A system and method for taws mode 2 flight testing

Abstract

The present application relates to a kind of system and method for TAWS mode 2 flight test.The present application proposes a kind of flight test technical scheme based on the flight test implementation process with virtual airport as core.The technical scheme is a kind of flight test of TAWS mode 2, which is carried out by the method of familiar simulation approach flight of pilot, can efficiently complete flight test task on the basis of effectively controlling the risk of aircraft controlled ground impact, can support the implementation of TAWS low height flight test in complex mountain area for civil aircraft airborne product.

Description

Technical Field

[0001] This invention relates to the field of civil aircraft testing and verification technology, specifically to a system and method for flight testing of Terrain Warning and Alert System (TAWS) Mode 2. Background Technology

[0002] In traditional civil aviation, the minimum safe flight altitude is no less than 600 meters above the highest obstacle in the area during the cruise phase and 300 meters above the highest obstacle in the terminal area. However, during the TAWS Mode 2 flight test, the aircraft was below the minimum safe altitude, posing a significant risk of crashing into a mountain. Secondly, the flight test required precise control of the aircraft's flight path to accurately trigger warnings at specific locations on the mountain peaks. Furthermore, low-altitude flights in mountainous areas are highly susceptible to turbulence, birds, human structures, and unmanned aerial vehicles, posing a significant threat to flight safety. Therefore, sophisticated monitoring and control of these threats are essential.

[0003] Therefore, conducting TAWS Mode 2 flight tests requires a scientifically sound and precise technical solution for controlling flight altitude and trajectory, as well as monitoring and controlling environmental factors, to improve the success rate of flight tests while ensuring safety. Currently, the focus is mainly on the product design of terrain warning and alert systems, designing some functions such as alarm image generation, alarm information generation or management, and forward-looking terrain warning based on aircraft performance. There is currently a lack of technical solutions for flight test methods for terrain warning and alert systems. There are gaps in the implementation methods and safety controls for flight tests. Furthermore, traditional TAWS Mode 2 flight tests involve the test pilot maneuvering the aircraft towards a target mountain peak, resulting in insufficient trajectory control precision and a high risk of deviation from the test route, potentially leading to flight test failure. Secondly, altitude control is based on barometric pressure measurements from airports far from mountainous areas; large deviations in barometric pressure at low altitudes in mountainous areas can lead to controlled impacts. Finally, traditional communication and monitoring methods for low-altitude mountain flights cannot maintain real-time contact with the aircraft, hindering timely flight control. The test relies entirely on the test pilot's autonomous control, resulting in significant uncertainty regarding test efficiency and flight safety.

[0004] Therefore, there is an urgent need for a system and method to improve existing technologies. Summary of the Invention

[0005] This summary is provided to introduce, in a simplified form, some concepts that will be further described in the following detailed description section. This summary is not intended to identify key or essential features of the claimed subject matter, nor is it intended to help determine the scope of the claimed subject matter.

[0006] To address the problems in existing technologies, a flight test technology solution based on a virtual flight test implementation process is proposed. This solution utilizes a simulated approach flight method familiar to pilots to conduct TAWS Mode 2 flight tests. While effectively controlling the risk of controlled ground collision, it can efficiently complete flight test missions and support the implementation of TAWS for civil aircraft in low-altitude test flights in complex mountainous areas.

[0007] Specifically, the technical solution of the present invention supports the implementation of TAWS Mode 2 flight tests in mountainous areas by constructing a virtual field architecture and designing a simulated approach, landing and go-around system and test flight implementation process that integrates runway, flight path, air pressure reference, radio altitude, and flight procedures including approach, landing and go-around.

[0008] Specifically, in one embodiment of the present invention, a system for TAWS Mode 2 flight testing is disclosed, the system comprising:

[0009] The flight planning module is configured as follows:

[0010] A virtual runway is constructed, with the highest point of the test target mountain as the entrance centerline point of the virtual runway and the altitude of the test target mountain as the landing elevation of the virtual runway.

