An unmanned airborne combat radar drone target

Abstract

The application discloses a kind of unmanned aerial vehicle-borne fighter radar target, including nose direction typical feature simulation combination, wing direction typical feature simulation combination and tail direction typical feature simulation combination, and the application relates to radar target technical field.The simulation combination of the nose, wing and tail direction typical features of the unmanned aerial vehicle-borne fighter radar target, can realize the simulation of the narrow airspace peak characteristic in the airspace RCS distribution characteristic of fighter through 60 ° variation angle reflector, and realize the simulation of the smooth spatial distribution characteristic in the airspace RCS distribution characteristic of fighter through dragon ball, and with 60 ° variation angle reflector combination realizes the simulation of fluctuation characteristic between multiple scatterers, multiple reflectors.Wave-absorbing material is combined with variation angle reflector, and the elimination problem of multiple reflectors in the combination body is realized.The application can realistically simulate the RCS spatial distribution characteristic of fighter, and is helpful to improve the examination authenticity and actual combat training effect of whole kill chain of troops.

Description

Technical Field

[0001] This invention relates to the field of technology, specifically to a radar target drone for unmanned aerial vehicles (UAVs) carrying fighter jets. Background Technology

[0002] Radar target drones are indispensable testing devices in the development, performance evaluation, combat effectiveness testing, combat training, and live-fire exercises of early warning radar systems and air defense weapon systems. Under the guidance of current new military doctrines, live-fire training is becoming increasingly important, requiring the most realistic simulation of real combat scenarios to improve the effectiveness of red-blue force confrontation exercises. To achieve optimal results, radar target drones must not only realistically simulate the electromagnetic characteristics of enemy aircraft or missile radar targets but also be cost-effective to meet the needs of large-scale use in equipment development and combat training.

[0003] Existing target drones can be broadly categorized into two types: target drones with autonomous propulsion systems and radar target simulators without autonomous propulsion systems. Target drones with autonomous propulsion systems can be further divided into two categories: real target drones and aircraft equipped with radar RCS enhancement devices such as corner reflectors. Radar target simulators without autonomous propulsion systems also fall into two main categories: airborne sling-mounted radar target simulators and airborne towed radar target simulators. Target drones with autonomous propulsion systems offer relatively superior performance but are expensive; radar target simulators without autonomous propulsion systems are relatively inexpensive but offer lower performance simulation realism. Furthermore, the nose, sides, and tail of fighter jets exhibit significant RCS peak areas, making them the most vulnerable to radar detection and attack. Therefore, accurate simulation of the RCS spatial distribution characteristics in these three directions is a key focus in target drone design. Consequently, a high-performance and low-cost fighter jet radar target drone needs to be designed. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention provides an unmanned aerial vehicle (UAV)-borne radar target drone, which solves the aforementioned problems.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a drone-borne radar target drone, comprising: The typical feature simulation assembly in the nose direction includes three first 60° variable angle reflectors (one large and two small), two first Luneburg spheres, and an insulating connecting frame. The insulating connecting frame is installed in the gap between the three first 60° variable angle reflectors, and the two first Luneburg spheres are located on both sides of the rear end of the large first 60° variable angle reflector. The wing-oriented typical feature simulation assembly includes four second 60° variable angle reflectors, two first metal spheres and one first metal baffle. The four second 60° variable angle reflectors are connected to each other vertically and horizontally. The two first metal spheres are installed at the two vertices of the front middle and right side of the four second 60° variable angle reflectors. The first metal baffle is installed on the inner side of the right wall of the upper right second 60° variable angle reflector. The typical feature of the tail section is simulated as an assembly including a third 60° variable angle reflector, two second metal spheres and a second Luneburg sphere. The two second metal spheres are mounted at the two vertices on the front side of the third 60° variable angle reflector, and the second Luneburg sphere is mounted on the inner bottom surface of the third 60° variable angle reflector.

[0006] Preferably, the three first 60° variable angle reflectors are composed of a first base plate and two main right-angled triangles and two side right-angled triangles vertically mounted on its top, and the two main right-angled triangles and the two side right-angled triangles are connected by an insulating connecting frame.

[0007] Preferably, the two side right-angled triangles are located at the middle position outside the two main right-angled triangles, and the two main right-angled triangles and the two side right-angled triangles form a 60° horizontal angle between each other.

