non-critical background data such as electronic maps, terrain textures, and weather radar base maps. This type of data mainly serves to enhance and assist, and its clarity or update rate can be sacrificed when the link is limited.

[0029] Step S2: Obtain the real-time spatial attitude parameters of the aircraft through airborne inertial navigation data, and predict the application layer's schedulable safe transmission quota by combining the rated parameters of the wireless communication hardware.

[0030] Since airborne wireless communication antennas typically have a certain directionality, and the metal structure of the fuselage will produce a physical shielding effect at a specific angle and under external electronic interference, this embodiment can predict channel changes in advance by judging the attitude.

[0031] The system outputs the aircraft's roll angle in real time via the onboard inertial reference system (IRS). and pitch angle Obtain the relative radial velocity of the aircraft with respect to the receiver. And the angle between the velocity vector and the communication link axis. .

[0032] The secure transmission quota of this invention specifically refers to the application-layer schedulable secure quota. Its technical essence is to establish a priori service access envelope using geometric space projection. Even if the physical layer retains some capacity through antenna diversity, this invention still tends to reduce the application-layer quota to an extremely low level during moments of dramatic attitude changes. This aims to completely eliminate buffer congestion caused by repeated retransmissions of non-critical data in unstable channels, thereby using all remaining physical bandwidth to ensure lossless transmission of L1-level core vector data. This "over-capacity protection" logic is the key to improving the reliability of situational awareness in highly dynamic environments.

[0033] Based on the above parameters, the secure transmission quota is calculated using a preset physical model. : The meanings of the variables are explained as follows: The rated maximum net throughput of wireless communication hardware under ideal line-of-sight link conditions. Preset by the physical layer protocol standard of the communication module.

[0034] Roll angle: Describes the loss of directional accuracy caused by the aircraft rotating around its longitudinal axis. It is output in real time by the onboard inertial reference system (IRS).

[0035] Aircraft pitch angle: Describes the energy component shift caused by the aircraft pitching up or down. Outputted in real time by the onboard inertial reference system (IRS).

[0036] : Radial velocity of the aircraft relative to the receiver.

[0037] The angle between the velocity vector and the communication link axis. Vector calculation based on the flight trajectory and the receiver's geographical coordinates. Calculate.

[0038] Sensitivity factor. This is the sensitivity scaling factor for the Doppler shift relative to the effective bandwidth of the application layer. It applies to different aerospace radio frequency bands. Value Recommendation Table: Unlike the conventional "antenna wavefront function", this formula uses cosine projection to introduce the "fuselage shielding effect". This constitutes a spatial directivity loss model. In high-dynamic airborne environments, aircraft fuselages are mostly metal shields. When drastic changes in flight attitude angles (roll or pitch) combined with external electronic interference cause the fuselage to fall between the antenna and the line-of-sight (LoS) path of the receiver, the signal will experience a "cliff-like" drop. By using the geometric projection of a cosine function, this model can predict the physical trend of bandwidth quota approaching zero within milliseconds when the attitude angle approaches 90°, thus providing a priori defensive commands.

[0039] The advantage of first-order linear simplification lies in avoiding complex logarithmic operations and establishing a linear prediction envelope using pure geometric projection. This approach does not depend on the antenna experimental coefficients of a specific aircraft model, has extremely high engineering versatility, and can meet the millisecond-level response requirements of avionics systems.

[0040] This term reflects the subcarrier orthogonality disruption caused by high-speed motion. The increased redundancy overhead is approximately linearly positively correlated with the frequency offset in engineering practice. The faster the speed, the greater the overhead for physical layer error correction and redundancy. This term directly and linearly reduces the available quota at the application layer, avoiding the need to perform complex logarithmic operations on the onboard mission computer.

[0041] when When the calculated result is lower than the actual link capacity, the system exhibits "defensive compression," ensuring a safety margin; when the calculated result is higher than the actual capacity, the underlying signal-to-noise ratio feedback mechanism still serves as a second layer of protection. This invention utilizes geometric situational awareness to provide a priori predictive instructions before link collapse.

[0042] Step S3: Dynamically adjust the bandwidth allocation weight of each spatial importance slice layer according to the ratio between the secure transmission quota and the preset threshold.

[0043] In aerospace wireless communication engineering, to ensure real-time performance in highly dynamic environments, approximately 30% of the bandwidth is typically reserved as a fading margin to address multipath effects and sudden interference. Therefore, the first preset threshold is selected as follows: When predicting quotas Break At this point, the link has entered a "non-ideal operating condition." If no measures are taken at this time, the application layer will perceive millisecond-level latency jitter due to the activation of the wireless link layer retransmission mechanism, resulting in display stuttering. Therefore, triggering "background space thinning" at this threshold, by sacrificing the bandwidth of non-critical L3 layers such as electronic maps and terrain textures, ensures that core L1 layer vector data receives absolute priority before perceived latency occurs.