[0011] A virtual flight path is constructed based on this virtual runway. The flight altitude of each segment of the virtual flight path is constrained by the landing elevation of the runway. This virtual flight path includes the following elements: approach, landing, and go-around; and

[0012] Based on the virtual flight path, an approach, landing, and go-around procedure is generated for the flight crew to execute;

[0013] The barometric pressure measurement module is configured to measure the field pressure of the virtual runway and calculate the corrected sea pressure in real time based on the altitude to provide barometric pressure reference data.

[0014] The meteorological observation module is configured to provide the meteorological information required for the flight test, including wind speed and direction at the entrance section of the virtual runway, visibility, and cloud base height; and

[0015] The VHF communication module is configured for air-to-ground communication, including sending the barometric reference data and the meteorological information to the aircraft.

[0016] In one embodiment of the present invention, the system further includes:

[0017] The airspace condition observation module is configured to observe the airspace condition and report the airspace condition to the crew via the VHF communication module. The airspace condition includes bird activity and drone activity.

[0018] Satellite communication module, configured for backup air-to-ground communication; and

[0019] The simulated control tower module is configured to operate the flight test operation control system.

[0020] In one embodiment of the present invention, the runway direction of the virtual runway is consistent with the design heading of the virtual flight path.

[0021] In one embodiment of the present invention, the corrected sea pressure is calculated by the following formula: p0 = p[288.15 / (288.15-0.00065H)] 5.256 Where P0 is the corrected sea level pressure, P is the measured surface pressure, and H is the altitude of the target mountain in the experiment.

[0022] In one embodiment of the invention, the flight planning module is further configured to generate aeronautical charts based on the approach, landing, and go-around procedure for use by the flight crew.

[0023] In one embodiment of the invention, the go-around altitude in the virtual flight path is adjusted based on the aircraft's minimum radio altitude when it flies over the entrance of the virtual runway.

[0024] In one embodiment of the present invention, the meteorological observation module includes an anemometer, a wind cone, and a visibility observation reference device, and the meteorological information is provided in conjunction with satellite cloud images.

[0025] In another embodiment of the present invention, a method for TAWS Mode 2 flight testing is disclosed, the method comprising:

[0026] A virtual runway is constructed, with the highest point of the test target mountain as the entrance centerline point of the virtual runway and the altitude of the test target mountain as the landing elevation of the virtual runway.

[0027] A virtual flight path is constructed based on the virtual runway. The flight altitude of each segment of the virtual flight path is constrained by the landing elevation of the runway. The virtual flight path includes the following elements: approach, approach, landing, and go-around.

[0028] Based on the virtual flight path, an approach, landing, and go-around procedure is generated for the flight crew to execute;

[0029] The field pressure of the virtual runway is measured and the corrected sea surface pressure is calculated in real time based on the altitude to provide atmospheric pressure reference data;

[0030] Provide the meteorological information required for this flight test, including wind speed and direction at the entrance section of the virtual runway, visibility, and cloud base height; and

[0031] The air pressure reference data and the meteorological information are sent to the aircraft.

[0032] In one embodiment of the invention, the method further includes observing airspace conditions and reporting the airspace conditions to the crew, the airspace conditions including bird activity and drone activity.

[0033] In one embodiment of the invention, the method further includes creating a flight chart based on the approach, landing, and go-around procedure for use by the flight crew.

[0034] Other aspects, features, and embodiments of the invention will become apparent to those skilled in the art after reading the following description of specific exemplary embodiments of the invention in conjunction with the accompanying drawings. Although features of the invention may be discussed below with reference to certain embodiments and drawings, all embodiments of the invention may include one or more of the advantageous features discussed herein. In other words, while one or more embodiments may be discussed having certain advantageous features, one or more of such features may also be used according to the various embodiments of the invention discussed herein. Similarly, although exemplary embodiments may be discussed below as embodiments of devices, systems, or methods, it should be understood that such exemplary embodiments can be implemented in various devices, systems, and methods. Attached Figure Description

[0035] To gain a more detailed understanding of the features described above in this disclosure, reference can be made to a more specific description of the above-briefly summarized aspects, some of which are illustrated in the accompanying drawings. However, it should be noted that the drawings illustrate only certain typical aspects of this disclosure and should not be considered as limiting its scope, as other equivalent aspects are permissible in this description.

