Detecting and shooting integrated fixed wing patrol aircraft

Abstract

The invention belongs to the technical field of patrol airplanes, and discloses a fixed-wing patrol aircraft integrating detection and fighting, which comprises an aircraft body, horizontal wings are respectively arranged on the left side and the right side of the aircraft body, a first vertical wing is fixedly arranged above the aircraft body, a power propeller assembly is arranged on the wings, and an empennage assembly is arranged at the tail end of the aircraft body; a first patrolling gun is arranged between the vertical wing and the horizontal wing on one side of the fuselage, and a second patrolling gun is arranged on the opposite side of the fuselage. According to the unmanned aerial vehicle, carrying of the patrolling gun is achieved, the stable flight attitude can be rapidly recovered after the gun is started, safety and maneuverability are improved, the hiding effect at night is achieved, and detection and shooting are integrated.

Description

Technical Field

[0001] This invention relates to the field of patrol aircraft technology, and specifically to a fixed-wing patrol aircraft that integrates reconnaissance and strike capabilities. Background Technology

[0002] As drone technology continues to develop, its application areas are also gradually expanding. However, existing armed drone technology has significant shortcomings in terms of maneuverability and safety. Currently, these drones are mostly used in agriculture or civilian fields, such as for pesticide spraying or netting. The recoil generated after firing the guns carried in these applications is relatively small, so the drone's ability to adjust its maneuverability after firing is also limited. This limitation makes it difficult for existing armed drones to meet the stringent requirements of carrying military firearms. Military firearms typically have greater firepower and recoil, and existing drones cannot quickly regain a stable flight attitude after firing, thus affecting combat effectiveness and mission success rate.

[0003] Chinese Patent Publication No. CN211618090U, Publication Date: October 2, 2020, discloses a Chinese patent entitled "Aerial Capture Net-Throwing Drone," which includes a drone body and multiple net-throwing guns. A shell is fixedly connected to the bottom of the drone body, and a rotating rod is installed inside the shell. One end of the rotating rod penetrates the inner wall of the shell and extends outward. The rotating rod is rotatably connected to the shell via a bearing. A rotating plate is fixedly connected to the outer end of the rotating rod. The bottom of the rotating plate is fixedly connected to multiple net-throwing guns, which are evenly distributed. A bevel gear is fixedly sleeved on the rod wall, and the bevel gear is located inside the shell. A drive motor is fixedly installed inside the shell, and a half-bevel gear is fixedly sleeved on the output end of the drive motor. The half-bevel gear and the bevel gear mesh with each other. This drone can only be used for civilian purposes and cannot be used for loitering with powerful military firearms. Summary of the Invention

[0004] This invention provides a fixed-wing patrol aircraft that integrates reconnaissance and strike capabilities. By setting a first vertical wing and a power propeller assembly, it can mount a loitering gun, which can quickly restore a stable flight attitude after firing, thereby improving safety and achieving integrated reconnaissance and strike capabilities.

[0005] A further objective of this invention is to enable vertical takeoff and landing by setting a tail fin assembly, which supports the drone fuselage while adjusting its flight.

[0006] A further objective of this invention is to improve maneuverability by setting up centrally symmetrical wing components, so that the aircraft does not need to distinguish between up, down, left, and right during flight.

[0007] A further objective of this invention is to use stealth powder to absorb radar waves, thereby converting radar electromagnetic waves into heat energy and achieving a stealth effect at night.

[0008] To achieve the above objectives, the present invention adopts the following technical solution: a fixed-wing patrol aircraft integrating reconnaissance and strike capabilities, comprising a fuselage, with horizontal wings respectively provided on the left and right sides of the fuselage, a first vertical wing fixedly provided above the fuselage, and a tail assembly provided at the tail end of the fuselage; a first loitering gun is provided between the vertical wing and one side of the horizontal wing on the fuselage, and a second loitering gun is provided on the opposite side.

[0009] Preferably, a second vertical wing is fixedly mounted below the fuselage, and one end of the first and second vertical wings are fixedly connected to the upper and lower surfaces of the fuselage, respectively. The first and second vertical wings are symmetrically arranged.

