A folding tail wing device of a gun-launched unmanned aerial vehicle and a gun-launched unmanned aerial vehicle

Abstract

The application discloses a folding tail wing device of a gun-launched unmanned aerial vehicle, which comprises four sets of folding wings, locking tongues, supports, rotating shafts and torsional springs, the four supports are uniformly distributed on the fuselage, the folding wings are outside the fuselage, the inner and outer surfaces of the folding wings are both circular arc surfaces, and the folding wings are connected with the supports through the rotating shafts; the torsional springs adopt 45-degree multi-turn torsional spring structures, are sleeved on the rotating shafts, abut against the fuselage at one end, and abut against the inner side planes of the folding wings at the other end; the locking tongues are fixed with the folding wings, and the supports are connected with the fuselage at the positions where gaps exist; the width of the locking tongues is consistent with the width of the gaps of the fuselage, and the locking tongues are self-locked after being embedded in the gaps. The application further discloses a gun-launched unmanned aerial vehicle. The application can be widely applied to various combat environments such as land battlefield, sea battlefield and air battlefield, and the initial speed and flight distance of the unmanned aerial vehicle can be effectively improved by adopting a mortar launcher, so that long-distance rapid combat can be realized.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a folding tail fin device for a gun-launched UAV and the gun-launched UAV itself. Background Technology

[0002] Mortars are simple in structure, easy to operate and maintain, and highly mobile, making them suitable for combat in various terrains and topographical conditions. Applying drones to mortar platforms is an innovation and experiment, as well as a research and expansion of technological applications, which can improve the overall combat capability of weapons. The engineering application of mortar-launched drones will bring considerable benefits to the user units and also improve the overall combat effectiveness of my country's drone platforms. The high-low pressure launch technology of mortar-launched drones can fully utilize the portability of mortars, improve the deployment efficiency of drones, and extend the combat time of drones. Portability allows for large-scale use in urban warfare; high deployment efficiency enables the rapid construction of dense drone reconnaissance networks and real-time feedback of the battlefield environment; and longer combat time ensures that drones can conduct more complex battlefield penetrations and more accurate target destruction. Mortar-launched drones help to improve the system architecture of future ground unmanned equipment, promote the leapfrog development and transformation of the army, and enhance the army's system combat capability. In recent years, with the further development of new micro-power unit technology, seeker technology that integrates detectors and guidance functions, dual-mode guidance technology of infrared imaging and millimeter wave homing, anti-jamming technology, and information network technology, mortar-launched UAVs have broad application prospects.

[0003] Artillery-launched unmanned aerial vehicles (UAVs) are a product of the organic integration of UAV technology and ammunition technology. Launched by various artillery pieces, rocket launchers, and other barrel-mounted weapons, they conduct patrol flights in the air to perform combat missions such as intelligence reconnaissance, target designation, information relay, area control, precision strikes, and damage assessment. Artillery-launched UAVs combine the characteristics of cruise missiles and UAVs. Compared with cruise missiles, they have longer loiter time, wider range of action, and stronger sustained deterrence capabilities. They can detect and attack various concealed targets, reverse-slope targets, and time-sensitive targets. However, because the flight stability problem of the UAV from the moment it leaves the muzzle to the moment its propeller unfolds has not been completely solved, the research on the tail fin device of existing artillery-launched UAVs cannot ensure long-term service reliability.

[0004] Applying drones to mortar platforms is a completely new endeavor, representing both research and expansion of drone technology, and can reasonably improve the overall combat capability of weapons. Designing the tail fins for mortar-launched drones is an unprecedented attempt, capable of addressing issues such as poor overall weapon capabilities, low initial takeoff velocity of drones, and unstable flight after being launched from a mortar. Summary of the Invention

[0005] The purpose of this invention is to provide a folding tail fin device for a gun-launched unmanned aerial vehicle (UAV) and the UAV itself, so as to improve the flight stability of the UAV from the stage after launch away from the gun muzzle to the stage of propeller deployment, and solve the problems of poor overall capability of existing weapons, low initial velocity of UAV takeoff, and unstable flight of gun-launched UAVs.

[0006] The technical solution to achieve the purpose of this invention is as follows: a folding tail fin device for a gun-launched unmanned aerial vehicle, characterized in that it includes four sets of folding wings, a locking tongue, supports, a rotating shaft, and a torsion spring. The four supports are evenly distributed on the fuselage. The folding wings are on the outside of the fuselage, with both the inner and outer surfaces being arc surfaces, and are connected to the supports through the rotating shaft. The torsion spring adopts a 45° multi-turn torsion spring structure, which is sleeved on the outside of the rotating shaft, with one end abutting against the fuselage and the other end abutting against the inner plane of the folding wing. The locking tongue is fixed to the folding wing, and there is a notch at the connection between the support and the fuselage. The width of the locking tongue is consistent with the width of the notch in the fuselage. When the locking tongue is inserted into the notch, it completes self-locking.

