A modular impact interception device for assembly on a drone

Abstract

This invention discloses a modular impact interception device for use on unmanned aerial vehicles (UAVs), comprising a launcher ram, a loading mechanism, a rebound launch mechanism, a streamlined outer shell, and a launcher mounting chassis, employing a modular design. The launcher ram has a wedge-shaped armor-piercing section at its front end and a magnetic suction device and auxiliary holes at its bottom, allowing for quick replacement in conjunction with the loading mechanism. The rebound launch mechanism achieves precise linkage between locking, triggering, and high-speed launch through the coordinated action of a longitudinal high-strength launch spring and a transverse tenon-and-mortise latching traction spring. Upon impact with the target, it drives the launcher ram to rebound and penetrate the core component. The device features a streamlined shape and a sealed design to reduce wind resistance, supports both pure physical impact and composite strike modes filled with thermite and expanded graphite powder, and is adaptable to multi-rotor and fixed-wing UAVs for installation in various orientations. This invention eliminates the need for explosives or self-destructive impacts, significantly reducing the cost of a single countermeasure, greatly improving interception accuracy and safety, and is reusable.

Description

Technical Field

[0001] This invention relates to the field of drone countermeasure and interception protection technology, specifically to a modular impact interception device assembled on a drone. Background Technology

[0002] With the rapid iteration and popularization of drone technology, its application scenarios in military and civilian fields such as information reconnaissance, security patrol, logistics transportation, and agricultural plant protection are constantly expanding, greatly improving operational efficiency and coverage. However, at the same time, problems such as illegal intrusion, malicious interference, and unauthorized flights are becoming increasingly prominent, posing a serious threat to public safety, privacy protection, and the protection of critical facilities, thus driving drone countermeasure technology to become a key research and development direction in the industry.

[0003] Current mainstream countermeasures against drones mainly revolve around electronic jamming, physical interception, and weapon strikes. Among these, the countermeasures most relevant to the technical solution of this invention can be summarized into the following three categories, and each type of countermeasure has obvious drawbacks:

[0004] Pure physical impact countermeasures: A typical example is patent CN119024863A. Its core principle is to manipulate the intercepting drone to directly collide with the target drone in a rigid manner, using the impact force to damage the target drone's structural integrity or power system, thus achieving the interception objective. The core drawback of this technology lies in its "mutual destruction" mode. During the interception process, both drones suffer irreversible damage due to the collision, resulting in high interception costs—when the target is a low-cost civilian drone, the interceptor must incur equal or even higher equipment damage costs, making long-term application economically unsustainable. Furthermore, the falling drone debris during the collision may cause secondary injuries to ground personnel or facilities, making safety risks difficult to control.

[0005] Net-based interception technology, such as the solution disclosed in patent CN207931998U, involves mounting a foldable net-catching device on the intercepting drone. Upon approaching the target, the net unfolds, entangling the drone's propellers or fuselage and rendering it incapable of flight. The key challenge of this technology lies in its extremely high requirements for operational precision and environmental conditions: on the one hand, it requires precise control of the distance, relative speed, and attitude between the intercepting drone and the target; otherwise, net-catching deviations can easily lead to interception failure. On the other hand, in scenarios with strong winds, high-speed maneuvering target drones, or multiple targets operating in parallel, the stability of the net deployment and the entanglement effect decrease significantly, resulting in a generally low success rate in practical applications and making it difficult to meet the interception needs in complex scenarios.

[0006] Explosive weapon interception technology: Represented by patent CN215984227U, this technology involves mounting small explosive devices, such as shotgun-like projectiles, on drones. These devices detonate upon approaching the target, using shockwaves and shrapnel to damage the target drone. While this technology possesses strong destructive capabilities, it suffers from serious safety hazards and application limitations: Explosive devices are controlled substances, requiring strict approval for their production, transportation, and use, making them unsuitable for routine scenarios such as civilian security and low-altitude air traffic control; furthermore, the dispersion of debris from the explosion is uncontrollable, easily injuring nearby legally flying drones, aircraft, or ground personnel and facilities, compromising safety and compliance.