[0008] Preferably, the four second 60° variable angle reflectors are composed of three large right-angled triangular plates vertically mounted on the second base plate and its upper and lower surfaces, respectively, and the three large right-angled triangular plates on the same side form a 60° angle between each other.

[0009] Preferably, the two first metal spheres are specifically embedded in the two front corners of the second base plate, and the first metal baffle is specifically installed in the middle position between the inner side of the upper rightmost large right-angled triangle and the top of the second base plate.

[0010] Preferably, the third 60° variable angle reflector is composed of a third base plate and two small right-angled triangular plates at a 60° angle to each other at its top. A second metal baffle is installed between the inner sides of the third base plate and the two small right-angled triangular plates and on the rear side of the second Luneburg ball, and the second metal baffle is at a 60° angle to the small right-angled triangular plates.

[0011] Preferably, the simulated assembly of typical features in the nose direction, the simulated assembly of typical features in the wing direction, and the simulated assembly of typical features in the tail direction are all supported and erected on a display stand for display. The display stand includes a base and several sets of support columns installed on its top by bolts. The simulated assembly of typical features in the nose direction, the simulated assembly of typical features in the wing direction, and the simulated assembly of typical features in the tail direction are all installed on the support columns.

[0012] Preferably, the top plate of the support column below the typical feature of the head direction simulation assembly extends to the left and right sides, and the two first Luneburg balls are installed on the top of both ends of the support column top plate without contacting the first 60° variable angle reflector.

[0013] Preferably, the back surfaces of the simulated assembly of typical features in the nose direction, the simulated assembly of typical features in the wing direction, and the simulated assembly of typical features in the tail direction are all covered with radar-absorbing material. Beneficial effects

[0014] This invention provides an unmanned aerial vehicle (UAV)-borne radar target drone. Compared with existing technologies, it has the following advantages: 1. This UAV-borne fighter jet radar target drone simulates the typical characteristics of the nose, wings, and tail directions in a simple and easy-to-manufacture assembly. It can simulate the narrow-domain peak characteristics of the fighter jet's airspace RCS distribution using a 60° variable-angle reflector, and the stable spatial distribution characteristics of the fighter jet's airspace RCS distribution using a Luneburg sphere. Furthermore, the combination with the 60° variable-angle reflector simulates the wave characteristics between multiple scatterers and multiple reflectors. The combination of absorbing materials and variable-angle reflectors eliminates the problem of multiple reflectors within the assembly. This invention can realistically simulate the spatial distribution characteristics of the fighter jet's RCS, helping to improve the realism of the full-kill chain assessment and the effectiveness of combat training, offering significant advantages over other target drones.

[0015] 2. This UAV-borne fighter radar target drone features simulated combinations of typical features in the nose direction, wing direction, and tail direction, supported by a display stand, facilitating display and simulation training. Attached Figure Description

[0016] Figure 1 This is a front-view perspective view of the simulated assembly of typical features in the nose direction of the present invention; Figure 2 This is a rear-view perspective view of the simulated assembly of typical features in the nose direction of the present invention; Figure 3 This is a front-view perspective view of the simulated assembly of typical features in the wing direction of the present invention; Figure 4 This is a rear-view perspective view of the simulated assembly of typical features in the wing direction of the present invention; Figure 5 This is a front-view perspective view of the simulated assembly of typical features in the tail direction of the present invention; Figure 6 This is a rear-view perspective view of the simulated assembly of typical features in the tail direction of the present invention; Figure 7 This is a perspective view of the overall structure of the present invention; Figure 8This is a diagram showing the RCS spatial distribution characteristics of the simulated assembly with typical features in the nose direction of the present invention at different frequencies. Figure 9 This is a spatial distribution diagram of the RCS of the radar target drone carried by the UAV of this invention.

