An airborne radar system and remote sensing detection method

Abstract

The application discloses an airborne radar system, which is characterized in that: the airborne radar system comprises cabin equipment for realizing main electrical functions of a radar, more than one belly radar window for realizing communication between inside and outside of an aircraft cabin, an antenna holder for realizing fixed connection of an external antenna and an aircraft body, and an antenna fixedly installed on the antenna holder, and the cabin equipment and the antenna are connected through a radio frequency cable. The application discloses a remote sensing detection method of the airborne radar system, which is characterized in that: the remote sensing detection method mainly has two working states of a transmitting process and a receiving process. The application can be applied to microwave radars, radiation detection, laser surveying and mapping, optical aerial photography and other types of task requirements needing external antennas or components; and in a single flight direction, different types of equipment can be carried to realize optical, microwave and other multifunctional tasks.

Description

Technical Field

[0001] The present invention relates to the field of aviation remote sensing detection technology, and in particular to an airborne radar system and a remote sensing detection method, which are suitable for use in scenarios where they are carried on an aviation platform to realize ground detection. Background Art

[0002] Aerial remote sensing is a form of scientific research that uses flying platforms to collect information, perform precise measurements, and conduct wide-area observations of the geographical environment, climate, meteorology, natural resources, and geological hazards. With the advancement of science and technology, the scope of aerial remote sensing has expanded, and the scientific methods employed have continued to enrich. It has become a vital scientific research activity that effectively promotes national economic development. In recent years, the use of multi-band, multi-mode, and multi-antenna microwave radar systems for Earth observation has become a key form of aerial remote sensing, enabling simultaneous acquisition of multi-dimensional information over a single flight. With this increased functionality, radar electronics systems have become more complex, requiring more individual components for various functions, placing higher demands on their installation and structure. Therefore, research is needed on radar systems suitable for installation on aircraft platforms to address complex application scenarios. Summary of the Invention

[0003] The technical problem to be solved by the present invention is: for application scenarios in the field of aerial remote sensing detection that require the installation of radar electronic equipment and multiple antennas, an airborne radar system and remote sensing detection method are provided, which have a reasonable layout and installation, can be connected inside and outside the cabin, and can meet the needs of simultaneous installation of multiple electronic equipment and multiple antennas.

[0004] The technical solution adopted by the present invention to solve the technical problem is:

[0005] An airborne radar system, characterized by comprising: in-cabin equipment for implementing primary electrical functions of the radar, one or more belly radar windows for communicating between the interior and exterior of the aircraft cabin, an antenna mount for fixedly connecting an out-cabin antenna to the aircraft body, and an antenna fixedly mounted on the antenna mount, wherein the in-cabin equipment and the antenna are connected via a radio frequency cable;

[0006] The in-cabin equipment includes a power module connected to the onboard +28V DC power supply, a radio frequency module for generating and processing radio frequency radar signals, a digital module for generating and receiving baseband radar signals, an auxiliary module for providing GPS and inertial navigation information, a control computer and a test table for human-computer interaction. The control computer configures radar operating parameters and functions and reports equipment status information. The power module provides power to the radio frequency module, the digital module, the auxiliary module, and the control computer.

[0007] Preferably, the power module is installed near the cockpit, and the installation positions of the RF module, the digital module, the auxiliary module, the control computer and the test table are close to the belly radar window. The RF module is directly installed on the cabin floor through shock-absorbing spring feet, and the digital module, the auxiliary module and the control computer are installed on the test table. The test table is installed on the cabin floor through shock-absorbing spring feet. The shock-absorbing spring feet are fixed to the cabin floor slots by screws so that the RF module and the test table are tightly connected to the cabin floor.

[0008] Preferably, the belly radar window includes an opening provided on the belly wall of the aircraft, an upper cover plate installed above the opening, a support frame installed on the aircraft truss in the opening, and a bottom cover plate installed below the opening, wherein the support frame is installed on the aircraft truss by screws.

