An unmanned aerial vehicle radar search apparatus

Abstract

The utility model relates to an unmanned vehicle technical field, and disclose an unmanned vehicle radar search device, including unmanned vehicle and radar, unmanned vehicle includes streamline fuselage, the wing that distributes in the top corner department of fuselage four around, and the landing gear that sets up in the bottom of both sides of fuselage, radar is embedded in the inside of fuselage, and radar is connected with the fuselage through two stage damping structure, integral type connection has the auxiliary search antenna on the fuselage located at the top of radar, and the auxiliary search antenna is connected with the fuselage through driving piece. The application reduces the vibration displacement of unmanned vehicle landing and in flight through two stage damping structure, and the air damping buffer is formed by cylinder, rubber ring and piston column when flying, inhibits high frequency vibration displacement, and the levitation force is generated when landing electromagnet and magnet block, and the impact is absorbed in magnetic suspension gap, and the mechanical clamping is matched, and the vibration acceleration is attenuated, and the radar search efficiency is guaranteed.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle technology, specifically to an unmanned aerial vehicle radar search device. Background Technology

[0002] Radar search by unmanned aerial vehicles (UAVs) is achieved by transmitting and receiving electromagnetic waves. Its working principle is as follows: the radar transmitter generates electromagnetic waves of a specific frequency and transmits them into space in a directional beam through an antenna. When these electromagnetic waves encounter a target, some of the energy is reflected back and captured by the radar receiver. By measuring the time difference between the transmitted and received electromagnetic waves, the target's distance can be determined; and by processing and analyzing the echo signals, more information such as the target's speed and direction can be extracted.

[0003] In unmanned aerial vehicle (UAV) applications, the structural design of the radar search device directly affects target detection efficiency and mission execution effectiveness. Traditional radar systems are often fixedly installed on UAVs. When the UAV lands, it comes into contact with the ground, causing vibrations that can displace the radar antenna's mechanical structure. This can lead to the radar beam deviating from the target area, resulting in "scanning blind spots" or "coverage discontinuities." To reduce vibration and improve search efficiency, damping springs and damping pads have been developed. However, damping springs are only effective for specific frequencies of vibration. When the UAV's landing vibration frequency deviates, the spring exhibits nonlinear characteristics under large-amplitude vibrations, causing additional torsional displacement of the radar, increasing beam pointing deviation, and causing the antenna stabilization system to fail, resulting in intermittent loss of target echoes and a reduced search refresh rate. Damping pads are prone to aging and wear, requiring periodic replacement, which is inconvenient. Therefore, these solutions do not meet current requirements. To address this, we propose a radar search device for unmanned aerial vehicles. Utility Model Content

[0004] The purpose of this invention is to provide an unmanned aerial vehicle (UAV) radar search device to solve the problem mentioned in the background art, where conventional radars are often installed in a fixed manner when they are mounted on UAVs. When the UAV lands and comes into contact with the ground, it is prone to vibration, which causes the radar's mechanical structure to shift, causing the radar beam to deviate from the target area and resulting in a "scanning blind zone".

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] An unmanned aerial vehicle (UAV) radar search device includes an UAV and a radar. The UAV includes a streamlined fuselage, wings distributed at the top corners of the fuselage, and landing gear located at the bottom of both sides of the fuselage. The radar is embedded inside the fuselage and is connected to the fuselage through a dual-stage shock absorption structure. An auxiliary search antenna is integrally connected to the fuselage located on top of the radar and is connected to the fuselage through a drive component.

[0007] Preferably, the dual-stage shock absorption structure includes a first connecting shock absorber and a second landing shock absorber. The first connecting shock absorber is symmetrically located on both sides of the radar inside the fuselage. Each first connecting shock absorber includes a cylinder, a piston rod, a connecting handle, and a rubber ring. The cylinder has a hollow structure with an open bottom. The piston rod is movably located inside the cylinder. The rubber ring is located at the top of the piston rod inside the cylinder. The outer circumferential wall of the rubber ring slides against the inner circumferential wall of the cylinder. An exhaust column is connected through the top of the cylinder. The bottom of the piston rod is connected to the fuselage through the connecting handle.