[0017] In the diagram: 1-Simulated assembly of typical features in the nose direction, 11-First Luneburg sphere, 12-Insulating connecting frame, 13-First base plate, 14-Main right-angled triangle plate, 15-Side right-angled triangle plate, 2-Simulated assembly of typical features in the wing direction, 21-First metal sphere, 22-First metal baffle, 23-Second base plate, 24-Large right-angled triangle plate, 3-Simulated assembly of typical features in the tail direction, 31-Second metal sphere, 32-Second Luneburg sphere, 33-Third base plate, 34-Small right-angled triangle plate, 4-Display stand, 41-Base, 42-Support column. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] This invention provides two technical solutions: Figures 1-6 and Figures 8-9 The first embodiment is shown: an unmanned aerial vehicle (UAV)-borne radar target drone, comprising a nose-direction typical feature simulation assembly 1, a wing-direction typical feature simulation assembly 2, and a tail-direction typical feature simulation assembly 3. The typical feature simulation assembly 1 in the nose direction includes three first 60° variable angle reflectors (one large and two small), two first Luneburg spheres 11, and an insulating connecting frame 12. The insulating connecting frame 12 is installed in the gap between the three first 60° variable angle reflectors, and the two first Luneburg spheres 11 are located on both sides of the rear end of the large first 60° variable angle reflector. The three first 60° variable angle reflectors are composed of a first base plate 13 and two main right-angled triangle plates 14 and two side right-angled triangle plates 15 vertically mounted on its top, and the two main right-angled triangle plates 14 and the two side right-angled triangle plates 15 are connected by an insulating connecting frame 12. In one possible implementation, the connecting frame 12 is provided with a slot for connecting the main right-angled triangle 14 and the side right-angled triangle 15.

[0020] In one possible implementation, the cross-sectional shape of the connecting frame 12 is rectangular or L-shaped.

[0021] In one possible implementation, the connecting frame 12 is made of a wave-transparent material.

[0022] In one possible implementation, the connecting frame 12 is made of PVC plastic.

[0023] In one possible implementation, at least two main right-angled triangles 14 and side right-angled triangles 15 are provided with fixed interfaces for connecting a Doppler effect simulator.

[0024] In one possible implementation, the main right-angled triangle 14 and the side right-angled triangle 15 are made of aluminum or stainless steel.

[0025] In one possible implementation, when the difference between the actual maximum value of the RCS of the first 60° variable angle reflector and the theoretical value is less than 1 dB, the distance between the right-angled sides of the two main right-angled triangles 14 or side right-angled triangles 15 connected to the same connecting frame 12 is less than or equal to 2.5 mm.

[0026] The two side right-angled triangles 15 are located in the middle of the outer side of the two main right-angled triangles 14, and the two main right-angled triangles 14 and the two side right-angled triangles 15 form a horizontal angle of 60° between each other.

[0027] The main right-angled triangle 14 has a right-angled side length of 600mm, the smaller side right-angled triangle 15 has a right-angled side length of 300mm, and both have a thickness of 3mm; the first Lomber ball 11 has a diameter of 80mm.

[0028] The wing-oriented typical feature simulation assembly 2 includes four second 60° variable angle reflectors, two first metal spheres 21 and one first metal baffle 22. The four second 60° variable angle reflectors are connected to each other vertically and horizontally. The two first metal spheres 21 are installed at the middle of the front side and the two vertices on the right side of the four second 60° variable angle reflectors. The first metal baffle 22 is installed on the inner side of the right wall of the upper right second 60° variable angle reflector. The four second 60° variable angle reflectors are composed of three large right-angled triangles 24 vertically installed on the second base plate 23 and its upper and lower surfaces, and the three large right-angled triangles 24 on the same side form a 60° angle between each other. Two first metal spheres 21 are specifically embedded in the two front corners of the second base plate 23. The first metal baffle 22 is specifically installed in the middle position between the inner side of the upper rightmost large right-angled triangle 24 and the top of the second base plate 23, and the left vertex of the first metal baffle 22 is offset 50mm to the rear.

[0029] In one possible implementation, the second 60° variable angle reflector and the first metal baffle 22 are made of aluminum or stainless steel.

[0030] In one possible implementation, the first metal sphere 21 is made of a silver-plated sphere with a silver plating thickness of 2 mm.

[0031] Furthermore, the large right-angled triangle 24 has a side length of 780mm and a thickness of 3mm; the first metal sphere 21 has a diameter of 200mm; and the first metal baffle 22 has a right-angled side length of 390mm and a thickness of 3mm.

[0032] The typical feature simulation assembly 3 in the tail direction includes a third 60° variable angle reflector, two second metal spheres 31 and a second Luneburg sphere 32. The two second metal spheres 31 are installed at the two vertices on the front side of the third 60° variable angle reflector, and the second Luneburg sphere 32 is installed on the inner bottom surface of the third 60° variable angle reflector.

