A low-cost air-launched towed stealth target drone

Abstract

The utility model discloses a low -cost air drop type towed stealth target machine in the technical field of unmanned plane, including the target machine that is composed of cabin section subassembly and rudder surface subassembly, the rudder surface subassembly swing installation is in cabin section subassembly, cabin section subassembly is by nose cabin, control cabin, first equipment cabin, battery cabin, second equipment cabin and tail cabin are composed, and the nose cabin, control cabin, first equipment cabin, battery cabin, second equipment cabin and tail cabin can all detachable connection between. The utility model discloses through adopting polyhedral stealth shape, stealth coating and replaceable signal enhancement equipment (active signal enhancer or corner reflector), greatly reduce the radar reflection area of self and simulate the radar echo characteristic of multiple stealth aircraft, realize the life -like simulation to different types stealth target, satisfy the actual combat demand of weapon system test and tactical training.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a low-cost, air-dropped, towed stealth target drone. Background Technology

[0002] With the rapid development of modern military aviation technology, advanced manned fighter jets and unmanned aerial vehicles are constantly improving in three core indicators: flight speed, combat radius, and stealth capability. In order to effectively carry out weapon system testing, tactical training, and tactical research, there is an urgent need for training targets that can realistically simulate such high-performance threat targets. However, existing mainstream target technology solutions have an irreconcilable contradiction in meeting the requirements of simulation realism and economic affordability.

[0003] Currently, equipment used to simulate aerial targets is mainly divided into two categories. One category is traditional unpowered towed targets, such as canvas targets, which are towed by a carrier aircraft via cables. These targets have simple structures and low costs, but their aerodynamic shape is rudimentary, their flight speed is low, their attitude is uncontrollable, and they have no stealth characteristics at all, making it impossible to simulate the key performance of modern fighter jets. The other category is high-performance unmanned target drones developed in recent years. These are small unmanned aerial vehicles with power, flight control, and avionics systems, which can better simulate real targets in terms of speed, range, and maneuverability. However, these target drones are technically complex and expensive, and their research and manufacturing costs are close to those of actual combat drones. If used as disposable consumables, the cost per mission is extremely high, which seriously restricts their deployment and application in routine and large-scale training of the armed forces.

[0004] Therefore, there are certain problems in the current target field: on the one hand, traditional low-cost towed targets have poor performance and cannot meet the simulation requirements of advanced tactical indicators such as high speed and stealth; on the other hand, unmanned target drones that can achieve high-performance simulation are too costly to use due to system complexity and high cost. Therefore, we urgently need a low-cost air-drop towed stealth target drone to solve the above problems. Utility Model Content

[0005] To address the shortcomings of existing technologies, this invention provides a new low-cost, air-launched, towed stealth target drone solution. By employing modular sections, folding control surfaces, stealth shape and coating, and replaceable signal enhancement equipment, the power system is eliminated and can be recycled and reused, achieving controllable flight attitude and realistic stealth simulation of the target drone, significantly reducing manufacturing and operating costs.

[0006] The purpose of this utility model is achieved as follows: a low-cost, air-deployable towed stealth target drone, comprising a target drone composed of a section assembly and a control surface assembly, wherein the control surface assembly is movably mounted on the section assembly; the section assembly consists of a nose section, a control section, a first equipment section, a battery section, a second equipment section, and a tail section, and the nose section, control section, first equipment section, battery section, second equipment section, and tail section are all detachably connected; the control surface assembly consists of a wing and a tail fin, the wing being connected to a first drive component in the first equipment section, and the tail fin being connected to a second drive component in the second equipment section.

[0007] Optionally, the nose section, control section, first equipment section, battery section, second equipment section, and tail section are all connected by connecting frames.

[0008] Optionally, a pull ring for connecting to an external tow rope is fixedly installed at the end of the nose section.

[0009] Optionally, a controller is fixedly installed inside the control cabin. When the controller is working, the first drive component and the second drive component drive the wings and tail to rotate, respectively.

[0010] Optionally, the first driving component includes a first hydraulic cylinder disposed in a first equipment compartment, the end of the first hydraulic cylinder being hinged to the first equipment compartment, a slide groove being provided on the first equipment compartment, a first hinge rod being slidably connected in the slide groove, a connecting block being provided on the first equipment compartment, one end of the first hinge rod being hinged to the connecting block, and the other end of the first hinge rod being hinged to the output end of the first hydraulic cylinder.

