A terrain collision avoidance warning system and method based on aerial multi-source data

Abstract

This invention discloses a terrain collision avoidance warning system and method based on multi-source aviation data, relating to the field of aviation early warning. The invention aims to collect information from multiple data sources on the aircraft in real time and combine this information with the aircraft's own aerodynamic performance to calculate the warning envelope, providing timely collision avoidance suggestions. This helps pilots avoid collisions with the ground or obstacles in complex terrain, low-altitude flight, or low-visibility conditions, improving flight safety. It also meets the terrain collision avoidance function requirements of aircraft with different performance characteristics at different flight phases, improving the accuracy and timeliness of terrain collision avoidance warnings.

Description

Technical Field

[0001] This invention relates to the field of aviation early warning, and specifically to a terrain collision avoidance warning system and method based on multi-source aviation data. Background Technology

[0002] The statements in this section are provided only as background information in connection with this disclosure and may not constitute prior art.

[0003] With the continuous development of aviation technology, flight safety has become an increasingly important concern. In complex terrain, low-altitude flight, or low-visibility conditions, pilots struggle to visually identify ground obstacles, increasing the risk of collisions between the aircraft and the ground or obstacles. To improve flight safety, terrain collision avoidance and warning systems have emerged, representing an effective means of preventing controlled ground collisions in aircraft today.

[0004] Currently, many aircraft both domestically and internationally are equipped with terrain collision avoidance and warning systems to reduce flight risks. Traditional terrain collision avoidance and warning systems mainly rely on single data sources such as airborne radar and satellite navigation for terrain warnings. While these systems have improved flight safety to some extent, they still have the following problems:

[0005] Single data source: Traditional terrain collision avoidance and alarm systems mainly rely on radar or satellite navigation data. The single data source is easily affected by external factors such as weather and terrain, resulting in low accuracy and timeliness of alarms.

[0006] Limitations of early warning strategies: Existing terrain collision avoidance systems mainly rely on fixed thresholds for early warning, which cannot be adjusted in real time according to the aircraft's own aerodynamic performance, resulting in certain errors in the early warning results.

[0007] High level of pilot intervention: In complex terrain, low-altitude flight, or low-visibility conditions, pilots need to pay close attention to warnings issued by the terrain collision avoidance and warning system and perform manual evasive maneuvers. This increases the pilot's workload to some extent and may lead to delayed responses.

[0008] Poor system compatibility: Terrain collision avoidance and warning systems on different aircraft may have compatibility issues, which is not conducive to data sharing and system integration.

[0009] To address the above issues, it is necessary to research a terrain collision avoidance warning method based on multi-source aviation data to improve the accuracy and timeliness of terrain collision avoidance systems, reduce pilot workload, and enhance flight safety. Summary of the Invention

[0010] The purpose of this invention is to address the problems existing in the prior art by providing a terrain collision avoidance warning system and method based on multi-source aviation data. This system meets the CTSO 151b standard and aims to collect information from multiple data sources on the aircraft in real time and combine this information with the aircraft's own aerodynamic performance to calculate the warning envelope. It then provides timely collision avoidance suggestions to help pilots avoid collisions with the ground or obstacles in complex terrain, low-altitude flight, or low-visibility conditions, thereby improving flight safety. This meets the terrain collision avoidance function requirements of aircraft with different performance characteristics at different flight phases, and improves the accuracy and timeliness of terrain collision avoidance warnings.

[0011] The technical solution of the present invention is as follows:

[0012] A terrain collision avoidance warning system based on multi-source aerial data includes:

[0013] Aircraft multi-source data acquisition and preprocessing module: receives various data from the airborne system in real time, and performs validity determination and preprocessing on the received data;

[0014] Aircraft performance impact judgment module: Receives various aircraft performance parameters sent from the aircraft multi-source data acquisition and preprocessing module, calculates the impact factor of each aircraft performance parameter on the terrain collision avoidance alarm envelope, and sends it to the alarm envelope threshold calculation module;

[0015] Flight Phase Determination Module: Receives data sent from the aircraft's multi-source data acquisition and preprocessing module, calculates the current flight phase of the aircraft, and sends it to the alarm envelope threshold calculation module;

[0016] Alarm envelope threshold calculation module: Receives data sent by the aircraft performance impact judgment module, the aircraft multi-source data acquisition and preprocessing module, and the flight phase judgment module, calculates the current aircraft terrain collision avoidance alarm envelope threshold, and sends it to the alarm judgment and output module;

[0017] Alarm determination and output module: Based on the received terrain collision avoidance alarm envelope threshold, combined with the current flight status and environmental information of the aircraft, determine whether the current aircraft has triggered a terrain collision avoidance alarm.