[0007] Furthermore, electronic jamming countermeasures are susceptible to electromagnetic interference, posing a risk of accidentally interfering with legitimate drones, and are only partially effective against drones with anti-jamming capabilities. Microwave and laser weapon strike technologies, on the other hand, face problems such as large equipment size, high energy consumption, and high cost, making it difficult to miniaturize and adapt them for drone deployment. Additionally, the strike range and effectiveness of laser weapons are significantly reduced in adverse weather conditions, and microwave weapons may cause secondary interference to surrounding electronic equipment, thus limiting their application scenarios.

[0008] In summary, existing drone countermeasure technologies generally suffer from the pain points of "high cost, low success rate, poor security, and limited adaptability." There is an urgent need for a drone interception device that can balance low cost, high reliability, security and compliance, and adaptability to multiple scenarios, in order to solve many of the shortcomings of current technologies and meet the actual needs of military and civilian sectors for drone countermeasures. Summary of the Invention

[0009] To address the existing technical problems, this invention provides a modular impact interception device for use with unmanned aerial vehicles (UAVs). Through multi-component collaborative design and structural innovation, a modular, highly adaptable, and high-efficiency impact device is constructed. The specific technical solution is as follows: The device adopts a modular architecture of "component splitting - precise adaptation - collaborative work". The core consists of five major components: a launching impact bar (101), a loading mechanism (103, 105, 701, 702), a rebound launching mechanism (106, 107, 108, 109), a streamlined launcher shell (102), and a launcher fixed chassis (110). Each component is detachably connected through standardized interfaces, which facilitates individual replacement and maintenance and allows for flexible adaptation to different UAV models. The launcher mounting base (110) serves as the installation foundation and is equipped with multiple sets of evenly distributed mounting holes. It can be fixed to any horizontal or vertical surface of the UAV body using fixing screws (201), enabling multi-directional assembly from the top, sides, and abdomen, thus overcoming the limitations of traditional device installation positions. The streamlined launcher shell (102) is entirely covered by the rebound launch mechanism and is sealed to the launcher mounting base (110) to form a complete aerodynamic shape, ensuring the structural integrity of the device and the UAV. In addition, the device is also equipped with a ramming rod fixing auxiliary device (103) for calibrating the launch direction and assisting in ejection, further improving launch accuracy.

[0010] The launching impact bar adopts a multi-functional structural design, and the specific design scheme is as follows:

[0011] The launching ram (101) is made of high-strength metal, such as stainless steel, high-strength alloy steel, and high-strength aluminum alloy, which is integrally formed to take into account both structural strength and puncture performance. The top is designed as a needle-shaped wedge armor-piercing part. Through precision machining, the diameter of the finest tip is 0.3~0.8mm, and the tip cone angle is 15º~30º. It can accurately pierce the shell of the target UAV and reach the core components such as the internal circuit board and power system, maximizing the puncture and damage effect. The middle section of the rod is a cylindrical structure to ensure stability during installation. A cylindrical fixing and pushing device is set at the rear to form a precise fit with the launching cavity (104) of the ram.

[0012] The launcher has a through-hole (701) in the middle, which serves as a force point for installation and disassembly. It can be used with a special installation tool (702) to achieve quick operation. The magnetic suction device (703) at the bottom of the pusher forms a "magnetic suction + buckle" double fixing structure with the bottom fixing buckle (105) of the launcher body. After installation, the magnetic suction device automatically attaches to the corresponding area at the bottom of the launcher, and the buckle evenly clamps the launcher body from all sides. This not only prevents the launcher from slipping when the UAV is flying at high speed or making maneuvering turns, but also prevents tilting before launch, thus ensuring launch accuracy.

[0013] The launching ram's propulsion device adopts a cavity structure (704), which reduces the overall weight of the device and the load pressure on the UAV, while reserving space for functional expansion. It can be filled with functional filling materials such as thermite and expanded graphite powder according to interception requirements, realizing the switching between "physical impact" and "high temperature damage" composite strike modes. At the same time, it supports the rapid replacement of pure physical armor-piercing rams and filled rams to adapt to targets with different protection levels.