[0036] Figure 1 A schematic block diagram of a system for TAWS Mode 2 flight testing according to an embodiment of the present invention is shown.

[0037] Figure 2 A schematic diagram of a virtual machine farm structure according to an embodiment of the present disclosure is shown.

[0038] Figure 3 A design diagram of an approach, landing, and go-around procedure according to an embodiment of the present disclosure is shown.

[0039] Figure 4 A flowchart illustrating a method for TAWS Mode 2 flight testing according to an embodiment of the present invention is shown.

[0040] Figure 5 The flight test implementation process based on a method and system according to an embodiment of the present invention is illustrated. Detailed Implementation

[0041] The various embodiments will now be described in more detail with reference to the accompanying drawings, which form part of this invention and illustrate specific exemplary embodiments. However, the embodiments may be implemented in many different forms and should not be construed as limiting the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of these embodiments to those skilled in the art. The embodiments may be implemented as methods, systems, or devices. Therefore, these embodiments may be implemented in hardware, entirely in software, or in a combination of software and hardware aspects. Therefore, the following detailed description is not intended to be limiting.

[0042] The steps in each flowchart can be performed by hardware (e.g., processor, engine, memory, circuitry), software (e.g., operating system, application, driver, machine / processor executable instructions), or a combination thereof. As will be understood by those skilled in the art, the methods involved in each embodiment may include more or fewer steps than shown.

[0043] To address the technical problems in existing technologies, this invention constructs a virtual field structure with the target test mountain peak as the runway entrance. This structure provides support services such as a virtual runway, communication command, barometric pressure reference, and meteorological services for flight testing. It effectively solves problems such as inaccurate barometric pressure references and incomplete communication monitoring signal coverage, providing a comprehensive support environment for flight testing. Furthermore, for TAWS Mode 2 flight testing, this invention designs a flight procedure covering the expected test mountain in mountainous areas, using the target mountain peak as the runway entrance. This allows for flight testing in a simulated approach and go-around manner familiar to pilots, precisely controlling the aircraft's trajectory and altitude, and improving flight test efficiency while ensuring flight safety.

[0044] The various aspects of the present invention will now be described in detail.

[0045] Figure 1 A schematic block diagram of a system 100 for TAWS Mode 2 flight testing according to an embodiment of the present invention is shown. The following will be combined with... Figure 2 and Figure 3 To describe in detail Figure 1 The system 100 shown.

[0046] In one embodiment of the present invention, the system 100 for TAWS Mode 2 flight test may include a flight planning module 102, a barometric pressure measurement module 104, a meteorological observation module 106, and a VHF communication module 108.

[0047] Figure 2 A schematic diagram of a virtual machine farm structure 200 according to an embodiment of the present disclosure is shown. Figure 2As shown, by constructing this virtual field architecture and designing flight procedures including runways, flight paths, barometric references, radio altitudes, approach, landing, and go-around, it supports the conduct of TAWS Mode 2 flight tests in mountainous areas.

[0048] Specifically, in one embodiment of the present invention, the flight planning module 102 can be configured to construct a virtual runway. In this embodiment, the virtual runway uses the highest point of the test target mountain as the entrance centerline point of the virtual runway and the altitude of the test target mountain as the runway landing elevation of the virtual runway, and the runway direction of the virtual runway is consistent with the design heading of the virtual flight path.

[0049] In one exemplary embodiment, such as Figure 2 As shown, the virtual runway uses the highest point of the test target mountain as the runway port centerline point. The runway length can be 3000 meters, the width can be 60 meters, the runway magnetic heading can be 142°, and the runway port landing elevation can be H meters.