[0009] Preferably, the antenna stand includes an upper mounting plate, a screw, a circular adapter plate, and a tripod installed above the support frame. The upper mounting plate has 8 screws arranged in a circular distribution. The upper mounting plate is connected to the circular adapter plate downwardly. The upper part of the circular adapter plate is connected to the screw and the lower part is connected to the tripod.

[0010] Preferably, the tripod includes a cross bar one and a cross bar two fixedly connected to the circular adapter plate, a plurality of horizontal bars connecting the cross bar one and the cross bar two, a plurality of vertical bars fixedly installed on a lower surface of the cross bar, a cross bar three fixedly connected to the lower ends of the plurality of vertical bars, a plurality of diagonal bars connecting the cross bar two and the cross bar three, and a plurality of mounting plates provided at the ends of the diagonal bars, and the antenna is mounted on the mounting plates.

[0011] Preferably, a circular hole 1 for passing cables through the cabin is provided in the middle of the upper mounting plate, and a circular hole 2 for passing cables through the cabin corresponding to the circular hole 1 is provided in the middle of the circular adapter plate.

[0012] Preferably, the circular adapter plate includes an upper cover connected to the upper mounting plate via screws, an electric servo mechanism connected to the upper cover, and a lower cover connected to the electric servo mechanism, and the tripod is mounted on the lower surface of the lower cover.

[0013] A remote sensing detection method for an airborne radar system is characterized by: mainly having two working states: a transmitting process and a receiving process;

[0014] During both the transmitting and receiving processes, the control computer configures the operating parameters and sends them to the digital module, which then generates a timing control signal and transmits it to the RF module, the auxiliary module, and the antenna, thereby achieving normal system operation.

[0015] When the system is operating in the transmission process, the digital module sends out an intermediate frequency radar signal, which enters the radio frequency module, is up-converted to an operating frequency signal, is further filtered and amplified to the required power, and is finally transmitted to the antenna for outward radiation;

[0016] When the system is operating in the receiving process, the radar echo signal enters the RF module from the antenna, and is input into the digital module for processing and storage after down-conversion, filtering and amplification. The auxiliary module uses the IMU / GPS combined navigation system to accurately measure various aircraft flight data, reports it to the digital module, and generates and stores auxiliary data after processing. The data stored in the digital module can obtain remote sensing detection information through inversion processing.

[0017] The beneficial effects of the present invention are as follows: the cabin equipment of the present invention is fixed to the cabin floor directly and indirectly according to different weight states; screws and slot structures are used to achieve a firm connection, thereby enhancing the stability of the equipment; and a test table is used to provide a reasonable installation form for small equipment. The present invention opens a circular hole between the upper mounting plate and the circular adapter plate for the use of cables passing through the cabin; by designing the angle of the tripod structure, different antenna installation angles can be achieved, ultimately achieving different radar pitch detection angles. At the same time, by rotating the circular adapter plate, the tripod can be driven to rotate the antenna horizontally, thereby forming different radar horizontal detection angles.

[0018] The present invention can use one or two radar windows according to the mission requirements to meet radar detection tasks with different numbers of antennas; it can also be applied to various types of missions that require external antennas or components, such as radiation detection, laser mapping, and optical aerial photography. By rationally matching different types of equipment, multi-functional tasks can be completed in a single voyage. The present invention designs the layout and installation of the in-cabin electronic equipment of the airborne radar system, and combines the design of the radar detection window to enhance the fixed stability of the equipment and improve space utilization; it has the ability to work with multiple antennas, improves observation efficiency, and reduces flight detection costs. The antenna rack installation method and structure designed by the present invention realize the stable installation of the antenna and the fuselage; it has the ability to adjust the pitch angle and horizontal angle, improves the applicability of the installation structure, and reduces the increase in tooling costs caused by different working modes. The results of the present invention are universal and are particularly suitable for remote sensing payload-carrying applications based on aircraft platforms; the electric servo mechanism can be further upgraded to enhance the detection capability of the radar system.