[0018] Furthermore, the data of the airborne system include:

[0019] Terrain database, obstacle database, navigation database, navigation data, inertial navigation atmospheric data, landing gear status data, flap status data and other avionics equipment data, as well as aircraft performance parameters.

[0020] Furthermore, it also includes:

[0021] After the alarm judgment and output module judges the alarm, it outputs the alarm information to the display and control terminal.

[0022] A terrain collision avoidance warning method based on aerial multi-source data, and a terrain collision avoidance warning system based on aerial multi-source data, comprising:

[0023] Terrain collision avoidance warnings are achieved by using warning envelope calculation mechanisms based on different aircraft performance and different flight phases.

[0024] Furthermore, the alarm envelope calculation mechanism for different aircraft performance includes:

[0025] The aircraft performance impact assessment module obtains aircraft performance parameters in real time from the aviation multi-source data acquisition and preprocessing module, and calculates the impact factors of this type of aircraft through model calculation.

[0026] The influencing factors are sent to the alarm envelope threshold calculation module through the data distribution interface to calculate the alarm envelope that meets the current aircraft performance.

[0027] Furthermore, the aircraft performance parameters include:

[0028] Aircraft payload capacity, maximum flight speed, minimum safe altitude, climb performance, and aircraft configuration information.

[0029] Furthermore, the influencing factors include:

[0030] The focus of the collision avoidance function, as well as the detection range, response time, reserved safe altitude, and aircraft pull-up loss altitude of the warning envelope.

[0031] Furthermore, the alarm envelope calculation mechanism for different flight phases includes:

[0032] The flight phase determination module calculates the current flight phase based on the received aircraft's current position, airspeed, altitude, and reference point position. Then, based on the characteristics of different flight phases and changes in the flight environment, it increases the reserved safe altitude of the warning envelope during the aircraft's takeoff and approach / landing phases; and expands the detection range of the warning envelope during the aircraft's cruise and high-speed flight phases, thereby achieving dynamic adjustment of the terrain collision avoidance envelope threshold.

[0033] Compared with existing technologies, the advantages of this invention are:

[0034] 1. Good compatibility. This invention studies the impact of performance parameters of different aircraft models, such as aircraft load capacity, maximum speed, and maximum climb rate, on the terrain collision avoidance envelope. It achieves adaptive adjustment of the warning envelope and threshold for different aircraft models, effectively improving the compatibility of the algorithm.

[0035] 2. Low false alarm rate. This invention automatically adjusts the alarm logic based on the aircraft's current flight phase (such as takeoff, cruise, landing, etc.) and changes in the flight environment. It can accurately adapt to the unique flight risks of different flight phases, reduce the false alarm rate, and ensure that important alarms are not missed.

[0036] 3. Strong multi-source data fusion capability. This invention integrates diverse data sources from different systems, devices, and sensors. Through comprehensive analysis and correlation mining, it discovers the impact of factors such as aircraft performance and flight phase on alarm thresholds, improving the comprehensiveness and accuracy of alarms. Attached Figure Description

[0037] Figure 1 This is a block diagram of a terrain collision avoidance warning system based on multi-source aerial data;

[0038] Figure 2 A schematic diagram illustrating the calculation of alarm envelopes for different aircraft performance characteristics;

[0039] Figure 3 A schematic diagram illustrating the calculation of alarm envelopes for different flight phases. Detailed Implementation

[0040] It should be noted that relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0041] The features and performance of the present invention will be further described in detail below with reference to embodiments.

[0042] Example 1

[0043] Please see Figure 1 A terrain collision avoidance warning system based on multi-source aerial data, specifically including the following modules:

[0044] Aircraft multi-source data acquisition and preprocessing module: Receives various data from airborne systems in real time, including terrain database, obstacle database, navigation database, navigation data, inertial navigation atmospheric data, landing gear status data, flap status data and other avionics equipment data, as well as aircraft performance parameters, and performs validity determination and preprocessing on the received data;

[0045] Aircraft performance impact judgment module: Receives various aircraft performance parameters sent from the aircraft multi-source data acquisition and preprocessing module, calculates the impact factor of each aircraft performance parameter on the terrain collision avoidance alarm envelope, and sends it to the alarm envelope threshold calculation module;

[0046] Flight Phase Determination Module: Receives data sent from the aircraft's multi-source data acquisition and preprocessing module, calculates the current flight phase of the aircraft, and sends it to the alarm envelope threshold calculation module;

[0047] Alarm envelope threshold calculation module: Receives data sent by the aircraft performance impact judgment module, the aircraft multi-source data acquisition and preprocessing module, and the flight phase judgment module, calculates the current aircraft terrain collision avoidance alarm envelope threshold, and sends it to the alarm judgment and output module;

[0048] Alarm determination and output module: Based on the received terrain collision avoidance alarm envelope threshold, combined with the current flight status and environmental information of the aircraft, determine whether the current aircraft has triggered a terrain collision avoidance alarm, and output the alarm information to the display and control terminal.