[0011] Optionally, the number of wings is two sets, and the two sets of wings rotate symmetrically on the first equipment compartment. Each wing consists of a wing root, a main wing surface, and an aileron surface rotatably connected to the main wing surface. A second hinge rod is hinged to each of the two sets of wing roots, and the other end of each of the two sets of second hinge rods is hinged to a connecting block. When the output end of the first hydraulic cylinder extends, the wing is in the first working area, and when the output end of the first hydraulic cylinder retracts, the wing is in the second working area.

[0012] Optionally, the second driving component includes a second hydraulic cylinder disposed in the second equipment compartment. A mounting bracket is fixedly installed in the second equipment compartment. The second hydraulic cylinder is hinged to the mounting bracket. A U-shaped rod is fixedly connected to the output end of the second hydraulic cylinder. Grooves are symmetrically provided on the U-shaped rod.

[0013] Optionally, the number of tail fins is two sets, and the two sets of tail fins rotate symmetrically on the second equipment compartment. The second equipment compartment has a rotating rod that rotates symmetrically. The rotating rod has an integrally formed actuating rod that matches the groove, and the end of the actuating rod is inserted into the groove. The two sets of tail fins are fixedly connected to the rotating rod. When the output end of the second hydraulic cylinder extends, the tail fin is in the first working area. When the output end of the second hydraulic cylinder retracts, the tail fin is in the second working area. When the tail fin is in the second working area, the two sets of tail fins are arranged in a V-shape.

[0014] Optionally, a battery pack for power supply is fixedly installed inside the battery compartment.

[0015] Optionally, the tail section is equipped with a signal enhancement device.

[0016] Compared with the prior art, the beneficial effects of this utility model are as follows: 1. According to one embodiment of the present disclosure, the low-cost air-dropped towed stealth target drone significantly reduces its own radar cross-section and simulates the radar echo characteristics of various stealth aircraft by adopting a multi-faceted stealth shape, stealth coating and replaceable signal enhancement equipment (active signal enhancer or corner reflector), thereby achieving realistic simulation of different types of stealth targets and meeting the combat-oriented requirements of weapon system testing and tactical training.

[0017] 2. According to one embodiment of this disclosure, the low-cost air-drop towed stealth target drone significantly reduces structural manufacturing costs, equipment procurement costs, and single-use costs by eliminating the power system, simplifying high-value electronic equipment, adopting a modular compartment design, reducing the overall size, and implementing a recycling and reuse mechanism. At the same time, it improves maintenance convenience and is suitable for large-scale, routine training scenarios. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the overall unfolded structure of this utility model.

[0020] Figure 2 This is a schematic diagram of the overall storage structure of this utility model.

[0021] Figure 3 This is a half-sectional structural diagram of the present invention.

[0022] Figure 4This is a first-view schematic diagram of the wing deployment structure of this utility model.

[0023] Figure 5 This is a schematic diagram of the second-view wing deployment structure of this utility model.

[0024] Figure 6 This is a schematic diagram of the internal structure of the first equipment compartment of this utility model.

[0025] Figure 7 This is a schematic diagram of the first working area of ​​the tail fin of this utility model.

[0026] Figure 8 This is a schematic diagram of the internal structure of the second equipment compartment of this utility model.

[0027] Figure 9 This is a schematic diagram of the tail wing storage structure of this utility model.

[0028] Figure 10 This is a schematic diagram of the wing storage structure of this utility model.

[0029] Figure 11 This is a schematic diagram of the second working area of ​​the wing according to the present invention.

[0030] Figure 12 This is a schematic diagram of the second working area of ​​the tail fin of this utility model.

[0031] The diagram shows the following: 1. Cabin section assembly; 11. Nose compartment; 12. Control compartment; 13. First equipment compartment; 131. First hydraulic cylinder; 132. Slide groove; 133. First hinge rod; 134. Connecting block; 135. Second hinge rod; 14. Battery compartment; 15. Second equipment compartment; 151. Second hydraulic cylinder; 152. Mounting bracket; 153. U-shaped rod; 154. Groove; 155. Rotating rod; 156. Actuating rod; 16. Tail compartment; 2. Control surface assembly; 21. Wing; 211. Wing root; 212. Main wing surface; 213. Aileron surface; 22. Tail fin; 3. Connecting frame; 4. Pull ring; 5. Controller; 6. Battery pack; 7. Reinforcing device. Detailed Implementation

[0032] 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.