[0008] Preferably, the second landing shock absorber includes an electromagnet, a mounting base, and a magnet block. The magnet block is attached to the bottom of the mounting base, and a locking block is provided on the top of the mounting base near the outer wall of the surrounding area. The electromagnet is located directly below the magnet block and connected to the fuselage. The electromagnet is electrically connected to the control equipment inside the unmanned aerial vehicle through a wire.

[0009] Preferably, the bottom of the radar has slots that engage with the card block.

[0010] Preferably, the outer walls on both sides of the radar are connected to the inner walls of the two cylindrical columns.

[0011] Preferably, the driving component includes a driving shaft and a driving motor. The driving shaft is connected through the auxiliary search antenna, and both ends of the driving shaft are connected to the fuselage through bearing seats. The output end of the driving motor is connected to one end of the driving shaft.

[0012] This utility model has the following beneficial effects:

[0013] 1. The combination of the cylindrical tube, rubber ring, and piston rod in this application forms an air damping buffer, which avoids the problem of beam pointing deviation caused by high-frequency vibration of the antenna during flight, thus affecting the search.

[0014] 2. A dynamic suspension buffer is set up. When the drone lands, the electromagnet is energized and generates a levitation force with the magnetic block. The magnetic levitation gap absorbs the impact energy and attenuates the impact acceleration generated by the ground collision. The non-contact magnetic levitation design avoids the aging and wear of traditional pads.

[0015] 3. The auxiliary search antenna is flipped via a drive shaft to form a composite detection array with the embedded radar, thereby improving search efficiency. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall design of this utility model.

[0017] Figure 2 This is a side view of the present invention.

[0018] Figure 3 This is a side view of the connection structure between the radar and the dual-stage shock absorption structure of this utility model.

[0019] Figure 4 This is a schematic diagram of the auxiliary search antenna and driving component of this utility model.

[0020] Figure 5 This is a block diagram of the control device connection of this utility model.

[0021] In the diagram: 1. Unmanned aerial vehicle; 11. Fuselage; 12. Wing; 13. Landing gear; 2. Radar; 21. Slot; 3. Auxiliary search antenna; 31. Drive shaft; 32. Drive motor; 4. First connecting shock absorber; 41. Column; 42. Piston column; 43. Connecting handle; 44. Rubber ring; 45. Exhaust column; 5. Second landing shock absorber; 51. Electromagnet; 52. Mounting base; 521. Locking block; 53. Magnet block. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] Please see the appendix Figure 1-5As shown, an unmanned aerial vehicle (UAV) radar search device includes an UAV 1 and a radar 2. The UAV 1 includes a streamlined fuselage 11, wings 12 distributed at the top corners of the fuselage 11, and landing gear 13 located at the bottom of both sides of the fuselage 11. The streamlined fuselage 11 reduces aerodynamic drag compared to a traditional rectangular fuselage, increasing the UAV's cruise speed and time, and improving stability. The streamlined fuselage 11 adopts a NACA airfoil section, with a leading-edge arc combined with an auxiliary search antenna 3 to form a leading-edge arc and a sharp trailing-edge design, shifting the airflow separation point backward and reducing aerodynamic drag compared to a traditional rectangular fuselage. When the UAV cruises, the streamlined design reduces engine power consumption, increasing the cruise speed and extending the endurance with the same amount of power. The radar 2 is embedded inside the fuselage 11. The radar 2 is connected to the fuselage 11 via a dual-stage shock absorption structure. An auxiliary search antenna 3 is integrally connected to the fuselage 11 located on top of the radar 2. The auxiliary search antenna 3 is connected to the fuselage 11 via a drive component. By setting up the auxiliary search antenna 3, the search blind zone is reduced and the search efficiency is improved. The auxiliary search antenna 3 is electrically connected to the radar 2 via a wire. The drive component includes a drive shaft 31 and a drive motor 32. The drive shaft 31 passes through and is connected to the auxiliary search antenna 3. Both ends of the drive shaft 31 are connected to the fuselage 11 via bearing seats. The output end of the drive motor 32 is connected to one end of the drive shaft 31. When auxiliary radar search is required, the drive motor 32 controls the auxiliary antenna 3 to reciprocate at a speed of 5° / s, which improves the search efficiency compared to the traditional single-antenna solution.