[0014] The loading mechanism is designed for convenience and precision, and is specifically designed for quick replacement and precise positioning. The core components include an auxiliary hole (701), a special installation auxiliary tool (702), an impact rod fixing auxiliary device (103) for the impact rod launching chamber (104), and an impact rod bottom fixing buckle (105). The loading mechanism supports both motorized and manual loading modes. During manual installation, the operator passes the installation auxiliary tool (702) through the auxiliary hole (701) of the launching impact rod. With the leverage of the tool and the limiting effect of the impact rod fixing auxiliary device (103), the launching impact rod can be directly pressed into the impact rod launching chamber (104) without disassembling the launcher body or other complex processes. During the loading process, the impact rod bottom fixing buckle (105) on the impact rod fixing chassis (111) automatically pops up and locks in place, and the magnetic suction device (703) simultaneously attracts it, realizing "one-click installation and automatic positioning". The operation can be completed by a single person, which greatly improves the reuse efficiency of the device and meets the needs of automated operation or manual emergency operation.

[0015] The rebound launching mechanism adopts a dual-spring cooperative design, and the specific design scheme is as follows:

[0016] As the core power component, the rebound launch mechanism adopts a dual-spring collaborative structure of "longitudinal energy storage + lateral locking". It consists of a powerful launch spring (107), a tenon and mortise snap-lock traction spring (108) and a tenon and mortise snap-lock structure (109) to realize the complete link of "stable locking - precise triggering - high-speed launch".

[0017] The energy storage and locking mechanism includes: a powerful launch spring (107) arranged longitudinally along the launch direction of the launch bar, which compresses and stores energy synchronously when the launch bar is installed, providing instantaneous explosive force for launch; a launch cavity support rod (106) evenly arranged along the inner wall of the launch cavity (104) of the launch bar, which not only provides installation support for the powerful launch spring (107), but also guides the movement trajectory of the launch bar, preventing the rod from deviating during launch; a tenon and mortise buckle structure (109) is composed of tenon and mortise buckles that fit together at the top and bottom, and a tenon and mortise buckle traction spring (108) is set laterally, with each end connected to a corresponding tenon and mortise buckle, providing continuous lateral traction force, so that the tenon and mortise structure fits tightly when there is no external force, and firmly locks the launch bar, ensuring that it does not loosen or launch incorrectly during flight.

[0018] The triggering and launching mechanism includes: when the UAV carrying device approaches the target, the wedge-shaped armor-piercing part of the launching ram makes priority contact with the target and generates a squeezing force. This force is transmitted to the tenon and mortise latch structure (109), causing the tenon and mortise latch to retract inward. The tenon and mortise latch traction spring (108) is stretched and deformed, and the locked state is released. At this time, the powerful launching spring (107) instantly releases the stored elastic potential energy, generating a powerful longitudinal thrust, driving the launching ram to be launched at high speed, achieving millisecond-level response launch. At the same time, the instantaneous recoil generated by the launch will slightly reverse and push the UAV backward, effectively avoiding direct collision between the UAV and the target due to inertia, and protecting the safety of the intercepting UAV.

[0019] The device housing adopts a streamlined housing design: the streamlined transmitter housing (102) adopts an aerodynamic arc-shaped curved surface structure, and the outline is optimized through fluid dynamics simulation. The surface is smooth and without protrusions, which can effectively reduce the air resistance of the UAV during flight and avoid problems such as UAV speed reduction and increased energy consumption caused by excessive wind resistance. The housing material is made of lightweight and high-strength material, which reduces its own weight while ensuring structural strength and reducing the impact on the UAV load.

[0020] The device's sealing and cavity design: The impact rod launch cavity (104) is designed as a cavity structure by default, which not only reserves space for the launch impact rod movement, but also further reduces the weight of the device; the device's cavity mounting hole adopts a sealed design, which uses a sealing gasket and a snap-on sealing structure to prevent airflow from entering the mounting hole during high-speed flight, avoid device shaking and falling off due to airflow disturbance, and at the same time ensure that the internal components are not corroded by external dust, water vapor, etc., thereby improving the device's service life.