[0033] like Figure 1-12 As shown, a low-cost, air-deployable towed stealth target drone includes a target drone consisting of a section assembly 1 and a control surface assembly 2, with the control surface assembly 2 movably mounted on the section assembly 1.

[0034] Here, the compartment assembly 1 adopts a multi-faceted stealth shape design, which can reduce the radar cross-section; the control surface assembly 2 is assembled to the corresponding mounting position of the compartment assembly 1 through a rotatable connection structure, which can realize the function switching of folding and unfolding to adapt to different working conditions.

[0035] Furthermore, the multifaceted stealth shape provides a foundation for simulating stealth targets, and the folding / unfolding design of the control surface component 2 improves the target drone's adaptability to different scenarios, while simplifying the overall structure and reducing design and manufacturing costs.

[0036] The module 1 consists of a nose section 11, a control section 12, a first equipment section 13, a battery section 14, a second equipment section 15, and a tail section 16. The nose section 11, control section 12, first equipment section 13, battery section 14, second equipment section 15, and tail section 16 can be detachably connected. The nose section 11, control section 12, first equipment section 13, battery section 14, second equipment section 15, and tail section 16 are all connected by a connecting frame 3.

[0037] Here, each compartment is an independent functional module. The connecting frame 3 is made of lightweight and high-strength material and is integrally molded. Both ends are precisely fitted with the docking end faces of adjacent compartments and are assembled using standardized fasteners. The connecting frame 3 has reserved cable channels to facilitate circuit connection between compartments. At the same time, it has been aerodynamically optimized to reduce aerodynamic drag during towed flight.

[0038] Furthermore, modular disassembly reduces mold development and parts processing costs, while standardized connecting frames 3 improve the interchangeability of each section, facilitating rapid replacement of damaged parts after recovery and enabling reuse; lightweight materials and aerodynamically optimized design reduce the load on the carrier aircraft and support batch loading and carrying.

[0039] A pull ring 4 for connecting to an external tow rope is fixedly installed at the end of the nose compartment 11.

[0040] Here, the pull ring 4 is made of integrated forging process, and the material is high-strength alloy steel. The surface is treated with anti-corrosion and wear-resistant treatment, and the inner side is equipped with anti-slip groove. Its inner diameter is compatible with the joint of the mainstream carrier tow rope, which can evenly transmit the towing force to the entire fuselage.

[0041] Furthermore, the high-strength material and anti-slip groove design ensure a stable and reliable towing connection, preventing loosening and detachment during flight; the standardized size adapts to a variety of carrier aircraft, eliminating the need for separately designed adaptation structures; and the anti-corrosion and wear-resistant treatment extends service life and reduces consumption costs.

[0042] A controller 5 is fixedly installed inside the control cabin 12. When the controller 5 is working, the first drive component and the second drive component drive the wing 21 and the tail 22 to rotate, respectively.

[0043] Here, the controller 5 integrates the flight control computer, attitude sensor and motor driver, and the modular design reduces the installation space and wiring complexity. The controller 5 is connected to the battery pack 6 and communicates with the first drive unit and the second drive unit through signal lines, which can collect fuselage attitude data in real time and send control commands.

[0044] Furthermore, the integrated design reduces the number of electronic devices, lowers procurement costs and failure risks, and improves operational reliability; the attitude sensing and flight control linkage enables precise control of flight attitude, breaking the limitation of uncontrollable attitude of traditional towed target drones and adapting to high-speed flight requirements.

[0045] The control surface assembly 2 consists of a wing 21 and a tail fin 22. The wing 21 is connected to a first drive unit inside the first equipment compartment 13. The first drive unit includes a first hydraulic cylinder 131 disposed inside the first equipment compartment 13. The end of the first hydraulic cylinder 131 is hinged to the first equipment compartment 13. A slide groove 132 is provided on the first equipment compartment 13. A first hinge rod 133 is slidably connected in the slide groove 132. A connecting block 134 is provided on the first equipment compartment 13. One end of the first hinge rod 133 is hinged to the connecting block 134, and the other end of the first hinge rod 133 is hinged to the output end of the first hydraulic cylinder 131.

[0046] Here, the cylinder end of the first hydraulic cylinder 131 is fixedly hinged to the inner wall of the first equipment compartment 13 via a hinge seat. The length of the slide 132 matches the stroke of the wing 21 when it is folded and unfolded. The sliding direction of the first hinge rod 133 is consistent with the length direction of the slide 132, forming a complete power transmission link.