[0024] The auxiliary search antenna 3 of this application is integrated and connected to the top of the fuselage 11 (see attached document). Figure 1 and 2 The auxiliary search antenna 3 structure on the top of the fuselage 11 has a leading edge arc and a sharp trailing edge design that moves the airflow separation point backward. Compared with the traditional rectangular fuselage, it reduces aerodynamic drag. When the UAV is cruising, the streamlined design can reduce engine power consumption and increase the cruising speed with the same amount of power.

[0025] When auxiliary search is required, the drive motor 32 controls the drive shaft 31 to drive the auxiliary antenna 3 to reciprocate within a range of ±135° at a speed of 5° / s, forming a composite detection perspective with the fixed-pointing main radar 2. When the main radar deviates from its pointing direction due to vibration, the auxiliary antenna covers the blind zone by adjusting its angle in real time. After data fusion, multiple dynamic targets can be tracked simultaneously. The hardware-level redundancy between the auxiliary antenna and the main radar 2 improves the success rate of the system in complex environments, making it suitable for high-reliability scenarios such as emergency rescue and military reconnaissance.

[0026] Please see the appendix Figure 1 , 3As shown in Figures 4 and 5, the dual-stage damping structure includes a first connecting damper 4 and a second landing damper 5. The radar 2, through the mechanical-electromagnetic synergy of the first connecting damper 4 and the second landing damper 5, forms a full-scenario damping solution of "flight vibration suppression + landing impact buffering." The first connecting damper 4 is symmetrically located on both sides of the radar 2 inside the fuselage 11. Each first connecting damper 4 includes a cylinder 41, a piston rod 42, a connecting handle 43, and a rubber ring 44. The cylinder 41 has a hollow structure with an open bottom. The piston rod 42 is movably located inside the cylinder 41. The rubber ring 44 is located at the top of the piston rod 42 inside the cylinder 41. The outer circumferential wall of the rubber ring 44 slides against the inner circumferential wall of the cylinder 41. An exhaust column 45 is connected through the top of the cylinder 41. The bottom of the piston rod 42 is connected to the fuselage 11 via a connecting handle 43. The first connecting shock absorber 4 is symmetrically distributed on both sides of the radar 2, and the second landing shock absorber 5 is integrated into the bottom of the radar and connected to the inner wall of the piston rod 42, forming a three-dimensional shock absorption network. This reduces the space occupied by the piston rod compared to traditional multi-component solutions. When the UAV vibrates during flight, the piston rod 42 reciprocates within the cylinder 41. Air inside the cylinder 41 enters and exits through the exhaust column 45, forming viscous drag and reducing the vibration of the radar 2. The rubber ring 44 provides elastic buffering during small-amplitude vibrations and generates nonlinear damping due to molecular chain friction during large-amplitude vibrations, adapting to different vibration intensities. Limiting blocks are provided on the inner walls of both sides of the bottom of the cylinder 41 to prevent the piston rod 42 from coming out of the cylinder 41, ensuring the connection between the radar 2 and the fuselage 11 (see appendix). Figure 3 (As shown).

[0027] The first connecting shock absorber 4 is symmetrically distributed on both sides of the fuselage 11 with the radar 2 as the center. Each shock absorber is fixed to the inner wall of the fuselage through the connecting handle 43. The top of the column 41 is rigidly connected to the radar shell, forming a three-dimensional shock absorption structure of "support on both sides + buffer at the top". Limiting blocks (5mm thick, made of polyoxymethylene POM) are set on the inner walls of both sides at the bottom of the column 41. When the piston column 42 moves downward, the limiting block abuts against the bottom boss of the piston column to prevent it from coming out of the column and ensure the reliability of the connection between the radar and the fuselage.