[0021] The launcher mounting chassis design: The launcher mounting chassis (110) serves as the core connection between the device and the UAV. It is integrally molded from high-strength lightweight alloy or plastic, taking into account both structural strength and lightweight requirements, and avoiding excessive load on the UAV. The chassis surface is provided with multiple sets of evenly distributed waist-shaped mounting holes, which can be adapted to the mounting hole spacing of different UAV models. It can be stably connected to any horizontal surface (such as the wing, fuselage side) or vertical surface (such as the fuselage belly, top) of the UAV body by fixing device screws (201), breaking through the limitations of traditional device installation positions. The upper surface of the chassis is provided with a sealing groove that matches the streamlined launcher shell (102). An elastic sealing gasket is embedded in the groove to achieve a tight seal when the shell and chassis are connected, preventing airflow from seeping into the device during high-speed flight. The bottom of the chassis is provided with an anti-slip buffer pad to avoid damage to the surface of the UAV body during installation, while enhancing the stability after installation and preventing the screws from loosening due to flight vibration.

[0022] In response to the maneuverability of multi-rotor drones, the device is designed for top and side mounting, combined with a direct ramming attack mode, enabling multi-angle interception through the drone's flexible attitude adjustment. For fixed-wing drones with high-speed flight characteristics, the device is top-mounted, adaptable to attacking from the bottom of the target. Utilizing the high-speed kinetic energy of the fixed-wing drone, combined with the device's ejection effect, it achieves a precise penetrating strike on the target, further enhancing the interception effect.

[0023] The application scope of the device is not limited to countering drones. It can also be flexibly assembled into various unmanned devices such as unmanned ships and unmanned vehicles by adapting to different installation interfaces, so as to meet the interception needs in different scenarios and expand the applicability of the technical solution.

[0024] Through the above-described structure and design, this invention effectively solves the aforementioned high-cost anti-reverse problem and can achieve:

[0025] Significantly reduce countermeasure costs: Abandoning the traditional "common destruction" model, the replaceable launcher ram and catapult design prevent damage to the countermeasure drone. The launcher ram is reusable, reducing the cost of a single countermeasure by more than 70% compared to traditional physical impact methods. The modular structure and convenient loading design reduce equipment maintenance and consumable costs, further improving economic efficiency.

[0026] The precision and effectiveness of the countermeasures are significantly improved: the streamlined shell and sealed design reduce the impact of wind resistance on flight attitude, and the magnetic and snap-lock dual fixing structure ensures that the launch bar does not deviate or slip during high-speed maneuvers; the tenon trigger mechanism responds quickly, and the powerful launch spring provides sufficient kinetic energy. Combined with the piercing effect of the wedge-shaped armor-piercing part, it can accurately penetrate the core components of the target. The countermeasure effect is significantly improved compared to the traditional pure physical impact mode, and it does not rely on the hardness advantage of the countermeasure drone's body.

[0027] Strong adaptability to multiple scenarios and devices: The modular design supports multi-directional installation of different types of drones such as multi-rotor and fixed-wing drones, and can also be extended to various unmanned devices such as unmanned ships and unmanned vehicles; it can flexibly switch between pure physical strike and composite strike modes, which can meet the countermeasure needs of various scenarios such as civilian security and low-altitude control, and adapt to different target types and environmental conditions.

[0028] High safety and compliance: Completely avoids the use of explosives, eliminates regulatory risks, meets civil safety standards, and can be widely used in various civil scenarios; manual loading mode and double fixing structure ensure operational safety, and countermeasures can be activated as needed to effectively avoid accidental injury to surrounding legal equipment or personnel.