[0033] The third 60° variable angle reflector is composed of a third base plate 33 and two small right-angled triangular plates 34 at a 60° angle to each other at its top. A second metal baffle 35 is installed between the inner sides of the third base plate 33 and the two small right-angled triangular plates 34 and behind the second Luneburg ball 32. The second metal baffle 35 and the small right-angled triangular plates 34 form a 60° angle.

[0034] In one possible implementation, the third 60° variable angle reflector and the second metal baffle 35 are made of aluminum or stainless steel.

[0035] In one possible implementation, the second metal ball 31 is made of a silver-plated sphere with a silver plating thickness of 2 mm.

[0036] Furthermore, the small right-angled triangle 34 has a right-angled side length of 540mm and a thickness of 3mm; the second metal ball 31 has a diameter of 80mm, and the right-side second metal ball 31 is placed 67.5mm away from the front vertex; the second Luneburg ball 32 has a diameter of 80mm, and is placed 270mm away from the rear vertex of the 60° angle reflector, and moved up 40mm; the second metal baffle 35 has a right-angled side length of 135mm and a thickness of 3mm, and the second metal baffle 35 is placed on the side 135mm away from the vertex, and the left vertex of the right-side second metal baffle 35 is moved back 20mm.

[0037] The back of the simulated assembly 1 (nose direction), the simulated assembly 2 (wing direction), and the simulated assembly 3 (tail direction) are all covered with absorbing material. The absorbing material is 3mm thick and has a vertical attenuation of not less than 17dB for plane waves incident at a working frequency of 10GHz.

[0038] Figure 8The diagram shows the RCS spatial distribution characteristics of the simulated combination of typical nose-direction features provided in this embodiment of the invention at different frequencies. It can be seen that at the three frequencies, the simulation scheme of the typical nose-direction features all have the characteristic of high RCS value in the narrow airspace range of the fighter jet's RCS spatial distribution characteristics. This proves that the simulation scheme of the typical nose-direction features is suitable for simulating fighter jets in multiple frequency bands. The simulated combination of typical wing and tail-direction features is also suitable for simulating fighter jets in multiple frequency bands.

[0039] Figure 9 This is a spatial distribution characteristic diagram of the RCS of a UAV-borne radar target drone provided in an embodiment of the present invention, with reference to... Figure 9 When the UAV-borne radar target drone is placed horizontally, the peak RCS values ​​at 10 GHz are observed near -180°, -152°, -90°, -39°, -9°, 0°, 9°, 39°, 90°, and 152°. The RCS values ​​are as follows: -180°: 21.26 dBsm; -152°: 12.37 dBsm; -90°: 38.17 dBsm; and -39°: 17.14 dBsm. The RCS value at -9° is 13.09 dBsm, at 0° it is 25.49 dBsm, at 9° it is 12.66 dBsm, at 39° it is 17.14 dBsm, at 90° it is 38.97 dBsm, and at 152° it is 12.37 dBsm. The RCS value at 0° has an error of 1.39 dB compared to typical data for fighter jets, and the RCS values ​​at other peaks also have errors of less than 3 dB compared to typical data for fighter jets.

[0040] This invention presents a simulated assembly of typical characteristics in the nose, wing, and tail directions, featuring a simple structure that is easy to manufacture and assemble. It can simulate the narrow-domain peak characteristics of the RCS distribution in the airspace of a fighter jet using a 60° variable-angle reflector, and the stable spatial distribution characteristics of the RCS distribution in the airspace of a fighter jet using a Luneburg sphere. Furthermore, the combination with the 60° variable-angle reflector simulates the wave characteristics between multiple scatterers and multiple reflectors. The combination of absorbing materials and variable-angle reflectors eliminates the problem of multiple reflectors within the assembly. This invention can realistically simulate the spatial distribution characteristics of the RCS of a fighter jet, helping to improve the realism of the full-kill chain assessment and the effectiveness of combat training, offering significant advantages over other target drones.