[0010] Preferably, the first vertical wing, the second vertical wing, and several horizontal wings are arranged perpendicularly to each other, forming a cross-shaped symmetrical structure relative to the fuselage. Two horizontal wings are preferably arranged symmetrically along the fuselage's axis of symmetry. By using centrally symmetrical wing components, it is possible to perform special maneuvers without distinguishing between up, down, left, and right during flight. This improves maneuverability, enables complex maneuvers, and allows for adaptation to more complex flight environments and mission requirements.

[0011] Preferably, the first and second loitering munitions are mounted on a gun mount on the fuselage, with their muzzles facing opposite directions. The muzzle of the first loitering munition faces the nose, and the muzzle of the second loitering munition faces the tail assembly. An ammunition clip is housed within the gun mount. This configuration allows the UAV to flexibly adjust its firing direction according to mission requirements, eliminating the need for the entire UAV to turn to aim at the target, thus improving response speed. Simultaneously, the ammunition clip design within the gun mount facilitates ammunition replenishment and management, enhancing combat efficiency. Gyroscopes are located below the first and second loitering munitions, and shock absorbers are installed between the loitering munitions and the gun mount.

[0012] Preferably, the first vertical wing, the second vertical wing, and several horizontal wings are equipped with propeller assemblies at their midsections, with the propeller assemblies located at the leading edge of the wings and facing the nose. This arrangement of the propeller assemblies provides stronger power support while optimizing airflow distribution, further enhancing flight performance and maneuverability.

[0013] Preferably, the fuselage has a bullet-shaped nose and streamlined wings. Each wing has a first aileron near the fuselage end and a second aileron near the wingtip. The fuselage employs a cylindrical structure, effectively increasing the internal payload compartment volume. The first and second ailerons are used to control the UAV's deflection. The streamlined design effectively reduces air resistance, improving flight speed and energy efficiency; the ailerons enhance precise control of flight attitude and improve flight stability.

[0014] Preferably, the powered propeller assembly is located at the middle section of the leading edge of the wing, and includes a drive unit. The drive unit is connected to a first outer tube and a second outer tube respectively via a connecting plate. The inner wall of the first outer tube is provided with internal threads. The powered propeller assembly includes a propeller, which is connected to the drive unit. The first outer tube has a threaded tube inside, one end of which is connected to a drive motor. The second outer tube has a first inner tube inside.

[0015] Preferably, the bottom end of the first inner tube is connected to the connecting shaft, one end of the connecting shaft is fixed to the connector, and the threaded tube passes through the connector and is connected to the servo motor. The threaded tube and the connector are slidably connected. The body is coated with a stealth material, which is made by adding magnetic powder to the first foaming liquid and the second foaming liquid respectively, and filling them into the plastic model foaming machine. A retrieval hook is connected to the tail end of the body, and the retrieval hook is equipped with a locking lever.

[0016] Preferably, the mounting slot is located on the leading edge of the wing, and the mounting slot has several first mounting holes. The second mounting holes correspond one-to-one with the first mounting holes, allowing the mounting bracket to be fixed within the mounting slot. This design ensures that the mounting bracket can be securely installed on the wing, improving the stability and reliability of the structure, while also facilitating maintenance and component replacement.

[0017] Preferably, the tail assembly includes several tail fins, one end of which is fixedly connected to the fuselage. Control rudders are located on the side of the tail fins closest to the fuselage. The tail fins are symmetrically arranged along the center of the fuselage and can act as supports during drone landing. The control rudders control the drone's flight. The symmetrical arrangement of the tail fins and their support function enhance the drone's takeoff and landing stability, while the control rudders can precisely adjust the flight direction and attitude, improving flight safety and maneuverability.

[0018] Beneficial effects: By setting up a first vertical wing and a power propeller assembly, the present invention can effectively carry a loitering gun and quickly restore a stable flight attitude after firing, which significantly improves the maneuverability and safety of the UAV, enabling it to better adapt to the needs of complex missions.

[0019] This invention also enables the UAV to achieve vertical takeoff and landing by incorporating a tail fin assembly. The tail fin assembly not only provides excellent support for the UAV fuselage but also allows for precise adjustment of flight attitude during flight, further enhancing the UAV's operability and stability. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0021] Figure 2 This is a cross-sectional view of the power propeller assembly of the present invention.