[0049] This embodiment also proposes a terrain collision avoidance warning method based on aerial multi-source data. Based on the aforementioned terrain collision avoidance warning system based on aerial multi-source data, it includes:

[0050] Terrain collision avoidance warnings are achieved by using warning envelope calculation mechanisms based on different aircraft performance and different flight phases.

[0051] 1. Alarm envelope calculation mechanism based on different aircraft performance

[0052] Different aircraft maneuverability has varying impacts on parameters such as detection range, response time, latency, and detection distance of terrain collision avoidance warning systems. This embodiment achieves rapid iteration of the warning envelope by calculating the relationship between aircraft performance and the warning envelope.

[0053] For details, please refer to Figure 2 The alarm envelope calculation mechanism for different aircraft performance includes:

[0054] The aircraft performance impact assessment module obtains aircraft performance parameters such as payload capacity, maximum flight speed, minimum safe altitude, climb performance, and aircraft configuration information in real time from the multi-source aviation data acquisition and preprocessing module, and calculates the impact factors of this type of aircraft through model calculation.

[0055] The data distribution interface sends the focus of the collision avoidance function, as well as influencing factors such as the detection range, response time, reserved safe altitude, and aircraft pull-up loss altitude of the alarm envelope, to the alarm envelope threshold calculation module to calculate the alarm envelope that meets the current aircraft performance.

[0056] Specifically, the calculation process is as follows:

[0057] The aircraft performance impact assessment module acquires aircraft performance parameters in real time from the multi-source aviation data acquisition and preprocessing module, such as aircraft payload capacity (W), maximum flight speed (Vmax), climb performance (ROC), descent performance (S), turn performance (T), and aircraft configuration information (Cfg). Through model calculations, it obtains the following impact factors: detection range impact factor, detection width impact factor, aircraft pull-up loss impact factor, and reserved safe altitude impact factor.

[0058] (δ range δ width δ hdn δ hｌoss )=f(W,V max H dn (ROC, S, T, Cfg)

[0059] Subsequently, the influencing factors are sent to the alarm envelope threshold calculation module via the data distribution interface to calculate the alarm envelope that meets the current aircraft performance requirements. The alarm envelope is a three-dimensional spatial region, and its parameters include detection range, detection width, and detection depth. The specific calculation method is shown below, where H... loss For aircraft takeoff losses, H dn To allow for a safe altitude, V is the aircraft speed, t is the pull-up time, θ is the aircraft pitch angle, ω is the pull-up angular velocity, and V decent For the rate of descent, k and b are both constants:

[0060]

[0061] H dn =δ hdn ·(k dn ·V+b dn )

[0062] Range = δ range ·(k r ·V+br )

[0063] Width=δ width ·(k w ·V+b w )

[0064]

[0065] 2. Alarm envelope calculation mechanism for different flight phases

[0066] As an aircraft enters different flight phases, factors such as its relative altitude to the ground, speed, and external environment vary significantly, leading to different requirements for the detection range, response time, and alarm accuracy of the terrain collision avoidance warning system. This mechanism calculates the aircraft's current flight phase and dynamically adjusts the alarm envelope threshold to reduce unnecessary alarm interference.

[0067] Specifically, such as Figure 3 As shown, the alarm envelope calculation mechanism for different flight phases includes:

[0068] The flight phase determination module calculates the current flight phase based on the received aircraft's current position, airspeed, altitude, and reference point position. Then, based on the characteristics of different flight phases and changes in the flight environment, it increases the reserved safe altitude of the warning envelope during the aircraft's takeoff and approach / landing phases; and expands the detection range of the warning envelope during the aircraft's cruise and high-speed flight phases, thereby achieving dynamic adjustment of the terrain collision avoidance envelope threshold.

[0069] Specifically, the calculation process is as follows:

[0070] The flight phase determination module calculates the current flight phase based on the received data such as the aircraft's current position (Loc), airspeed (V), altitude (H), and reference point position (Locref). The flight phase includes takeoff, climb, cruise, approach, landing, and go-around phases.

[0071] phase = y(Loc, V, H, Loc) ref )

[0072] The data distribution interface sends the flight phase to the alarm envelope threshold calculation module, which calculates the alarm envelope that meets the current flight phase. The specific calculation method is shown in the following formula, where R p W p D p These represent the impact values ​​of different flight phases on detection range, detection width, and detection depth, respectively.