[0047] Furthermore, the mechanical transmission structure is simple and reliable, reducing costs and failure probability compared to complex electronic drive schemes; the guide effect of the slide 132 on the articulated rod ensures that the wing 21 moves smoothly without jamming, and the hydraulic cylinder drive has a strong load capacity, which can overcome aerodynamic drag to complete attitude adjustment.

[0048] There are two sets of wings 21, which rotate symmetrically on the first equipment compartment 13. Each wing 21 consists of a wing root 211, a main wing surface 212, and an aileron surface 213 rotatably connected to the main wing surface 212. Each wing root 211 is hinged with a second hinge rod 135, and the other end of each second hinge rod 135 is hinged to a connecting block 134. When the output end of the first hydraulic cylinder 131 extends, the wing 21 is in the first working area. When the output end of the first hydraulic cylinder 131 retracts, the wing 21 is in the second working area.

[0049] Here, the main wing surface 212 is made of lightweight composite material and coated with a stealth coating; the aileron surface 213 is rotatably connected to the outer end of the main wing surface 212 via a hinge and can be deflected independently; the first working area is the horizontally deployed state of the wing 21, which is used to provide lift, and the second working area is the folded state of the wing 21, which is used for mounting and storage.

[0050] Furthermore, the folding design significantly reduces the space occupied during mounting, making it convenient for carrier aircraft to carry in batches; lightweight composite materials and stealth coating reduce the fuselage weight and enhance stealth performance; the independent control of the 213 ailerons enables the adjustment of the fuselage roll attitude, improving the simulation realism; and the modular structure also facilitates replacement after damage.

[0051] The tail fin 22 is connected to the second drive unit inside the second equipment compartment 15. The second drive unit includes a second hydraulic cylinder 151 disposed inside the second equipment compartment 15. A mounting bracket 152 is fixedly installed inside the second equipment compartment 15. The second hydraulic cylinder 151 is hinged to the mounting bracket 152. A U-shaped rod 153 is fixedly connected to the output end of the second hydraulic cylinder 151. Grooves 154 are symmetrically provided on the U-shaped rod 153.

[0052] Here, the mounting bracket 152 is U-shaped and is fixed inside the second equipment compartment 15 by bolts. The middle part of the cylinder body of the second hydraulic cylinder 151 is hinged to the mounting bracket 152 by a hinge shaft, allowing it to rotate flexibly. The U-shaped rod 153 is fixed to the output end of the second hydraulic cylinder 151 by threads. The inner wall of the groove 154 is smoothed to ensure smooth power transmission.

[0053] Furthermore, the U-shaped mounting bracket 152 provides a stable mounting base for the hydraulic cylinder while reserving sufficient rotation space; the symmetrical groove 154 design enables synchronous driving of the two sets of tail wings 22, simplifies the transmission structure, reduces the number of parts, and lowers manufacturing costs and assembly difficulty.

[0054] There are two sets of tail fins 22, which rotate symmetrically on the second equipment compartment 15. A rotating rod 155 rotates symmetrically on the second equipment compartment 15. An actuating rod 156 adapted to the groove 154 is integrally formed on the rotating rod 155, and the end of the actuating rod 156 is inserted into the groove 154. The two sets of tail fins 22 are fixedly connected to the rotating rod 155. When the output end of the second hydraulic cylinder 151 extends, the tail fin 22 is in the first working area. When the output end of the second hydraulic cylinder 151 retracts, the tail fin 22 is in the second working area. When the tail fin 22 is in the second working area, the two sets of tail fins 22 are arranged in a V-shape.

[0055] Here, the rotating rod 155 extends laterally through the rear side wall of the second equipment compartment 15 and is fixedly connected to the tail fin 22 by bolts; the toggle rod 156 is adapted to the curvature of the groove 154 and fits tightly; the first working area is the tail fin 22 folded and close to the fuselage, and the second working area is the V-shaped unfolded state. The direction and pitch attitude of the fuselage can be controlled by the differential deflection of the two sets of tail fins 22.

[0056] Furthermore, the folding design, in conjunction with the wing 21, further reduces the payload space and enhances mission flexibility; the V-tail 22 combines lift provision and attitude control functions, simplifies the design compared to traditional structures, reduces aerodynamic drag, improves attitude adjustment accuracy through differential control, and its modular structure facilitates maintenance and replacement.

[0057] A battery pack 6 for power supply is fixedly installed inside the battery compartment 14.