[0044] In a typical airborne multifunction display (MFD) data stream, L1 layer command vector data such as altitude, attitude, and alarm characters typically occupy only 5% to 15% of the rated bandwidth. Below At this point, the remaining bandwidth is insufficient to support any continuous sensor video stream (L2 layer). The system then enters "vector-based mode," concentrating all bandwidth resources on the L1 layer and performing multi-path redundant transmission. Setting the bitrate to 0.3 is to utilize a "bandwidth for reliability" strategy in extremely low signal-to-noise ratio environments, ensuring that the pilot can still see the most critical navigation commands in real time even when the aircraft is in extreme attitudes such as a 90° roll causing obstruction, through extremely high coding redundancy such as 1 / 3 bitrate or repeated transmission. Therefore, the second preset threshold is selected... .

[0045] Therefore, when At the time: Maintain full HD transmission.

[0046] when At this time, the system automatically performs "background space thinning". It keeps the L1 layer intact, reduces the refresh rate of the L2 layer, and performs spatial downsampling on the L3 layer, transmitting only the central area or low-resolution textures to ensure that critical instruments do not stutter.

[0047] when At this time: Enter "Vector Consistency Mode". Completely truncate L3 layer transmission, transform L2 layer into low-capacity feature points, and utilize all freed bandwidth to perform multi-path redundant transmission of L1 level vector data. The secure transmission quota is a priori service access envelope. When the calculated value approaches 0, the system does not consider the bandwidth to have disappeared, but rather triggers "over-quota protection" logic, actively compressing the quota of non-critical data to zero, thereby allocating all remaining physical layer resources to L1 level data for multi-path redundant transmission.

[0048] Step S4: Encode the airborne display data according to the adjusted bandwidth allocation weights and perform wireless transmission.

[0049] Taking the example of an aircraft performing intense tactical maneuvers, in actual flight missions, when an aircraft performs intense tactical maneuvers such as rapid evasion or sharp turns, the wireless communication link faces the most severe physical challenges. This embodiment demonstrates how the system ensures the absolute real-time performance of core data through "defensive prediction" through the following specific process: Assuming the aircraft is currently in a steep roll turn, the roll angle of the fuselage relative to the horizontal plane is... Increased sharply to Pitch angle for At this point, the metal fuselage, tilted at a large angle, significantly shields the line-of-sight path between the communication antenna and the receiver. Simultaneously, the aircraft is approaching the receiver radially at a high subsonic speed; its Doppler shift correction factor is calculated to be... Set the rated maximum net throughput of the wireless communication hardware. for .

[0050] Traditional feedback typically lags by hundreds of milliseconds, making it unable to handle link collapses caused by such instantaneous maneuvers. This system's quota prediction module no longer waits for underlying signal-to-noise ratio feedback, but immediately substitutes it into the geometric model for prior calculations. After receiving the predicted quota, the weight adjustment module quickly compares it with the preset threshold: Calculate the ratio: The value has fallen below the second preset threshold. .

[0051] The system detected that the current link had entered an "extremely severe operating condition." If it continued to attempt to transmit the full amount of data, the application layer would experience severe perceived latency and screen tearing. Therefore, the system immediately forced its way into "vector maintenance mode."

[0052] exist Within the limited bandwidth, the system executes the following non-uniform orchestration strategy: Completely stop the transmission of third priority layers such as terrain textures and background maps, and truncate the continuous frame transmission of second priority layers such as infrared sensor video streams, converting them into feature points with extremely low refresh rates.

[0053] All freed-up bandwidth resources will be allocated to the first priority layer, namely the instruction vector layer.

[0054] Taking advantage of the extremely small amount of L1 layer data, such as altitude, heading, attitude lines, and alarm characters, in Multipath redundancy transmission and high-intensity forward error correction (FEC) coding are performed within the space.

[0055] Through the above dynamic adjustments, even when the fuselage is severely obstructed and the total bandwidth drops to the original quota, the system can still achieve its intended performance. Under the following extreme conditions, the core navigation parameters and alarm information displayed on the HUD (Head-Up Display) or multifunction display in the pilot's eyes remain absolutely smooth and without lag. This invention successfully uses "geometric spatial situation" to predict "physical link trends" and completes the replacement of business logic within milliseconds before a substantial collapse in link quality, greatly improving flight safety in extreme dynamic environments.