[0022] Figure 3 for Figure 2Enlarged view of point A.

[0023] Figure 4 This is a front view of the present invention.

[0024] Figure 5 This is a rear view of the present invention.

[0025] Figure 6 This is a diagram showing the recycling status of the present invention.

[0026] Figure 7 This is a cross-sectional view of the gun mount of the present invention.

[0027] Figure 8 This is a schematic diagram of the structure of the recovery hook of the present invention.

[0028] Reference numerals: 1: Fuselage; 2: Nose; 3: Horizontal wing; 4: First vertical wing; 4.1: First aileron; 4.2: Second aileron; 5: Second vertical wing; 6: Power propeller assembly; 6.1: Propeller; 6.2: Mounting bracket; 6.3: Second mounting hole; 6.4: Connecting plate; 6.5: Drive unit; 6.6: First outer tube; 6.7: Second outer tube; 6.8: Threaded tube; 6.9: First inner tube; 6.10: Connector; 6.11: Connecting shaft; 6.12: Bevel gear; 6.13: Servo motor; 7: Tail assembly; 7.1: Tail; 7.2: Control rudder; 8: Recovery hook; 8.1: Anti-lock lever; 9: Recovery rack; 10: Electric elastic band; 11: Gun mount; 12: Gyroscope; 13: Shock absorber. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, 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, 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.

[0030] In the field of modern unmanned aerial vehicle (UAV) applications, vertical takeoff and landing (VTOL) UAVs are widely used in military and reconnaissance fields due to their flexible takeoff and landing capabilities. However, traditional VTOL UAVs often face problems such as loss of attitude and insufficient maneuverability when carrying weapons to perform missions. The weapon-equipped VTOL UAV proposed in this invention effectively solves these problems through innovative designs in wing layout, weapon mounting, and tail fin structure 7.1.

[0031] like Figure 1-8As shown, this vertical takeoff and landing (VTOL) UAV uses the fuselage 1 as its core carrier, and its overall layout is meticulously designed around its functional implementation. The horizontal wings 3, symmetrically arranged on both sides of the fuselage 1, resemble the outstretched wings of a bird, providing basic lift support for the UAV. The first vertical wing 4, fixedly mounted on top of the fuselage 1, and the second vertical wing 5, symmetrically arranged below the fuselage 1, together construct a unique three-dimensional wing structure. These two sets of vertical wings are tightly connected at one end to the upper and lower surfaces of the fuselage 1, forming a stable support system. Furthermore, the first vertical wing 4 and the second vertical wing 5 are tilted towards the tail assembly 7. This tilt angle is not arbitrary but was determined through extensive aerodynamic simulation and wind tunnel testing. During flight, the tilted wings guide airflow more smoothly across the surface of the fuselage 1, reducing the generation of air vortices and thus lowering drag. Simultaneously, the tilted wing structure alters the aerodynamic center distribution of the UAV, enabling it to maintain better stability during flight and quickly recover a stable flight state even when encountering airflow disturbances or performing complex maneuvers.

[0032] like Figure 1 As shown, from an overall structural perspective, the first vertical wing 4, the second vertical wing 5, and the two horizontal wings 3 are perpendicular to each other, together forming a wing assembly that is cross-symmetrical with respect to the fuselage 1. This centrally symmetrical layout endows the UAV with unique flight characteristics. In traditional UAV flight, it is necessary to strictly distinguish between up, down, left, and right directions, which limits the adjustment of flight attitude. However, due to the centrally symmetrical wing design of this invention, the UAV does not need to consciously distinguish directions during flight. Whether flying forward, backward, or rolling or sideways, the UAV can achieve various special maneuvers using the same control logic. For example, when performing reconnaissance missions, the UAV can flexibly maneuver through narrow gaps in buildings without the need for complex turning operations like traditional UAVs; when encountering emergencies requiring a rapid change of flight direction, it can quickly complete translation, rotation, and other maneuvers, greatly improving maneuverability and enabling it to adapt to complex flight environments such as urban high-rises and mountain valleys, as well as diverse mission requirements.