[0050] In one embodiment of the invention, the flight planning module 102 can also be configured to construct a virtual trajectory based on the virtual runway. In this embodiment, the flight altitude of each segment of the virtual trajectory is constrained by the runway landing elevation, and the virtual trajectory includes the following elements: approach, approach, landing, and go-around. In another embodiment of the invention, the go-around altitude in the virtual trajectory is adjusted based on the aircraft's minimum radio altitude when flying over the entrance of the virtual runway. The aircraft's radio altitude gradually decreases as it approaches the mountain, reaching a minimum value when flying over the mountaintop, and is used to adjust the go-around altitude during flight.

[0051] In one embodiment of the invention, the flight planning module 102 may be further configured to generate an approach, landing, and go-around procedure for the flight crew to execute based on the virtual flight path. In this embodiment, the flight planning module 102 may also be further configured to create aeronautical charts based on the approach, landing, and go-around procedure for use by the flight crew.

[0052] Figure 3 A design diagram 300 of an approach, landing, and go-around procedure according to an embodiment of the present disclosure is shown. In one exemplary embodiment, a procedure is designed based on actual flight test conditions. Figure 3The flight path shown includes two Initial Approach Fixes (IAF), one Intermediate Approach Fix (IF), one Final Approach Fix (FAF), and one Go-around Point (MAPt). The altitude of the IAF can be 3000 meters, the IAF can be 2600 meters, and the FAF can be H+200 meters H+600 meters (adjustable according to different test requirements). The distance from IAF to IF is 34 kilometers, the distance from IF to FAF is 25 kilometers, and the distance from FAF to MAPt is 25 kilometers. 2) Approach, Landing, and Go-around Procedures: Based on the flight path, design the approach, landing, and go-around procedures and create aeronautical charts for the flight crew. See details... Figure 3 The flight procedure constrains information such as the location of each waypoint, flight path altitude, and descent profile. The go-around procedure involves a straight climb to 3000 meters, followed by a right turn towards BJ304.

[0053] As those skilled in the art will understand, the above-described virtual trajectory and approach-landing go-around procedure are merely exemplary and not restrictive. In other embodiments of the present invention, other suitable virtual trajectories may be constructed and any other suitable approach-landing go-around procedure may be generated based on such virtual trajectories.

[0054] Back Figure 1 In one embodiment of the invention, the air pressure measurement module 104 may be configured to measure the field pressure of the virtual runway and calculate the corrected sea level pressure in real time based on the altitude to provide air pressure reference data. In this embodiment, the corrected sea level pressure is calculated using the following formula: p0 = p[288.15 / (288.15-0.00065H)] 5.256 Where P0 is the corrected sea level pressure, P is the measured surface pressure, and H is the altitude of the target mountain in the test. During the aircraft's approach and landing, the pressure gauge is adjusted using the ground-provided pressure correction. The minimum radio altitude of the aircraft when flying over the virtual runway threshold is used to determine the minimum altitude of the aircraft to take off, thereby controlling the pressure altitude for the next simulated approach and go-around.

[0055] As those skilled in the art will understand, the above-described method for calculating the corrected sea level pressure is merely exemplary and not restrictive. Any other suitable calculation method may be used to calculate the corrected sea level pressure in other embodiments of the present invention.

[0056] In one embodiment of the present invention, the air pressure measurement module 104 may be implemented as an air pressure measurement device set on the mountaintop, for measuring the field pressure of the virtual runway in real time and calculating the corrected sea pressure in real time based on the altitude of the virtual runway.

[0057] In one embodiment of the invention, the meteorological observation module 106 may be configured to provide meteorological information required for the flight test, including wind speed and direction, visibility, and cloud base height at the entrance section of the virtual runway. In another embodiment of the invention, the meteorological observation module includes an anemometer, wind cone, and visibility observation reference equipment mounted on a mountaintop, and the meteorological information may be provided in conjunction with satellite cloud imagery.