[0029] Easy to operate and highly continuous: The replacement process for the launch-type ram is simple and efficient, and can be completed quickly by a single person; the number of devices carried by a single drone can be flexibly increased or decreased, and after use, it can be quickly reloaded through automated facilities or manual methods, realizing the cycle of "launch-recovery-reloading", which greatly improves the continuity and efficiency of counter-attack operations. Attached Figure Description

[0030] Figure 1 is a side perspective view of the main body of the device (with the launching impact bar installed) according to an embodiment of the present invention;

[0031] Figure 2 is a bottom view of the device according to an embodiment of the present invention;

[0032] Figure 3 is a top view of the device according to an embodiment of the present invention;

[0033] Figure 4 is a cross-sectional view of the waist of the device according to an embodiment of the present invention;

[0034] Figure 5 is an illustration of the device's launching impact bar first impacting the target according to an embodiment of the present invention. The device is initially activated, the tenon and mortise structure is not open, and it has not been ejected.

[0035] Figure 6 is a diagram of the device after impact and launch according to an embodiment of the present invention. The device has been activated, the tenon and mortise structure has been opened, and it has been forcefully launched.

[0036] Figure 7 is an illustration of the launching impact bar and installation auxiliary tools according to an embodiment of the present invention;

[0037] Figure 8 is a schematic diagram of the insertion of the launching impact bar and auxiliary tool according to an embodiment of the present invention;

[0038] Figure 9 is a schematic diagram of the installation of the launching impact bar according to an embodiment of the present invention;

[0039] Explanation of reference numerals in the attached drawings: 101 Launching ram, 102 Streamlined launcher housing, 103 Ram fixing auxiliary device, 104 Ram launching cavity, 105 Ram bottom fixing buckle, 106 Launch cavity support rod, 107 Powerful launching spring, 108 Tenon and mortise buckle traction spring, 109 Tenon and mortise buckle structure, 110 Launcher fixing chassis, 111 Ram fixing chassis, 201 Fixing device screw, 501 Simulated target, 701 Auxiliary hole, 702 Installation auxiliary tool, 703 Magnetic suction device, 704 Cavity structure. Detailed Implementation

[0040] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0041] Example 1: Basic Impact Mode

[0042] 1. Installation Phase

[0043] (1) Fixing the transmitter body to the UAV

[0044] Select a suitable UAV (multi-rotor or fixed-wing) as the mounting platform and determine the installation location according to the interception requirements. Referring to the bottom view of the device shown in Figure 2, take out the impact device of the present invention, and use four sets of fixing screws (201) to securely fix the main body of the launcher to the pre-set installation area such as the belly, under the wing, or top of the UAV through the preset mounting holes on the launcher fixing base (110) in Figure 2. During installation, ensure that the launcher fixing base (110) is in close contact with the surface of the UAV body, and tighten the screws evenly to avoid the device shaking or falling off due to loosening during high-speed flight.

[0045] After installation, check the sealing connection between the streamlined launcher housing (102) and the launcher mounting base (110) according to Figure 1 to ensure that the mounting holes are properly sealed and there is no gap or air leakage, thus ensuring the overall aerodynamic performance of the device. At the same time, confirm that the components such as the ram fixing auxiliary device (103) and the launch chamber support rod (106) in Figure 1 are installed without deviation, providing a stable foundation for subsequent loading and launching of the launch ram. Check the centering of the launch ram (101) according to Figure 3 to ensure that it is coaxial with the ram launch chamber (104) to avoid directional deviation during launch. At the same time, observe the overall assembly status of the streamlined launcher housing (102) to confirm that there are no protrusions or assembly gaps, thus ensuring aerodynamic performance.

[0046] (2) Loading operation of the launching batter

[0047] Prepare a metal launching rod (101) as shown in Figure 7. The top of the rod has a needle-shaped structure with an auxiliary hole (701) in the middle. The rear part has a cylindrical fixed pushing device, and the bottom is equipped with a magnetic attraction device (703). The inside of the pushing device is a hollow structure (704). Before filling, it is necessary to confirm that the needle-shaped structure at the top of the rod is not deformed, the auxiliary hole (701) is unobstructed, and the magnetic attraction device (703) is functioning properly.

[0048] Take the installation auxiliary tool (702) in Figure 7 and, as shown in Figure 8, pass the front end of the installation auxiliary tool (702) through the auxiliary hole (701) of the launching batter, so that the tool and the launching batter form a stable assembly combination, which facilitates the application of pressure for installation.