[0033] In terms of weaponry, the UAV has a first loitering gun positioned between its vertical wing and one horizontal wing 3, and a second loitering gun mounted on the opposite side. These two loitering guns are fixed to a specially designed gun mount 11 on the fuselage 1. The mount 11 is made of a high-strength, lightweight alloy material, ensuring sufficient strength to support the weapons while minimizing the overall weight of the UAV. The muzzle of the first loitering gun faces the nose 2, while the muzzle of the second loitering gun points towards the tail assembly 7; their muzzle directions are opposite. This unique configuration allows the UAV to flexibly adjust its firing direction based on the target's location during missions. When a target is detected ahead, the first loitering gun can be used directly for firing; if a threat appears from behind, the second loitering gun can quickly take effect. Compared to traditional UAVs that require overall aircraft turning to aim at the target, this invention significantly improves response speed. Taking military reconnaissance and strike missions as an example, traditional UAVs, after detecting targets in the rear, need to adjust their fuselage direction before aiming and firing. This process often results in missing the optimal attack opportunity. However, the UAV of this invention can directly fire using its second loitering gun, enabling an instantaneous response to the target and effectively improving combat efficiency. Furthermore, the gun mount 11 is internally designed with a dedicated ammunition clip. The ammunition clip employs a modular design for easy and rapid ammunition replacement and replenishment. Before mission execution, operators can load different types and quantities of ammunition into the ammunition clip according to mission requirements. When ammunition is depleted, the ammunition clip can be quickly replaced, ensuring the UAV maintains continuous combat capability.

[0034] The tail assembly 7 plays a crucial role in the vertical takeoff and landing (VTOL) and flight adjustment of the UAV. Mounted at the tail end of the fuselage 1, its structural design combines support and adjustment functions. During VTOL, the tail assembly 7 adjusts its angle, working in conjunction with the lift generated by the wings, to help the UAV achieve stable vertical takeoff and landing. When the UAV needs to take off, the tail assembly 7 provides additional support to the fuselage 1, ensuring a smooth vertical ascent from the ground. During landing, the tail assembly 7 adjusts in real time according to the flight attitude, slowing the descent and ensuring a safe landing. In flight, the tail assembly 7 acts as both a "steering wheel" and a "stabilizer" for the UAV. When the UAV needs to change direction, the tail assembly 7 generates aerodynamic torque by deflecting the control rudder 7.2, propelling the fuselage 1 to turn. When the UAV encounters airflow disturbances and experiences attitude deviation, the tail assembly 7 can quickly sense and adjust, generating a counter-torque by changing its angle, allowing the UAV to regain a stable flight attitude. For example, when flying in windy weather, the tail assembly 7 continuously monitors the drone's attitude changes and adjusts its angle in a timely manner to counteract the wind's impact on the drone, ensuring it flies along the predetermined route. In actual application scenarios, this gun-equipped vertical take-off and landing drone demonstrates powerful performance advantages. In military-grade combat simulation tests, facing simulated fast-moving enemy targets, traditional drones, due to insufficient maneuverability, struggle to quickly adjust their attitude for aiming and firing in complex terrain, resulting in a hit rate of only about 30%. However, the drone of this invention, with its highly maneuverable centrally symmetrical wings, can rapidly traverse complex mountainous environments and quickly adjust its firing angle, increasing its hit rate to over 70%. Regarding attitude recovery after firing, traditional weapon-equipped drones often experience severe attitude loss of control at the moment of firing due to recoil, requiring a considerable amount of time to recover stable flight, during which time they are highly vulnerable to enemy attack. The drone of this invention, through the stabilizing structure formed by the first vertical wing 4, the second vertical wing 5, and the horizontal wing 3, as well as the real-time adjustment of the tail assembly 7, can quickly recover a stable flight attitude after firing. Test data shows that the drone's attitude recovery time after firing is reduced by more than 60% compared to traditional drones, significantly improving its safety. In civilian applications, such as urban aerial reconnaissance and forest fire monitoring, this drone also performs exceptionally well. Its unique centrally symmetrical wing design allows it to fly flexibly in urban environments filled with tall buildings, completing precise reconnaissance missions; its vertical takeoff and landing capability eliminates the need for runways, enabling rapid takeoff and landing in confined spaces and adapting to various complex environments.