[0058] In one embodiment of the invention, the VHF communication module 108 can be configured for air-to-ground communication, including transmitting the barometric reference data and meteorological information to the aircraft. In this embodiment, the VHF communication module 108 can be implemented as a VHF radio station built on a mountaintop and can also be used for civil aviation communication monitoring and flight test communication command.

[0059] In another embodiment of the invention, system 100 may optionally further include ( Figure 1 (Not shown in the image): Clearance condition observation module, which can be configured to observe clearance conditions and report the clearance conditions to the crew via the VHF communication module, the clearance conditions including bird activity and UAV activity; satellite communication module, which can be configured for backup air-to-ground communication; and simulated tower module, which can be configured to operate the test flight operation control system.

[0060] Figure 4 A flowchart of a method 400 for TAWS Mode 2 flight testing according to an embodiment of the present invention is shown.

[0061] Method 400 begins at step 402, constructing a virtual runway with the highest point of the test target mountain as the entrance centerline point of the virtual runway and the altitude of the test target mountain as the runway landing elevation.

[0062] Next, method 400 continues to step 404, constructing a virtual trajectory based on the virtual runway. The flight altitude of each segment of the virtual trajectory is constrained by the runway landing elevation. The virtual trajectory includes the following elements: approach, approach, landing, and go-around. In one embodiment of the invention, the runway orientation of the virtual runway is consistent with the design heading of the virtual trajectory. In one embodiment of the invention, the go-around altitude in the virtual trajectory is adjusted based on the aircraft's minimum radio altitude when flying over the entrance of the virtual runway.

[0063] Then, method 400 continues to step 406, generating an approach, landing, and go-around procedure for the crew to execute based on the virtual flight path. In one embodiment of the invention, method 400 further includes creating a flight chart based on the approach, landing, and go-around procedure for the crew's use.

[0064] Subsequently, method 400 continues to step 408, measuring the field pressure of the virtual runway and calculating the corrected sea level pressure in real time based on the altitude to provide atmospheric pressure reference data. In one embodiment of the invention, the corrected sea level pressure is calculated using the following formula: p0 = p[288.15 / (288.15-0.00065H)] 5.256 Where P0 is the corrected sea level pressure, P is the measured surface pressure, and H is the altitude of the target mountain in the experiment.

[0065] Next, method 400 continues to step 410, providing the meteorological information required for the flight test, including wind speed and direction, visibility, and cloud base height at the entrance section of the virtual runway. In one embodiment of the invention, the meteorological observation module includes an anemometer, a wind cone, and a visibility observation reference device, and the meteorological information is provided in conjunction with satellite cloud imagery.

[0066] Finally, method 400 continues to step 412, sending the barometric reference data and the meteorological information to the aircraft.

[0067] After step 412, method 400 ends.

[0068] Furthermore, by combining the aforementioned system 100 with method 400, this invention constructs an implementation process for TAWS Mode 2 flight testing, connecting a complete set of flight testing methods, covering the entire business process from test preparation, virtual field construction, aircraft takeoff, receiving meteorological information, setting flight plans according to virtual flight paths, strictly following flight paths to complete the test, and finally returning to the field and landing.

[0069] Specifically, Figure 5 A flight test implementation process 500 based on a method 400 and a system 100 according to an embodiment of the present invention is shown.

[0070] 1) The mountaintop control team is in position; 2) The control equipment and facilities are set up, including communication, navigation, surveillance, and meteorology systems (including System 100 and its various modules); 3) The aircraft is informed that it is ready to take off; 4) The aircraft takes off and enters the airspace; 5) The weather conditions are reported; 6) The aircraft completes the test flight plan settings (the virtual flight path generated by the flight plan module 102 in System 100) and barometric reference settings and flies according to the flight path; 7) The activity of birds and drones in the mountaintop area is reported; 8) The aircraft continues to fly along the flight path, and when the expected warning occurs, it flies over the target mountain peak (executes the approach, landing, and go-around procedure based on the generated virtual flight path); 9) The ground determines the validity of the test and informs the aircraft to continue to the next set of tests or to end the test; 10) The aircraft returns to the airfield and lands, and the control team withdraws from the airfield.