[0028] The second landing shock absorber 5 includes an electromagnet 51, a mounting base 52, and a magnet 53. The magnet 53 is attached to the bottom of the mounting base 52. A locking block 521 is located on the top of the mounting base 52 near its outer perimeter. The electromagnet 51 is located directly below the magnet 53 and connected to the fuselage 11. The electromagnet 51 is electrically connected to the control equipment inside the unmanned aerial vehicle 1 via a wire. The bottom perimeter of the radar 2 has slots 21 that engage with the locking block 521. The outer walls on both sides of the radar 2 are connected to the inner walls of two cylindrical tubes 41. When the unmanned aerial vehicle 1 needs to land and make contact with the ground, the controller energizes the electromagnet 51, causing the electromagnet 51 to generate... The magnetic force causes the magnet block 53 to float upwards. While floating, the magnet block 53 is connected to the mounting base 52, which is connected to the radar 2. At this time, the radar 2 is also suspended. When the radar 2 floats upwards, it drives the column cylinder 41 to move upwards for shock absorption. When the electromagnet 51 is deactivated and the electromagnetic force disappears, the radar 2 drives the column cylinder 41 to slowly move downwards outside the piston column 42, ensuring the connection between the radar 2 and the unmanned aerial vehicle 1. The dual-stage shock absorption structure, through the integration of mechanical damping and electromagnetic levitation technologies, breaks through the frequency domain limitations and lifespan bottlenecks of traditional shock absorption schemes, providing an innovative solution for UAV radar that balances efficiency, reliability, and cost.

[0029] 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.

[0030] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. An unmanned aerial vehicle (UAV) radar search device, comprising an UAV (1) and a radar (2), characterized in that: The unmanned aerial vehicle (1) includes a streamlined fuselage (11), wings (12) distributed at the top corners of the fuselage (11), and landing gear (13) located at the bottom of both sides of the fuselage (11). The radar (2) is embedded inside the fuselage (11) and is connected to the fuselage (11) through a dual-stage shock absorption structure. An auxiliary search antenna (3) is integrally connected to the fuselage (11) located on top of the radar (2) and is connected to the fuselage (11) through a drive component.

2. The radar search device for unmanned aerial vehicles according to claim 1, characterized in that: The dual-stage shock absorption structure includes a first connecting shock absorber (4) and a second landing shock absorber (5). The first connecting shock absorber (4) is symmetrically located on both sides of the radar (2) inside the fuselage (11). Each first connecting shock absorber (4) includes a cylinder (41), a piston rod (42), a connecting handle (43), and a rubber ring (44). The cylinder (41) is hollow inside with an open bottom. The piston rod (42) is movably located inside the cylinder (41). The rubber ring (44) is located at the top of the piston rod (42) inside the cylinder (41). The outer circumferential wall of the rubber ring (44) slides against the inner circumferential wall of the cylinder (41). An exhaust column (45) is connected through the top of the cylinder (41). The bottom of the piston rod (42) is connected to the fuselage (11) through the connecting handle (43).

3. The radar search device for unmanned aerial vehicles according to claim 2, characterized in that: The second landing shock absorber (5) includes an electromagnet (51), a mounting base (52), and a magnet (53). The magnet (53) is attached to the bottom of the mounting base (52). A locking block (521) is provided on the top of the mounting base (52) near the outer wall. The electromagnet (51) is located directly below the magnet (53) and connected to the fuselage (11). The electromagnet (51) is electrically connected to the control equipment inside the unmanned aerial vehicle (1) through a wire.

4. The radar search device for unmanned aerial vehicles according to claim 3, characterized in that: The radar (2) has slots (21) at its bottom perimeter that engage with and connect to the card block (521).

5. The radar search device for unmanned aerial vehicles according to claim 4, characterized in that: The outer walls on both sides of the radar (2) are connected to the inner walls of the two cylindrical tubes (41).

6. The radar search device for unmanned aerial vehicles according to claim 1, characterized in that: The driving component includes a drive shaft (31) and a drive motor (32). The drive shaft (31) is connected to the auxiliary search antenna (3) through it. Both ends of the drive shaft (31) are connected to the fuselage (11) through bearing seats. The output end of the drive motor (32) is connected to one end of the drive shaft (31).

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