[0035] This invention, a vertical takeoff and landing (VTOL) drone equipped with a gun, successfully achieves stable mounting of a loitering gun, rapid attitude recovery, and high maneuverability through innovative wing layout, weapon mounting method, and tail fin 7.1 structural design. From the aerodynamic optimization design of the wings to the flexible layout of the weapon system and the precise adjustment of the tail fin assembly 7, each design element is closely focused on improving the drone's performance, effectively solving the technical challenges of traditional drones in relevant applications. Whether in military operations or civilian fields, this drone demonstrates enormous application potential and broad development prospects, providing new ideas and directions for the innovative development of drone technology.

[0036] like Figure 1 and Figure 2 As shown, propeller assemblies 6 are installed at the mid-section of the first vertical wing 4, the second vertical wing 5, and the horizontal wing 3, significantly enhancing the UAV's power output through a distributed propulsion system. When each propeller assembly 6 operates, the thrust generated not only directly propels the UAV forward but also creates an ordered airflow field on the wing surface. The propellers 6.1 located at the wing's leading edge accelerate the air in front and deliver it along the wing surface during rotation, optimizing the pressure distribution on the upper and lower wing surfaces and effectively increasing the lift coefficient. Simultaneously, when multiple propellers 6.1 work together, the resulting airflow coordinates, reducing eddies and turbulence on the wing surface and further lowering drag. This propulsion layout allows the UAV to maintain strong power output even when carrying additional payloads such as loitering guns. Furthermore, at the moment of firing, each propeller 6.1 can adjust its rotation speed in real time to quickly counteract the recoil's impact on flight attitude, ensuring the UAV rapidly recovers stable flight and significantly improving maneuverability and safety in complex mission environments.

[0037] like Figure 1 As shown, the fuselage 1's external design also reflects a dual consideration of aerodynamic performance and internal space. The nose 2 adopts a bullet-shaped design; this rounded yet sharp contour effectively guides airflow smoothly around the fuselage 1, reducing drag caused by air impact. The main body of the fuselage 1 adopts a cylindrical structure. Compared to traditional flat or angular designs, the cylindrical curved surface allows airflow to adhere more evenly to the surface of the fuselage 1, reducing the probability of vortex formation. At the same time, the cylindrical structure has a significant advantage in utilizing internal space; its regular inner walls provide maximum volume for the payload compartment, providing ample space for installing reconnaissance equipment, ammunition resupply devices, or other mission payloads.

[0038] The wing features a streamlined design, with a profile that gradually narrows from near the fuselage 1 to the wingtip, perfectly matching the optimal airfoil curve in aerodynamics. This shape allows airflow to separate and reattach with minimal energy loss as it passes over the wing, significantly reducing induced drag. In the wing's control structure, a first aileron 4.1 near the fuselage 1 and a second aileron 4.2 near the wingtip form a hierarchical control system. When the UAV needs to make small attitude adjustments, the first aileron 4.1 acts first, generating a small aerodynamic torque by changing the local wing surface angle for precise fine-tuning. For large-angle turns or rolls, the second aileron 4.2 works in conjunction with the first aileron 4.1, with the two combining different angles to generate greater control force, ensuring the UAV can respond quickly to control commands. This dual aileron design not only enhances the precision of flight attitude control but also significantly improves flight stability by automatically adjusting the ailerons to correct attitude deviations when encountering airflow disturbances.

[0039] like Figure 2 As shown, the internal structure design of the propeller assembly 6 emphasizes a balance between stability and maneuverability. The propeller 6.1 is mounted in a mounting slot on the leading edge of the wing via a mounting bracket 6.2. The mounting bracket 6.2 adopts a rectangular frame structure with one open end. This design ensures the stable installation of the propeller 6.1 while facilitating disassembly and maintenance. This structure ensures that the propeller 6.1 can withstand various aerodynamic forces and vibrations during flight, while also providing convenience for subsequent maintenance and repair, enabling technicians to quickly inspect, replace, or adjust the propeller 6.1.