[0058] Here, a dedicated installation chamber is reserved in the battery compartment 14. The battery pack 6 adopts a modular design and is connected to various electrical devices through standardized interfaces. The compartment walls are made of heat-insulating and flame-retardant materials, and the interior is equipped with a buffer and shock-absorbing structure and reserved heat dissipation holes. The battery pack 6 supports quick disassembly and charging.

[0059] Furthermore, the large-capacity battery pack ensures the target drone can operate for extended periods, meeting the needs of long-range training; the modular design improves the turnaround efficiency of the target drone, while the heat-insulating, flame-retardant, and buffered heat dissipation structure enhances battery safety, extends service life, and reduces waste.

[0060] An enhancement device 7 for receiving signals is fixedly installed inside the stern compartment 16.

[0061] Here, the enhancement device 7 includes two optional modules: an active signal enhancer and a corner reflector. Both are fixed to the mounting base of the tail compartment 16 via a standardized interface and can be flexibly replaced according to training needs. The bulkhead of the tail compartment 16 is made of a wave-transparent material, and the mounting base has reserved adjustment space, which can finely adjust the device angle to improve the signal simulation accuracy.

[0062] Furthermore, the dual-module design adapts to different accuracy and cost requirements. The active signal enhancer can realistically simulate various stealth target signals, while the corner reflector further reduces the cost of use. The standardized interface facilitates equipment replacement, and the wave-transparent bulkhead ensures stable signal transmission, improving the practicality and versatility of the target drone.

[0063] In this utility model, during the mounting preparation stage: the target drone is suspended below the carrier aircraft by universal lifting lugs. At this time, the wings 21 and tail fins 22 are folded to reduce the space occupied by the mounting and facilitate batch carrying by the carrier aircraft; the battery pack 6 is fully charged, and the controller 5, signal enhancement equipment 7, etc. are in standby mode to ensure rapid start-up after deployment.

[0064] Deployment Phase: After the carrier aircraft arrives at the designated airspace, the target drone is released through the separation mechanism. Controller 5 is simultaneously activated, sending deployment commands to the first and second drive components. The output end of the first hydraulic cylinder 131 extends, and through the linkage of the first hinge rod 133, connecting block 134, and second hinge rod 135, it drives the wing 21 to unfold from a folded state to a horizontal state, providing lift for flight. The output end of the second hydraulic cylinder 151 retracts, and through the U-shaped rod 153, actuating rod 156, and rotating rod 155, it drives the tail fin 22 to unfold from a folded state to a V-shape. At the same time, the pull ring 4 of the nose compartment 11 is securely connected to the carrier aircraft's tow rope, completing the deployment process.

[0065] Flight attitude control phase: After the target drone is deployed, it is towed by the carrier aircraft via a tow rope. Battery pack 6 continuously supplies power to the controller 5, hydraulic cylinders, and other equipment. The attitude sensor in controller 5 collects the fuselage's flight attitude data in real time. Based on the difference between preset parameters and the actual attitude, the flight control computer sends control commands to the motor driver: by adjusting the extension and retraction of the first hydraulic cylinder 131, the aileron surface 213 is deflected in conjunction with the target drone, controlling the roll attitude of the fuselage; by adjusting the extension and retraction of the second hydraulic cylinder 151, the two sets of V-tails 22 are driven to deflect differentially, controlling the direction and pitch attitude of the fuselage, ensuring the stability of the target drone's attitude during high-speed towing, and adapting to the flight characteristic simulation requirements of advanced fighter jets.

[0066] Stealth target simulation phase: The target drone adopts a multi-faceted stealth shape design, combined with the stealth coating on the main wing surface 212 of the wing 21, which greatly reduces its own radar cross-section; the signal enhancement equipment 7 in the tail compartment 16 works synchronously. If an active signal enhancer is selected, it can generate radar echo signals of various frequencies to accurately simulate the signal characteristics of various stealth aircraft; if a low-cost corner reflector is selected, it can directly enhance the ground radar echo, realize basic stealth target simulation, and adapt to different training accuracy requirements.

[0067] Mission Recovery Phase: After the training mission is completed, the carrier aircraft tows the target drone back to the designated recovery area via a tow rope. Controller 5 sends a folding command, driving the wings 21 and tail 22 to fold back to their original positions. The target drone is then recovered via the recovery mechanism. After recovery, damaged sections or equipment can be quickly replaced using the modular, detachable connection structure. The battery pack 6 is recharged, and the target drone can be put back into use after simple maintenance, reducing the cost per mission.