[0073] Range = δ range ·(k r·V+b r )+R p

[0074] Width=δ width ·(k w ·V+b w )+W p

[0075]

[0076] As shown in the formula above, the detection depth of the warning envelope is increased during the aircraft takeoff and approach / landing phases; the detection range of the warning envelope is expanded during the aircraft cruise phase, thereby achieving dynamic adjustment of the terrain collision avoidance envelope threshold.

[0077] It should be noted that the calculation process mentioned above can be implemented by those skilled in the art based on the acquired data and target data, and will not be elaborated further here.

[0078] The embodiments described above merely illustrate specific implementation methods of this application, and while the descriptions are detailed and specific, they should not be construed as limiting the scope of protection of this application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the technical solution of this application, and these modifications and improvements all fall within the scope of protection of this application.

[0079] This background section is provided to generally present the context of the invention. The work of the currently named inventors, the work to the extent described in this background section, and aspects of this section that did not constitute prior art at the time of application are neither expressly nor impliedly acknowledged as prior art to the invention.

Claims

1. A terrain collision avoidance warning system based on multi-source aerial data, characterized in that, include: Aircraft multi-source data acquisition and preprocessing module: receives various data from the airborne system in real time, and performs validity determination and preprocessing on the received data; Aircraft performance impact judgment module: Receives various aircraft performance parameters sent from the aircraft multi-source data acquisition and preprocessing module, calculates the impact factor of each aircraft performance parameter on the terrain collision avoidance alarm envelope, and sends it to the alarm envelope threshold calculation module; Flight Phase Determination Module: Receives data sent from the aircraft's multi-source data acquisition and preprocessing module, calculates the current flight phase of the aircraft, and sends it to the alarm envelope threshold calculation module; Alarm envelope threshold calculation module: Receives data sent by the aircraft performance impact judgment module, the aircraft multi-source data acquisition and preprocessing module, and the flight phase judgment module, calculates the current aircraft terrain collision avoidance alarm envelope threshold, and sends it to the alarm judgment and output module; Alarm determination and output module: Based on the received terrain collision avoidance alarm envelope threshold, combined with the current flight status and environmental information of the aircraft, determine whether the current aircraft has triggered a terrain collision avoidance alarm.

2. The terrain collision avoidance warning system based on multi-source aerial data according to claim 1, characterized in that, The data of the airborne system include: Terrain database, obstacle database, navigation database, navigation data, inertial navigation atmospheric data, landing gear status data, flap status data, avionics data, and aircraft performance parameters.

3. The terrain collision avoidance warning system based on multi-source aerial data according to claim 1, characterized in that, Also includes: After the alarm judgment and output module judges the alarm, it outputs the alarm information to the display and control terminal.

4. A terrain collision avoidance warning method based on multi-source aerial data, characterized in that, A terrain collision avoidance warning system based on aerial multi-source data according to any one of claims 1-3 includes: Terrain collision avoidance warnings are achieved by using warning envelope calculation mechanisms based on different aircraft performance and different flight phases.

5. A terrain collision avoidance warning method based on aerial multi-source data according to claim 4, characterized in that, The alarm envelope calculation mechanism for different aircraft performance includes: The aircraft performance impact assessment module obtains aircraft performance parameters in real time from the aviation multi-source data acquisition and preprocessing module, and calculates the impact factors of this type of aircraft through model calculation. The influencing factors are sent to the alarm envelope threshold calculation module through the data distribution interface to calculate the alarm envelope that meets the current aircraft performance.

6. A terrain collision avoidance warning method based on aerial multi-source data according to claim 5, characterized in that, The aircraft performance parameters include: Aircraft payload capacity, maximum flight speed, minimum safe altitude, climb performance, and aircraft configuration information.

7. A terrain collision avoidance warning method based on aerial multi-source data according to claim 5, characterized in that, The impact factors include: The focus of the collision avoidance function, as well as the detection range, response time, reserved safe altitude, and aircraft pull-up loss altitude of the warning envelope.

8. A terrain collision avoidance warning method based on aerial multi-source data according to claim 4, characterized in that, The alarm envelope calculation mechanism for different flight phases includes: The flight phase determination module calculates the current flight phase based on the received aircraft's current position, airspeed, altitude, and reference point position. Then, based on the characteristics of different flight phases and changes in the flight environment, it increases the reserved safe altitude of the warning envelope during the aircraft's takeoff and approach / landing phases; and expands the detection range of the warning envelope during the aircraft's cruise and high-speed flight phases, thereby achieving dynamic adjustment of the terrain collision avoidance envelope threshold.

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