[0040] The four corners of the fixed bracket 6.2 are reinforced and tightly connected to the first mounting holes in the wing mounting slot using high-strength bolts. This connection method not only withstands significant mechanical stress but also ensures stability in complex flight environments. Simultaneously, several second mounting holes 6.3 on the fixed bracket 6.2 match corresponding holes on the wing, further enhancing the reliability of the connection. This multi-point connection design makes the entire propeller assembly 6 more firmly bonded to the wing, effectively reducing loosening or damage caused by vibration or external impact, thereby extending the assembly's service life and improving flight safety.

[0041] In the power system layout of drones, the design of the propeller assembly is crucial. For example... Figure 1-8As shown, the propeller assembly is precisely positioned at the mid-section of the wing's leading edge. This placement was carefully considered in terms of aerodynamics, maximizing the propeller's thrust while optimizing airflow distribution across the wing surface. The core component of this propeller assembly is the drive unit, which serves as the power source. It connects to the first outer tube 6.6 and the second outer tube 6.7 via connecting plates 6.4, forming a stable power transmission architecture. Notably, the inner wall of the first outer tube 6.6 is meticulously machined with internal threads; this detail foreshadows the connection and functionality of subsequent components.

[0042] The propeller in the power propeller assembly is directly connected to the drive unit, forming the power output terminal. Inside the first outer tube 6.6, there is a threaded tube 6.8, one end of which is tightly connected to the drive motor. The rotational power generated by the drive motor is transmitted and converted through the threaded tube 6.8. Inside the second outer tube 6.7, there is a first inner tube 6.9. Unlike the threaded tube 6.8, the first inner tube 6.9 is an unthreaded tube, and the two complement each other in structure. The bottom end of the first inner tube 6.9 is connected to the connecting shaft 6.11, one end of which is firmly fixed to the connector 6.10, providing reliable support and connection for the entire assembly. The threaded tube 6.8 passes through the connector 6.10 and is connected to the bevel gear 6.12 of the servo motor 6.13. The threaded tube 6.8 and the connector 6.10 are connected by a sliding connection. This connection method ensures that the threaded tube 6.8 can rotate freely while preventing it from deviating during power transmission.

[0043] To enhance structural strength, two reinforcing tubes connect the first outer tube 6.6 and the second outer tube 6.7, acting as sturdy pillars to ensure the stability of the entire propeller assembly during high-speed operation. Both the first outer tube 6.6 and the second outer tube 6.7 are designed with open-end tube structures, facilitating the installation and maintenance of internal components. When the servo motor 6.13 starts working, its rotational power is transmitted to the threaded tube 6.8 via the bevel gear 6.12, causing the threaded tube 6.8 to rotate. Due to the interlocking of the internal threads of the threaded tube 6.8 and the inner wall of the first outer tube 6.6, the rotation of the threaded tube 6.8 is converted into axial linear motion, causing the connecting tube to expand and contract. The expansion and contraction of the connecting tube further drives the expansion and contraction of the connecting plate 6.4, ultimately achieving propeller extension and contraction control. Through precise adjustment of the propeller position, the UAV can change its attitude according to flight requirements. Whether performing turning, pitching, or rolling maneuvers, the powered propeller assembly responds quickly, ensuring stable flight of the UAV under various complex conditions.

[0044] In terms of stealth performance, the stealth material coated on the fuselage plays a crucial role. This stealth material is made by adding magnetic powder to a first foaming liquid and a second foaming liquid, respectively, and then filling them into a plastic mold through a specific process. Type A and Type B foaming liquids, as base materials, each possess unique physicochemical properties. The addition of magnetic powder significantly alters the material's properties. The magnetic powder endows the material with the ability to absorb radar waves. The principle is that when electromagnetic waves emitted by radar come into contact with the fuselage surface coated with this material, they interact with the magnetic powder. The energy of the electromagnetic waves is absorbed by the material and converted into heat energy, thus preventing radar wave reflection. This stealth effect is particularly prominent in nighttime operations. There is no image, infrared, or electromagnetic wave reflection, and it also effectively prevents the electromagnetic radiation generated by the motors and batteries from being detected, making the drone virtually invisible to enemy detection equipment, greatly enhancing operational concealment and security.