[0068] The above description of the embodiments is only for the purpose of helping to understand the method and core idea of ​​this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made to this utility model without departing from the principle of this utility model, and these improvements and modifications also fall within the protection scope of the claims of this utility model.

Claims

1. A low-cost, air-dropped, towed stealth target drone, characterized in that: The target drone includes a section assembly (1) and a control surface assembly (2), wherein the control surface assembly (2) is movably mounted on the section assembly (1); The module assembly (1) consists of a nose section (11), a control section (12), a first equipment section (13), a battery section (14), a second equipment section (15), and a tail section (16), and the nose section (11), control section (12), first equipment section (13), battery section (14), second equipment section (15), and tail section (16) can be detached and connected to each other; The control surface assembly (2) consists of a wing (21) and a tail (22). The wing (21) is connected to a first drive unit in the first equipment compartment (13), and the tail (22) is connected to a second drive unit in the second equipment compartment (15).

2. The low-cost, air-dropped, towed stealth target drone according to claim 1, characterized in that: The nose section (11), control section (12), first equipment section (13), battery section (14), second equipment section (15) and tail section (16) are all connected by a connecting frame (3).

3. A low-cost, air-dropped, towed stealth target drone according to claim 2, characterized in that: A pull ring (4) for connecting to an external tow rope is fixedly installed at the end of the nose section (11).

4. A low-cost, air-dropped, towed stealth target drone according to claim 3, characterized in that: The control cabin (12) is fixedly equipped with a controller (5). When the controller (5) is working, the first drive component and the second drive component drive the wings (21) and tail (22) to rotate respectively.

5. A low-cost, air-dropped, towed stealth target drone according to claim 4, characterized in that: The first driving component includes a first hydraulic cylinder (131) disposed in the first equipment compartment (13). The end of the first hydraulic cylinder (131) is hinged to the first equipment compartment (13). A slide groove (132) is provided on the first equipment compartment (13). A first hinge rod (133) is slidably connected in the slide groove (132). A connecting block (134) is provided on the first equipment compartment (13). One end of the first hinge rod (133) is hinged to the connecting block (134), and the other end of the first hinge rod (133) is hinged to the output end of the first hydraulic cylinder (131).

6. A low-cost, air-dropped, towed stealth target drone according to claim 5, characterized in that: The number of wings (21) is two sets. The two sets of wings (21) rotate symmetrically on the first equipment compartment (13). The wings (21) are composed of wing roots (211), main wing surfaces (212) and aileron surfaces (213) rotatably connected to the main wing surfaces (212). The two sets of wing roots (211) are each hinged with a second hinge rod (135). The other end of the two sets of second hinge rods (135) is hinged to the connecting block (134). When the output end of the first hydraulic cylinder (131) extends, the wings (21) are in the first working area. When the output end of the first hydraulic cylinder (131) retracts, the wings (21) are in the second working area.

7. A low-cost, air-dropped, towed stealth target drone according to claim 6, characterized in that: The second driving component includes a second hydraulic cylinder (151) disposed in the second equipment compartment (15). A mounting bracket (152) is fixedly installed in the second equipment compartment (15). The second hydraulic cylinder (151) is hinged to the mounting bracket (152). A U-shaped rod (153) is fixedly connected to the output end of the second hydraulic cylinder (151). Grooves (154) are symmetrically provided on the U-shaped rod (153).

8. A low-cost, air-dropped, towed stealth target drone according to claim 7, characterized in that: The tail fins (22) are in two sets. The two sets of tail fins (22) rotate symmetrically on the second equipment compartment (15). The second equipment compartment (15) has a rotating rod (155) that rotates symmetrically. The rotating rod (155) has an integrally formed a lever (156) that matches the groove (154). The end of the lever (156) is inserted into the groove (154). The two sets of tail fins (22) are fixedly connected to the rotating rod (155). When the output end of the second hydraulic cylinder (151) extends, the tail fins (22) are in the first working area. When the output end of the second hydraulic cylinder (151) retracts, the tail fins (22) are in the second working area. When the tail fins (22) are in the second working area, the two sets of tail fins (22) are arranged in a V-shape.

9. A low-cost, air-dropped, towed stealth target drone according to claim 1, characterized in that: A battery pack (6) for power supply is fixedly installed inside the battery compartment (14).

10. A low-cost, air-dropped, towed stealth target drone according to claim 1, characterized in that: The tail section (16) is equipped with a signal enhancement device (7) for receiving signals.

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