[0049] Holding the end of the installation aid (702), referring to Figure 9, align the launching rod (101) with the entrance of the launching chamber (104) in Figure 1, and press it down slowly and vertically. With the leverage of the installation aid (702), the launching rod smoothly enters the launching chamber until the magnetic attraction device (703) at the bottom of the launching rod is fully engaged.

[0050] At this time, the bottom fixing buckle (105) of the impact rod on the impact rod fixing chassis (111) in Figure 1 automatically pops up, clamping the cylindrical fixing and pushing device of the launching impact rod from all sides. Together with the magnetic suction device (703), it forms a double fixing structure of "magnetic suction + buckle" to prevent the launching impact rod from tilting or slipping. At the same time, the powerful launching spring (107) arranged longitudinally in Figure 1 is compressed and stores elastic potential energy. The mortise and tenon buckle traction spring (108) arranged laterally pulls the mortise and tenon buckle structure (109) so that the top and bottom mortise and tenon buckles fit tightly, realizing the locking of the launching impact rod and completing the loading operation.

[0051] 2. Aiming Phase

[0052] The drone and ground control terminal are activated. The detection system on the drone searches for the target drone. After target identification and precise positioning are completed, the optimal interception route is planned.

[0053] The drone is maneuvered to approach the target drone, and its flight attitude is adjusted in real time to ensure that the needle-shaped structure of the launch ram (101) in Figure 5 is always aligned with the core area of ​​the target drone, such as the location of the circuit board and power system. Since the protruding part of the launch ram (101) extends beyond the drone body, it can be ensured that the ram contacts the target first before the drone body collides.

[0054] When the distance between the UAV and the target UAV reaches the preset interception range, the UAV maintains high-speed and stable flight to ensure that the aiming angle between the launch bar (101) and the target is stable. At this time, the device is in the state shown in Figure 5, the tenon and mortise buckle structure (109) is not unlocked, the launch bar is not ejected, and it is in a ready-to-fire state.

[0055] 3. Launch Phase

[0056] As the drone continues to approach the target, when the needle-shaped structure of the launch ram (101) first contacts the target drone shell and generates a squeezing force, the force is transmitted to the tenon and mortise buckle structure (109) in Figure 4, causing the tenon and mortise buckle to retract inward.

[0057] In Figure 4, the tenon-and-mortise snap-fit ​​traction spring (108) is stretched and deformed under tension, and the locking state of the tenon-and-mortise snap-fit ​​structure (109) is released. At this time, the powerful launching spring (107) storing elastic potential energy in Figure 4 releases energy instantaneously, generating a strong longitudinal thrust, which pushes the launching batter (101) to be ejected at high speed along the launching chamber (104) in Figure 1. The launching chamber support rod (106) guides the trajectory of the launching batter, and the batter fixing auxiliary device (103) further calibrates the launching direction to ensure penetration accuracy.

[0058] The needle-shaped structure of the launch ram (101) precisely penetrates the carbon fiber shell of the target UAV, reaching its internal core components and causing physical damage. Simultaneously, the instantaneous recoil generated by the launch slightly propels the UAV backward, preventing a direct collision between the UAV and the target UAV due to inertia and protecting the platform. After launch, the device is in the state shown in Figure 6, with the tenon-and-mortise latch structure (109) fully unlocked, and the launch ram has been fired.

[0059] 4. Return Phase

[0060] After the interception is completed, the drone is controlled by the ground control terminal to return to the take-off and landing point along the preset return route.

[0061] After the UAV lands, manually loosen the bottom fixing buckle (105) of the ramming bar in Figure 1, and use the installation auxiliary tool (702) to pass through the auxiliary hole (701) of the ramming bar to remove the ramming bar from the ramming bar launching chamber (104). If the ramming bar is intact, it can be used directly for the next loading; if it is damaged, replace it with a new ramming bar.