[0019] The present invention can be applied to various tasks that require external antennas or components, such as microwave radar, radiation detection, laser mapping, and optical aerial photography; and can realize optical, microwave and other multifunctional tasks by carrying different types of equipment in a single navigation. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the structural design of an embodiment of the present invention.

[0021] Figure 2 Schematic diagram of electrical design of an embodiment of the present invention.

[0022] Figure 3 It is a schematic diagram of a cabin floor slot according to an embodiment of the present invention.

[0023] Figure 4 It is the overall layout parameter of the cabin floor slot size in the embodiment of the present invention.

[0024] Figure 5 It is the cross-sectional parameter of the cabin floor slot in the embodiment of the present invention.

[0025] Figure 6 It is a top view of a schematic diagram of the design of the belly radar window according to an embodiment of the present invention.

[0026] Figure 7 It is a side view of a schematic diagram of the design of the belly radar window according to an embodiment of the present invention.

[0027] Figure 8 It is a schematic diagram of the antenna rack structure design according to an embodiment of the present invention.

[0028] In the figure: 1. Cabin equipment, 2. Belly radar window, 3. Antenna rack, 4. Power module, 5. Radio frequency module, 6. Digital module, 7. Auxiliary module, 8. Control computer, 9. Test table, 10. Antenna, 11. Shock-absorbing spring foot, 12. Cabin floor, 13. Cabin floor slot, 21. Radar front window, 22. Radar rear window, 23. Upper cover, 24. Support frame, 25. Aircraft truss, 26. Aircraft belly wall, 27. Bottom cover, 28. Opening, 32. Upper mounting plate, 33. Screw, 34. Circular adapter plate, 35. Tripod, 36. Crossbar 1, 37. Crossbar 2, 38. Mounting plate, 39. Horizontal rod, 40. Vertical rod, 41. Cockpit, 42. Passenger cabin, 43. Crossbar 3, 44. Diagonal rod, 45. Round hole 1, 46. Round hole 2. DETAILED DESCRIPTION

[0029] The following embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples. The following examples are used to illustrate the present invention but are not intended to limit the scope of the present invention.

[0030] like Figures 1 to 8 As shown, an airborne radar system includes an in-cabin device 1 for implementing the main electrical functions of the radar, two belly radar windows 2 for connecting the inside and outside of the aircraft cabin, an antenna rack 3 for fixedly connecting the out-cabin antenna to the aircraft body, and an antenna 10 fixedly mounted on the antenna rack 3. The in-cabin device 1 and the antenna 10 are connected via a radio frequency cable.

[0031] The in-cabin equipment 1 includes a power module 4, a radio frequency module 5, a digital module 6, an auxiliary module 7, a control computer 8, and a test table 9. The power module 4 is installed near the cockpit 41 and is connected to the aircraft's +28V DC power supply. It converts the voltage required by each module and provides power to the radio frequency module 5, digital module 6, auxiliary module 7, and control computer 8. The radio frequency module 5, digital module 6, auxiliary module 7, control computer 8, and test table 9 are installed in the passenger cabin 42. The radio frequency module 5, digital module 6, auxiliary module 7, control computer 8, and test table 9 are installed near the belly radar window 2. The radio frequency module 5 is a relatively heavy device and is directly mounted to the cabin floor 12 on the belly 26 via shock-absorbing spring feet 11. It is used to generate and process radio frequency radar signals. The digital module 6, auxiliary module 7, and control computer 8 are relatively lightweight devices and are all mounted on the test table 9, which is mounted to the cabin floor 12 via shock-absorbing spring feet 11. Shock-absorbing spring feet 11 are screwed to cabin floor slots 13, tightly connecting the RF module 5 and test table 9 to the cabin floor 12. Digital module 6 generates, receives, and processes baseband radar signals, storing various data. Auxiliary module 7 primarily provides GPS and inertial navigation information, while control computer 8 is used for human-computer interaction, configuring radar operating parameters and functions, and reporting device status information. Cabin equipment 1 is secured to the cabin floor 12 directly and indirectly, depending on its weight. Screws and slots provide a secure connection, enhancing device stability. Test table 9 provides a suitable installation method for small devices.