[0071] In summary, this invention provides a novel and refined flight test method and system for TAWS Mode 2 flight testing, and offers a safe and efficient solution for conducting low-altitude, high-risk flight tests in mountainous areas.

[0072] The embodiments of the present invention have been described above with reference to block diagrams and / or operational descriptions of methods, systems, and computer program products according to embodiments of the present invention. The functions / actions indicated in the blocks may appear in a different order than shown in any flowchart. For example, depending on the functions / actions involved, two blocks shown consecutively may actually be executed substantially simultaneously, or these blocks may sometimes be executed in reverse order.

[0073] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A system for TAWS Mode 2 flight testing, the system comprising: The flight planning module is configured as follows: A virtual runway is constructed, wherein the highest point of the test target mountain is used as the entrance centerline point of the virtual runway, and the altitude of the test target mountain is used as the landing elevation of the virtual runway. A virtual flight path is constructed based on the virtual runway. The flight altitude of each segment of the virtual flight path is constrained by the landing elevation of the runway. The virtual flight path includes the following elements: approach, approach, landing, and go-around. as well as Based on the virtual flight path, generate an approach, landing, and go-around procedure for the flight crew to execute; A barometric pressure measurement module is configured to measure the field pressure of the virtual runway and calculate a corrected sea pressure in real time based on the altitude to provide barometric pressure reference data. The meteorological observation module is configured to provide the meteorological information required for the flight test, including wind speed and direction, visibility and cloud base height at the entrance section of the virtual runway. as well as A VHF communication module configured for air-to-ground communication, including transmitting the barometric reference data and the meteorological information to the aircraft.

2. The system of claim 1, wherein the system further comprises: The airspace condition observation module is configured to observe airspace conditions and report the airspace conditions to the crew via the VHF communication module. The airspace conditions include bird activity and UAV status. Satellite communication module, configured for backup air-to-ground communication; and The simulated control tower module is configured to operate the flight test operation control system.

3. The system of claim 1, wherein the runway direction of the virtual runway is consistent with the design heading of the virtual trajectory.

4. The system of claim 1, wherein the corrected sea pressure is calculated by the following formula: p0 = p[288.15 / (288.15-0.00065H)] 5.256 Where P0 is the corrected sea level pressure, P is the measured surface pressure, and H is the altitude of the target mountain.

5. The system of claim 1, wherein the flight planning module is further configured to generate aeronautical charts for use by the crew based on the approach, landing, and go-around procedure.

6. The system of claim 1, wherein the go-around altitude in the virtual trajectory is adjusted based on the aircraft's minimum radio altitude when the aircraft flies over the entrance of the virtual runway.

7. The system as described in claim 1, wherein the meteorological observation module includes an anemometer, a wind cone, and a visibility observation reference device, and the meteorological information is provided in conjunction with satellite cloud images.

8. A method for TAWS Mode 2 flight testing, the method comprising: A virtual runway is constructed, wherein the highest point of the test target mountain is used as the entrance centerline point of the virtual runway, and the altitude of the test target mountain is used as the landing elevation of the virtual runway. A virtual flight path is constructed based on the virtual runway. The flight altitude of each segment of the virtual flight path is constrained by the landing elevation of the runway. The virtual flight path includes the following elements: approach, approach, landing, and go-around. Based on the virtual flight path, generate an approach, landing, and go-around procedure for the flight crew to execute; The field pressure of the virtual runway is measured and the corrected sea pressure is calculated in real time based on the altitude to provide atmospheric pressure reference data; Provide the meteorological information required for the flight test, including wind speed and direction, visibility and cloud base height at the entrance section of the virtual runway; as well as The air pressure reference data and the meteorological information are sent to the aircraft.

9. The method of claim 8, wherein the method further comprises observing airspace conditions and reporting the airspace conditions to the crew, the airspace conditions including bird activity and drone activity.

10. The method of claim 8, wherein the method further comprises generating a flight chart based on the approach, landing, and go-around procedure for use by the crew.

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