[0041] Figure 7The second embodiment is shown, and its main difference from the first embodiment is that the typical feature simulation assembly 1 in the nose direction, the typical feature simulation assembly 2 in the wing direction, and the typical feature simulation assembly 3 in the tail direction are all supported and erected on the display stand 4 for display. The display stand 4 includes a base 41 and several sets of support columns 42 that are bolted to its top. The typical feature simulation assembly 1 in the nose direction, the typical feature simulation assembly 2 in the wing direction, and the typical feature simulation assembly 3 in the tail direction are all installed on the support columns 42. The top plate of the support column 42 below the typical feature simulation assembly 1 in the nose direction extends to the left and right sides. Two first Luneburg balls 11 are installed on the top of the top plates at both ends of the support column 42 and do not contact the first 60° variable angle reflector.

[0042] By setting up a display stand 4 to support the display of the typical features of the nose direction (simulated assembly 1), the typical features of the wing direction (simulated assembly 2), and the typical features of the tail direction (simulated assembly 3), it is convenient to display them and to load them on the UAV for simulation training.

[0043] Furthermore, any content not described in detail in this specification is existing technology known to those skilled in the art.

[0044] It should be noted that, in this document, relational terms such as "first" and "second" are used only 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 process, method, article, or apparatus.

[0045] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A drone-borne radar target drone, characterized in that: include: The typical feature simulation assembly in the nose direction includes three first 60° variable angle reflectors (one large and two small), two first Luneburg spheres, and an insulating connecting frame. The insulating connecting frame is installed in the gap between the three first 60° variable angle reflectors, and the two first Luneburg spheres are located on both sides of the rear end of the large first 60° variable angle reflector. The wing-oriented typical feature simulation assembly includes four second 60° variable angle reflectors, two first metal spheres and one first metal baffle. The four second 60° variable angle reflectors are connected to each other vertically and horizontally. The two first metal spheres are installed at the two vertices of the front middle and right side of the four second 60° variable angle reflectors. The first metal baffle is installed on the inner side of the right wall of the upper right second 60° variable angle reflector. The typical feature of the tail section is simulated as an assembly including a third 60° variable angle reflector, two second metal spheres and a second Luneburg sphere. The two second metal spheres are mounted at the two vertices on the front side of the third 60° variable angle reflector, and the second Luneburg sphere is mounted on the inner bottom surface of the third 60° variable angle reflector.

2. The UAV-borne radar target drone according to claim 1, characterized in that: The three first 60° variable angle reflectors consist of a first base plate and two main right-angled triangles and two side right-angled triangles mounted vertically on top of it, and the two main right-angled triangles and the two side right-angled triangles are connected by an insulating connecting frame.

3. The UAV-borne radar target drone according to claim 2, characterized in that: The two side right-angled triangles are located in the middle of the outer side of the two main right-angled triangles, and the two main right-angled triangles and the two side right-angled triangles form a 60° horizontal angle between each other.

4. The UAV-borne radar target drone according to claim 1, characterized in that: The four second 60° variable angle reflectors are composed of three large right-angled triangles vertically mounted on the second base plate and its upper and lower surfaces, respectively, with the three large right-angled triangles on the same side forming a 60° angle between each other.

5. The UAV-borne radar target drone according to claim 4, characterized in that: The two first metal spheres are specifically embedded in the two front corners of the second base plate, and the first metal baffle is specifically installed in the middle position between the inner side of the upper rightmost large right-angled triangle and the top of the second base plate.

6. The UAV-borne radar target drone according to claim 1, characterized in that: The third 60° variable angle reflector is composed of a third base plate and two small right-angled triangular plates at a 60° angle to each other at its top. A second metal baffle is installed between the inner sides of the third base plate and the two small right-angled triangular plates and on the back side of the second Luneburg ball. The second metal baffle is at a 60° angle to the small right-angled triangular plates.

7. The UAV-borne radar target drone according to claim 1, characterized in that: The simulated assemblies of typical features in the nose direction, wing direction, and tail direction are all supported and erected on a display stand for display. The display stand includes a base and several sets of support columns on its top, which are bolted together. The simulated assemblies of typical features in the nose direction, wing direction, and tail direction are all mounted on the support columns.

8. The UAV-borne radar target drone according to claim 7, characterized in that: The typical features of the machine head direction simulate the top plate of the support column below the assembly extending to the left and right sides, with two first Luneburg spheres installed at the top of both ends of the support column top plate without contacting the first 60° variable angle reflector.

9. The UAV-borne radar target drone according to claim 1, characterized in that: The back of the simulated assembly of typical features in the nose direction, the simulated assembly of typical features in the wing direction, and the simulated assembly of typical features in the tail direction are all covered with radar-absorbing material.

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