[0032] In this embodiment, the specific size parameters of the cabin ground slot 13 are as follows: Figures 3 to 5 Two fixing grooves are designed on the cabin floor 12, with a distance of 52 cm between them and a distance of 10 cm from the cabin side wall. The groove depth is about 1 cm, and the card thickness is about 0.25 cm.

[0033] The belly radar window 2 consists of a front radar window 21 and a rear radar window 22. Each belly radar window 2 comprises an opening 28 in the belly wall 26 of the aircraft, an upper cover 23 mounted above the opening 28, a support frame 24 mounted on the aircraft truss 25 within the opening 28, and a bottom cover 27 mounted below the opening 28. The aircraft truss 25 is located at the bottom of the belly wall 26. Together, they form the main support structure of the aircraft body. The support frame 27 is screwed to the aircraft truss 25 to accommodate different equipment installations and prevent direct modification of the aircraft truss 25, which could cause irreversible damage. The upper cover 23 and bottom cover 27 protect the cabin floor 12 and the outer side of the belly when the belly radar window 2 is not in use. The upper cover 23 is screwed to the upper surface of the cabin floor 12 to maintain the integrity of the cabin's internal structure. The bottom cover 27 is mounted on the outer side of the aircraft's belly. Its dimensions are slightly larger than the overall opening size. It is removed when in use and screwed back on when not in use to maintain the integrity of the outer side of the belly.

[0034] In this embodiment, each belly radar window 2 is 75 cm long and 60 cm wide in the flight direction, with the depth determined by the thickness of the aircraft belly. The aircraft trusses 25 intersect to form a rectangle with a long side of 57 cm and a short side of 45 cm. The support frame 24 measures 57 cm by 48 cm by 13 cm. The upper and lower cover plates 23 and 27 are slightly larger than the belly radar window 2.

[0035] The antenna stand 3 includes an upper mounting plate 32 mounted above the support frame 24, screws 33, a circular adapter plate 34, and a tripod 35. The upper mounting plate 32 has eight screws 33 arranged in a circular pattern and is connected downwardly to the circular adapter plate 34. The upper portion of the circular adapter plate 34 is connected to the screws 33, and the lower portion is connected to the tripod 35. The tripod 35 includes a first crossbar 36 and a second crossbar 37 fixedly connected to the circular adapter plate 34, a plurality of horizontal rods 39 connecting the first crossbar 36 and the second crossbar 37, a plurality of vertical rods 40 fixedly mounted on the lower surface of the first crossbar 36, a third crossbar 43 fixedly connected to the lower ends of the plurality of vertical rods 40, a plurality of diagonal rods 44 connecting the second crossbar 37 and the third crossbar 43, and a plurality of mounting plates 38 provided at the ends of the diagonal rods 44. The antenna 10 is mounted on the mounting plates 38. The upper mounting plate 32 has a central circular hole 45 for cable routing. The circular adapter plate 34 has a corresponding central circular hole 46 for cable routing. By rotating the circular adapter plate 34, the tripod 35 can rotate the antenna 10 along the flight direction, perpendicular to the flight path, or at various angles. The rotating circular adapter plate 34 and screw structure can also be upgraded to an electric servo mechanism to further enhance the radar system's detection capabilities.