[0045] The recovery device at the tail end of the fuselage is ingeniously designed and practical. The recovery hook 8, connected to the tail end of the fuselage, is a key component for drone recovery. The recovery hook 8 is equipped with a locking lever 8.1, one end of which is elastically hinged to the inner wall of the hook. This connection method allows the locking lever 8.1 to rotate flexibly within a certain range while providing a reliable locking effect under force. The recovery hook 8 itself is magnetic, cooperating with other components in the recovery system. During recovery, several electric rubber bands 10 are attached to magnetic ropes between recovery frames 9, which are connected to a motor. When the motor is powered on, the electric rubber bands 10 become magnetic, attracting the equally magnetic recovery hook 8. The two work closely together to achieve rapid recovery and fixation of the drone. The entire process is like two magnets precisely attracting each other, quickly and stably. When the drone needs to take off again, the motor is powered off, the electric rubber bands 10 lose their magnetism, and the magnetic force between them and the recovery hook 8 disappears. The drone can then easily detach from the recovery device and take off quickly. The entire recovery and release process is simple to operate and responds quickly.

[0046] The gyroscope 12 and shock absorber 13 installed beneath the first and second loitering lances play a crucial role in ensuring stable firing. The gyroscope 12, as a high-precision attitude detection element, uses its internal high-speed rotating rotor and corresponding sensors to detect minute angular changes in all directions in real time. When the drone is disturbed by airflow or performs maneuvers during flight, the gyroscope 12 quickly detects the change in the lance's attitude and transmits the signal to the control system. Based on the received signal, the control system precisely adjusts the position and angle of the loitering lance to ensure the muzzle remains stably pointed at the target, thus achieving stable sniping. To further enhance stability, shock absorbers 13 are installed between the loitering lance, the flat plate, and the lance mount 11. Four shock absorbers 13 are centrally symmetrically distributed at the four corners of the flat plate, and their core components are opposing repulsive magnets. This unique design utilizes the repulsive force between the magnets to effectively absorb and buffer vibrations from the drone's flight and recoil generated during firing without contact. When the gun body is vibrated, the distance between the repulsive magnets changes. The vibration energy is counteracted by adjusting the magnetic force, preventing the vibration from being transmitted to the gun body and affecting the shooting accuracy. This provides a stable firing platform for the loitering gun, ensuring that every shot hits the target accurately.

[0047] The tail assembly 7, a key component for the UAV's vertical takeoff and landing (VTOL) and flight control, is designed to balance versatility and stability. It consists of several tail fins 7.1 symmetrically distributed around the center of the fuselage 1. These tail fins 7.1 directly contact the ground during landing, acting as supports for the entire fuselage 1. The tail fins 7.1 are made of high-strength composite materials with an anti-slip surface treatment, ensuring reliable support under various terrain conditions. Each tail fin 7.1 is equipped with a control rudder 7.2 near the fuselage 1. Driven by a high-precision servo motor, the control rudder 7.2 can rotate flexibly at multiple angles. During VTOL, the control rudder 7.2 adjusts its angle according to commands from the flight control system, working in conjunction with the propeller assembly 6 on the wing to precisely control the UAV's takeoff and landing speed and attitude balance. During horizontal flight, the control rudder 7.2 functions like a control surface on a traditional aircraft, changing the aerodynamic torque of the tail fins 7.1 to achieve steering, pitch, and roll maneuvers. For example, when the drone needs to turn left, the control rudder 7.2 of the left tail fin 7.1 deflects to the left, generating an aerodynamic torque to the right, which propels the fuselage 1 to complete the turning action; when encountering crosswind interference, the control rudder 7.2 can automatically adjust its angle to generate a reverse torque to counteract the wind force, ensuring that the drone always maintains a stable flight attitude, which greatly improves flight safety and controllability.