[0062] Clean the impurities in the ram launch chamber (104), check the status of the core components such as the tenon and mortise snap structure (109), the powerful launch spring (107), and the tenon and mortise snap traction spring (108) in Figure 1, and after confirming that there are no abnormalities, the launch ram can be loaded again, and the above process can be repeated to achieve cyclic use.

[0063] Example 2: Enhanced Strike Mode

[0064] The basic procedures for the installation, aiming, launching, and return phases in this embodiment are the same as in Embodiment 1, with the only difference being the functional expansion of the launching ram. The specific enhancements are as follows:

[0065] Prepare the launcher (101) shown in Figure 7. Use the cavity structure (704) of its propulsion device to fill the cavity with a preset dose of thermite or expanded graphite powder. After filling, seal the cavity opening to prevent leakage of filling material during flight.

[0066] Following the loading process of Example 1, the loaded launching batter is inserted into the launching chamber (104) of the batter in Figure 1 using the installation auxiliary tool (702) to complete the magnetic attraction and buckle fixation and the tenon and mortise structure locking.

[0067] During the launch phase, when the launch ram (101) is ejected at high speed and penetrates the target UAV shell, if it is filled with thermite, it will react under the impact force and generate high temperature, which will damage the electronic components and power system of the target UAV through heat conduction; if it is filled with expanded graphite powder, it will diffuse and adhere to the circuit surface of the target UAV after penetration, causing circuit short circuit failure, thus achieving a composite strike effect of "physical impact + high temperature damage" or "physical impact + electronic interference", and the damage efficiency is significantly improved compared with pure physical impact.

[0068] After returning to base, remove the used launcher ram, clean the residual filling material and impurities in the launcher cavity (104), check the status of the internal components of the launcher, replace with a new refillable launcher ram or refill the filling material, and then the interception mission can be performed again.

[0069] The device of this invention can flexibly adjust its installation and attack methods according to the type of drone: when mounted on the top or side of a multi-rotor drone, it can utilize its maneuverability to carry out multi-angle ramming attacks; when mounted on the top of a fixed-wing drone, it can utilize its high-speed flight characteristics to launch attacks from the bottom of the target drone, further improving the interception success rate. Furthermore, this device can be adapted to different mounting interfaces and installed on various types of unmanned equipment such as unmanned ships and unmanned vehicles for interception and countermeasures against various unmanned devices.

Claims

1. A modular collision interception device assembled on a drone, characterized in that, The device includes a launching ram, a loading mechanism, a rebound launching mechanism, a streamlined outer shell, and a launcher mounting chassis. The launcher mounting chassis is fixed to the UAV body via a detachable connection structure. The streamlined outer shell covers the outside of the rebound launching mechanism and is sealed to the launcher mounting chassis. The launching ram is movably engaged with the rebound launching mechanism. The rebound launching mechanism is driven by the launching ram, and after the launching ram contacts the target, it is triggered to unlock and drive the launching ram to rebound at high speed to penetrate or destroy the target.

2. The apparatus according to claim 1, characterized in that, The front end of the launcher has an integrally formed wedge-shaped armor-piercing part, which is made of hard metal and has a needle-shaped head. It can accurately pierce the carbon fiber shell and internal core circuit board and power system components of the target UAV. Combined with the kinetic energy output of the rebound launch mechanism, it can achieve efficient penetration and destruction.

3. The apparatus according to claim 1, characterized in that, The loading mechanism includes an auxiliary hole on the launching rod, a special installation auxiliary tool, and a guide and positioning structure for the launcher body. The installation auxiliary tool passes through the auxiliary hole of the launching rod and can quickly press the launching rod into the launching chamber of the rebound launching mechanism. After installation, it is firmly fixed by a combination of snap-fit ​​and magnetic positioning.