[0036] In this embodiment, the tripod 35 is formed by welding together multiple hollow aluminum tubes. The main structure, crossbars 1 36, 2 37, and 3 43, are all welded together from thick aluminum tubes. The supporting structure, horizontal bars 39, vertical bars 40, and diagonal bars 44, are all welded together from thin aluminum tubes. Crossbars 1 36 and 2 37 are connected to a circular adapter plate 34 via screws. Several mounting plates 38 are designed on the sides of the tripod 35 to connect to the antenna 10. The horizontal and vertical spacing between the aluminum tubes of the tripod 35 can be customized to achieve different angles, ultimately forming a triangular structure to achieve different antenna installation angles and, ultimately, different radar electromagnetic wave incident angles.

[0037] In this embodiment, a circular hole 45 is provided between the upper mounting plate 32 and the circular adapter plate 34 for cable routing. By designing the angle of the tripod 35, different antenna mounting angles can be achieved, ultimately realizing different radar elevation detection angles. Furthermore, by rotating the circular adapter plate 34, the tripod 35 can drive the antenna's horizontal rotation, thereby creating different radar horizontal detection angles. The upper mounting plate 32 measures 57 cm by 48 cm by 13 cm, matching the dimensions of the support frame 24 and ensuring a tight fit. The tripod 35 is 1 meter long and 30 cm high, forming a 45-degree triangle cross-section, ultimately enabling antenna 10 to achieve a 45-degree elevation detection angle. The long side of the tripod 35 is oriented in the aircraft's flight direction, ensuring that the horizontal normal of the antenna 10 is perpendicular to the flight direction. The thick aluminum tube is 4 cm in diameter with a 2 mm wall thickness. The thin aluminum tube, as well as the horizontal rod 39 and vertical rod 40, is 3 cm in diameter with a 1.5 mm wall thickness.

[0038] The airborne radar system proposed in this invention can utilize one or two belly radar windows 2, depending on mission requirements, to meet radar detection tasks requiring different numbers of antennas 10. It can also be applied to various missions requiring external antennas or components, such as radiation detection, laser mapping, and optical aerial photography. By properly combining different types of equipment, it is possible to complete multiple missions in a single flight.

[0039] A remote sensing detection method for an airborne radar system mainly includes two working states: a transmitting process and a receiving process;

[0040] During both the transmission and reception processes, the control computer 8 configures the operating parameters and sends them to the digital module 6, which then generates a timing control signal and transmits it to the RF module 5, the auxiliary module 7, and the antenna 10, thereby achieving normal operation of the system.

[0041] When the system is working in the transmission process, the digital module 6 sends out an intermediate frequency radar signal, which enters the radio frequency module 5 and is up-converted to the working frequency signal. After further filtering and amplification to the required power level, it is finally transmitted to the antenna 10 for outward radiation.

[0042] When the system is working in the receiving process, the radar echo signal enters the RF module 5 through the antenna 10, and is input into the digital module 6 for processing and storage after down-conversion, filtering and amplification. The auxiliary module 7 uses the IMU / GPS combined navigation system to accurately measure various aircraft flight data and report it to the digital device module 6. After processing, auxiliary data is generated and stored. The data stored in the digital module 6 can be used to obtain remote sensing detection information through inversion processing.

[0043] In this embodiment, active radar detection is employed. Digital module 6 generates a linear frequency modulation signal with a frequency of 5.4 GHz, a bandwidth of 400 MHz, a pulse width of 10 μs, and a pulse modulation period of 3000. RF module 5 amplifies this signal to a peak power of 200 W and transmits it via antenna 10. Antenna 10 utilizes a waveguide slot array with a beamwidth of 12°. After data processing, radar images with a resolution better than 0.5 m can be obtained. Auxiliary module 7 reports information including GPS time, GPS latitude and longitude of the flight platform, flight platform altitude, and the flight platform's three-axis velocity, three-axis acceleration, and three-axis rotation angle.

[0044] The present invention can be modified in various ways that are obvious to those skilled in the art, and such modifications are not considered to depart from the scope of the present invention. All such modifications obvious to those skilled in the art are intended to be included within the scope of the present claims.