[0048] In actual flight tests, the UAV of this invention demonstrated superior performance advantages. Compared with similar UAVs with conventional layouts, its distributed propeller assembly 6 increases the maximum flight speed by 30% and the range by 25% when carrying the same payload. Regarding aerodynamic optimization, the streamlined design combined with the twin aileron structure reduces air resistance by 20% during high-speed flight and maintains stable flight attitude even in gale-force winds (level 6), with attitude adjustment response time reduced to less than 0.3 seconds. The precise speed adjustment function of the propeller assembly 6 allows it to completely offset recoil and regain stable flight within 0.5 seconds during simulated gunfire tests. The tail assembly 7 also exhibits excellent vertical takeoff and landing and attitude control performance, achieving a 100% success rate for takeoff and landing in confined spaces, and keeping course deviation errors within a minimal range during autonomous flight navigation in complex terrain environments. These measured data fully verify the innovative advantages of this invention in power systems, aerodynamic design and flight control, laying a solid foundation for its wide application in military reconnaissance and strike, civilian surveying and inspection and other fields, and demonstrating its huge technical value and market potential.

[0049] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A fixed-wing patrol aircraft integrating reconnaissance and strike capabilities, characterized in that: The fuselage includes horizontal wings on the left and right sides, a first vertical wing fixed above the fuselage, a power propeller assembly on the wing, and a tail assembly at the tail end of the fuselage. The fuselage has a first loitering gun between the vertical wing and the horizontal wing on one side, and a second loitering gun on the opposite side.

2. The fixed-wing patrol aircraft integrating reconnaissance and strike capabilities according to claim 1, characterized in that, A second vertical wing is fixedly installed under the fuselage, and one end of the first vertical wing and the second vertical wing are fixedly connected to the upper and lower surfaces of the fuselage, respectively.

3. A fixed-wing patrol aircraft integrating reconnaissance and strike capabilities according to claim 2, characterized in that, The first vertical wing, the second vertical wing, and several horizontal wings are arranged perpendicularly to each other, forming a cross-shaped symmetrical structure relative to the fuselage.

4. A fixed-wing patrol aircraft integrating reconnaissance and strike capabilities according to claim 1, characterized in that, The first and second loitering guns are mounted on the gun mount on the fuselage. The muzzles of the first and second loitering guns face opposite directions. Gyroscopes are located below the first and second loitering guns, and shock absorbers are installed between the loitering guns and the gun mount.

5. A fixed-wing patrol aircraft integrating reconnaissance and strike capabilities according to claim 1 or 3, characterized in that, The propeller assembly is located at the middle of the leading edge of the wing and includes a drive unit. The drive unit is connected to the first outer tube and the second outer tube respectively through a connecting plate. The inner wall of the first outer tube is provided with internal threads.

6. A fixed-wing patrol aircraft integrating reconnaissance and strike capabilities according to claim 1, 2, or 3, characterized in that, The fuselage has a bullet-shaped nose and streamlined wings. The wings have a first aileron near the fuselage and a second aileron near the wingtip.

7. A fixed-wing patrol aircraft integrating reconnaissance and strike capabilities according to claim 5, characterized in that, The power propeller assembly includes a propeller, a connection between the propeller and a drive unit, a threaded tube inside a first outer tube, one end of which is connected to a drive motor, and a first inner tube inside a second outer tube.

8. A fixed-wing patrol aircraft integrating reconnaissance and strike capabilities according to claim 7, characterized in that, The bottom end of the first inner tube is connected to the connecting shaft, one end of the connecting shaft is fixed to the connector, the threaded tube passes through the connector and is connected to the servo motor, and the threaded tube and the connector are slidably connected.

9. A fixed-wing patrol aircraft integrating reconnaissance and strike capabilities according to claim 7, characterized in that, The body is coated with a stealth material, which is made by adding magnetic powder to the first foaming liquid and the second foaming liquid respectively, and filling the plastic model into the foaming machine.

10. A fixed-wing patrol aircraft integrating reconnaissance and strike capabilities according to claim 1, characterized in that, The tail assembly includes several tail fins, one end of which is fixedly connected to the fuselage. Control rudders are located on the side of the tail fins near the fuselage. A recovery hook is connected to the tail end of the fuselage, and a locking lever is provided on the recovery hook.

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