[0056] The present invention can also be an apparatus, method, and / or computer program product. A computer program product may include a readable storage medium having computer-readable program instructions loaded thereon for causing a processor to implement various aspects of the present invention.

[0057] Storage media can be tangible devices that hold and store instructions for use by instruction execution devices. Storage media can include, for example, electrical storage devices, magnetic storage devices, optical storage devices, electromagnetic storage devices, semiconductor storage devices, or any suitable combination thereof. More specific examples (a non-exhaustive list) of readable storage media include: portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), static random access memory (SRAM), portable compact disc read-only memory (CD-ROM), digital multifunction disc (DVD), memory sticks, floppy disks, mechanical encoding devices, such as punch cards or recessed protrusions storing instructions thereon, and any suitable combination thereof.

[0058] It should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This way of describing the specification is only for clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

[0059] The detailed descriptions listed above are merely specific descriptions of feasible embodiments of the present invention, and are not intended to limit the scope of protection of the present invention. All equivalent embodiments or modifications made without departing from the spirit of the present invention should be included within the scope of protection of the present invention.

Claims

1. A wireless data transmission method for airborne display devices, characterized in that, include: Step S1: Acquire airborne display data and divide the airborne display data into multiple spatial importance slice layers with different priorities according to the security relevance of the displayed content; Step S2: Obtain the real-time spatial attitude parameters of the aircraft through airborne inertial navigation data, and predict the application layer's schedulable safe transmission quota by combining the rated parameters of the wireless communication hardware. Step S3: Dynamically adjust the bandwidth allocation weight of each spatial importance slice layer according to the ratio between the secure transmission quota and the preset threshold; Step S4: Encode the airborne display data according to the adjusted bandwidth allocation weights and perform wireless transmission.

2. The wireless data transmission method for airborne display devices according to claim 1, characterized in that, In step S1, the airborne display data is divided into multiple spatial importance slice layers, specifically: The core vector data affecting flight safety is divided into the first priority layer; The sensor video stream data is divided into a second priority layer; Non-critical electronic maps and terrain texture data are classified as the third priority layer.

3. The wireless data transmission method for airborne display devices according to claim 1, characterized in that, In step S2, the secure transmission quota is predicted as follows: The roll and pitch angles of the aircraft are output in real time through the airborne inertial reference system, and the relative radial velocity of the aircraft relative to the receiver is obtained. The secure transmission quota is calculated based on the roll angle, pitch angle, relative radial velocity, and the rated maximum net throughput of the wireless communication hardware under an ideal line-of-sight link.

4. The wireless data transmission method for airborne display devices according to claim 3, characterized in that, The calculation process for the secure transmission quota is as follows: The rated maximum net throughput is multiplied by the cosine of the roll angle and the cosine of the pitch angle, respectively, to describe the directional loss and energy shift caused by the aircraft attitude. By further combining the ratio of relative radial velocity to electromagnetic wave propagation speed, a Doppler frequency shift correction factor is introduced for product operation to obtain the final safe transmission quota.

5. A wireless data transmission method for airborne display devices according to claim 2, characterized in that, In step S3, the bandwidth allocation weights of each spatially important slice layer are dynamically adjusted, specifically as follows: When the predicted secure transmission quota is lower than the first preset threshold and higher than the second preset threshold, the background space thinning logic is triggered to reduce the bandwidth allocation of the third priority layer in order to ensure the transmission bandwidth of the first and second priority layers. When the predicted secure transmission quota is lower than the second preset threshold, the system enters vector maintenance mode, stops transmission in the second and third priority layers, and concentrates all bandwidth resources in the first priority layer.

6. A wireless data transmission method for airborne display devices according to claim 5, characterized in that, The first preset threshold is 0.7 times the rated maximum net throughput, and the second preset threshold is 0.3 times the rated maximum net throughput.

7. A wireless data transmission system for airborne display devices, characterized in that, The wireless data transmission method for an airborne display device according to any one of claims 1 to 6 includes: The slicing module acquires airborne display data and divides the airborne display data into multiple spatial importance slice layers with different priorities based on the security relevance of the displayed content. The quota prediction module obtains the real-time spatial attitude parameters of the aircraft through airborne inertial navigation data and predicts the application layer's schedulable safe transmission quota by combining the rated parameters of the wireless communication hardware. The weighting adjustment module dynamically adjusts the bandwidth allocation weight of each spatial importance slice layer according to the ratio between the secure transmission quota and the preset threshold. The data transmission module encodes the airborne display data according to the adjusted bandwidth allocation weights and performs wireless transmission.

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