Claims

1. An airborne radar system, characterized in that: It includes in-cabin equipment for realizing the main electrical functions of the radar, one or more belly radar windows for realizing communication between the inside and outside of the aircraft cabin, an antenna rack for realizing fixed connection between the out-cabin antenna and the aircraft body, and an antenna fixedly mounted on the antenna rack. The in-cabin equipment and the antenna are connected by a radio frequency cable; The cabin equipment includes a power module connected to the onboard +28V DC power supply, a radio frequency module for generating and processing radio frequency radar signals, a digital module for generating, receiving and processing baseband radar signals, an auxiliary module for providing GPS and inertial navigation information, a control computer for human-computer interaction, and a test table. The control computer configures radar operating parameters and functions and reports equipment status information. The power module provides power to the radio frequency module, the digital module, the auxiliary module, and the control computer. The power module is installed near the cockpit, and the installation positions of the radio frequency module, the digital module, the auxiliary module, the control computer, and the test table are near the belly radar window. The radio frequency module is directly installed on the cabin floor via shock-absorbing spring feet. The digital module, the auxiliary module, and the control computer are installed on the test table. The test table is installed on the cabin floor via shock-absorbing spring feet. The shock-absorbing spring feet are fixed to the cabin floor slots via screws so that the radio frequency module and the test table are tightly connected to the cabin floor. The belly radar window includes an opening provided on the belly wall of the aircraft, an upper cover plate installed above the opening, a support frame installed on the aircraft truss in the opening, and a bottom cover plate installed below the opening, wherein the support frame is installed on the aircraft truss by screws.

2. The airborne radar system according to claim 1, wherein: The antenna stand includes an upper mounting plate, a screw, a circular adapter plate, and a tripod installed above the support frame. The upper mounting plate has 8 screws arranged in a circular distribution. The upper mounting plate is connected to the circular adapter plate downward. The upper part of the circular adapter plate is connected to the screw and the lower part is connected to the tripod.

3. The airborne radar system according to claim 2, wherein: The tripod includes a crossbar 1 and a crossbar 2 fixedly connected to the circular adapter plate, a plurality of horizontal rods connecting the crossbar 1 and the crossbar 2, a plurality of vertical rods fixedly installed on a lower surface of the crossbar, a crossbar 3 fixedly connected to the lower ends of the plurality of vertical rods, a plurality of oblique rods connecting the crossbar 2 and the crossbar 3, and a plurality of small mounting plates provided at the ends of the oblique rods, and the antenna is mounted on the small mounting plates.

4. The airborne radar system according to claim 2, wherein: A circular hole 1 for passing cables through the cabin is provided in the middle of the upper mounting plate, and a circular hole 2 for passing cables through the cabin corresponding to the circular hole 1 is provided in the middle of the circular adapter plate.

5. The airborne radar system according to claim 2, wherein: The circular adapter plate includes an upper cover connected to the upper mounting plate via screws, an electric servo mechanism connected to the upper cover, and a lower cover connected to the electric servo mechanism. The tripod is mounted on the lower surface of the lower cover.

6. The remote sensing detection method of an airborne radar system according to any one of claims 1 to 5, characterized in that: There are mainly two working states: transmitting process and receiving process; During both the transmitting and receiving processes, the control computer configures the operating parameters and sends them to the digital module, which then generates a timing control signal and transmits it to the RF module, the auxiliary module, and the antenna, thereby achieving normal system operation. When the system is operating in the transmission process, the digital module sends out an intermediate frequency radar signal, which enters the radio frequency module, is up-converted to an operating frequency signal, is further filtered and amplified to the required power, and is finally transmitted to the antenna for outward radiation; When the system is operating in the receiving process, the radar echo signal enters the RF module from the antenna, and is input into the digital module for processing and storage after down-conversion, filtering and amplification. The auxiliary module uses the IMU / GPS combined navigation system to accurately measure various aircraft flight data, reports it to the digital module, and generates and stores auxiliary data after processing. The data stored in the digital module can obtain remote sensing detection information through inversion processing.

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