4. The apparatus according to claim 1, characterized in that, The rebound launching mechanism includes a high-strength spring energy storage device, a tenon-and-mortise trigger release mechanism, and a tenon-and-mortise buckle traction spring. The high-strength spring energy storage device is longitudinally arranged along the launching direction of the launching impact bar, providing instantaneous explosive force to the launching impact bar. The tenon-and-mortise trigger release mechanism includes mutually fitting top and bottom tenon-and-mortise buckles. The tenon-and-mortise buckle traction spring is arranged laterally and connected to the tenon-and-mortise buckles, providing lateral traction force to ensure stable locking of the tenon-and-mortise structure when there is no external force. When the launching impact bar contacts the target and generates a squeezing force, the tenon-and-mortise buckles retract inward and release the lock, and the high-strength spring energy storage device instantly releases kinetic energy, driving the launching impact bar to launch at high speed.

5. The apparatus according to claim 1, characterized in that, The launching impact bar has an axially extending cavity structure inside, which can be selectively filled with thermite and expanded graphite powder functional filler materials. After filling, it forms a composite impact mode that combines impact and auxiliary damage. The thermite reacts and generates high temperature at the moment of impact and penetration, which damages the target electronic components through heat conduction. The expanded graphite powder diffuses and adheres to the target circuit surface after penetration, causing the circuit to short-circuit and fail.

6. The apparatus according to claim 4, characterized in that, The rebound launching mechanism adopts a dual-spring cooperative structure with a horizontal spring for rebound and a vertical spring for explosive force; the horizontally arranged tenon and mortise buckle traction spring is responsible for locking and unlocking the tenon and mortise structure, and the vertically arranged high-strength spring energy storage device is responsible for providing the core explosive force for launching the launcher. The mechanical trigger control through tenon and mortise buckles enables precise linkage between locking, triggering, and launching, ensuring structural stability during flight and releasing sufficient kinetic energy upon impact.

7. The apparatus according to claim 2, characterized in that, The bottom of the launching impact bar is equipped with a magnetic attraction device, and the center of the launching impact bar fixing base is provided with a magnetic attraction area. At the same time, the magnetic attraction area is provided with a bottom fixing buckle of the launching impact bar. After the launching impact bar is installed, the magnetic attraction device and the attraction area automatically attract and position themselves, and the bottom fixing buckle clamps the launching impact bar body from all sides, forming a launching impact bar with a double fixing structure of magnetic attraction and buckle.

8. The apparatus according to claim 1, characterized in that, The streamlined outer shell adopts an aerodynamic arc-shaped structure design with a smooth, non-protruding surface, which can significantly reduce wind resistance during drone flight. The mounting holes of the launcher base and the drone adopt a sealed structure design to prevent airflow from entering and causing device vibration. The rear push device of the launcher ram adopts a cavity structure, which reduces the overall weight of the device while ensuring structural strength. Combined with the streamlined outer shell and sealed design, it avoids vibration, detachment, and drone speed reduction problems caused by wind resistance and airflow interference during high-speed flight.

9. The apparatus according to claim 1, characterized in that, The device adopts a modular design, with detachable connections between the launching ram, the rebound launching mechanism, and the launcher mounting chassis. This allows for the rapid replacement of different types of launching rams (including pure armor-piercing and filler types), and the number of devices can be flexibly increased or decreased according to the payload capacity of the UAV and actual usage requirements. A single UAV can carry multiple sets of devices to achieve multi-target strikes or continuous strikes. After use, it can be quickly reloaded through automated facilities, achieving a "launch-recovery-reloading" cycle.

10. The apparatus according to claim 9, characterized in that, The device's installation and attack methods are adaptable to different types of unmanned equipment: for multi-rotor drones, it can be mounted on the top or side via a fixed chassis of the launcher, employing a direct ramming attack mode and utilizing the drone's maneuverability to adjust the attack angle; for fixed-wing drones, it can be mounted on the top and adapted to the target drone's bottom attack posture, using the high-speed flight characteristics of the fixed-wing drone to pursue it, and activating the rebound launch mechanism when approaching the target, so that the launcher ramming bar penetrates through the bottom of the target, avoiding direct collision with the target and thus preventing damage to itself.

11. The apparatus according to any one of claims 1-10, characterized in that, The device can also be mounted on unmanned platforms such as unmanned ships and unmanned vehicles to intercept and destroy unmanned equipment of the same or different types.

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