[0007] Furthermore, the support includes a central cuboid and two wedge-shaped locking members arranged at the top and bottom. The locking members have a circular groove at their center with the same diameter as the rotating shaft. The rotating shaft and the support with the locking members are connected by a keyway.

[0008] A gun-launched unmanned aerial vehicle (UAV) includes a UAV body and a folding tail fin device for stabilizing flight when the UAV leaves the gun muzzle. The UAV body comprises a communication system, a power system, a servo system, a battery system, an optoelectronic system, a damage system, and a launch system. Each of the power system, servo system, battery system, optoelectronic system, and damage system has a central circular hole. The communication system and launch system are respectively connected to the beginning and end of a long cylindrical shaft. The power system, servo system, battery system, optoelectronic system, and damage system are arranged from head to tail within the UAV and connected by the long cylindrical shaft passing through the circular hole. The folding tail fin device is located at the tail of the UAV and is directly connected to the launch system.

[0009] The communication system is used to synchronize the UAV's position and heading, facilitating flight mission planning by the control center. It includes a positioning module and a flight control module. The power system drives the UAV, with the upper and lower wings of the UAV connected to the motor spindle. It includes a motor module and a wing connection module. The servo system is used for attitude and motion control of the UAV. It includes an attitude control module and a motion control module. The battery system provides operating power for the UAV, providing energy support during the cruise phase. It includes a power supply module and a power supply module. The optoelectronic system is used to collect images and locations of the target and upload them to the control center for guidance of guided weapons. The damage system, equipped with explosives or electromagnetic shielding devices, is located at the tail of a long cylindrical shaft and is used to perform damage missions planned by the control center. It includes a damage module. The launch system is used to propel the UAV to the designated combat area, providing initial kinetic energy. It includes high- and low-voltage booster modules.

[0010] Furthermore, when not launched, the UAV is placed in the muzzle in a folded state. At this time, the folded wings are folded, the torsion springs fitted outside the pivot are compressed, the folded wings are in contact with the fuselage, and the torsion springs are in a torsional energy storage state, constrained by the muzzle wall.

[0011] After the drone is launched by the launch system, the folding wing is separated from the muzzle and is instantly twisted by the torsion spring. The torsion spring immediately releases its potential energy and uses the torsional torque to rotate the folding wing to the unfolded position. When the end face of the locking tongue is inserted into the notch of the fuselage, the folding wing self-locks, completing the unfolding of the folding wing.

[0012] During flight, the communication system synchronizes the UAV's position and heading, the power system drives the UAV's operation, the servo system controls the UAV's attitude and movement, the battery system provides the UAV with operating power, the optoelectronic system collects images and locations of the target and uploads them to the control center to provide guidance for guided weapons, and the damage system completes the damage mission.

[0013] Compared with existing technologies, the significant advantages of this invention are: (1) It adopts a mortar launching platform, which simplifies the takeoff process and increases the initial takeoff velocity. The tail fins are deployed when the UAV leaves the muzzle after launch, which effectively improves the flight stability of the UAV from the stage of leaving the muzzle to the stage of propeller deployment, enabling long-range and high-efficiency combat. (2) The mechanical folding tail fins are deployed using the torsional torque of torsion springs, which meets the requirements of the UAV's gun-launched structure while greatly reducing the number of electronic components, improving the stability and reliability of the UAV during low-load launch. (3) The folding tail fins are used as the tail structure of the UAV. This structure has high stability, good maneuverability, fast retraction speed and compact structure, which improves the UAV's adaptability to complex battlefield environments. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the tail fin deployment state of the present invention.

[0015] Figure 2 This is a schematic diagram of the support of the present invention.

[0016] Figure 3 This is a schematic diagram of the overall structure of a gun-launched unmanned aerial vehicle according to the present invention.

[0017] Figure 4 This is a schematic diagram of the overall drone after removing part of the outer shell according to the present invention.

[0018] Figure 5 This is a schematic diagram of the tail fin folded state of the present invention. Implementation

[0019] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0020] Combination Figure 1 The folding tail wing device 15 includes a folding wing 1, a locking tongue 2, a support 3, a rotating shaft 4, and a torsion spring 5. There are four folding wings 1, four locking tongues 2, four supports 3, four rotating shafts 4, and four torsion springs 5. The four supports 3 are evenly distributed on the fuselage 6. The folding wing 1 is set on the outside of the fuselage 6, and both its inner and outer surfaces are arc surfaces. The folding wing 1 is connected to the support 3 through the rotating shaft 4. The torsion spring 5 adopts a 45° multi-turn torsion spring structure, which is sleeved on the outside of the rotating shaft 4. One end abuts against the fuselage 6, and the other end abuts against the inner plane of the folding wing 1. The locking tongue 2 is fixed to the folding wing 1. There is a notch at the connection between the support 3 and the fuselage 6. The width of the locking tongue 2 is the same as the width of the notch in the fuselage 6. When the locking tongue 2 is inserted into the notch, it completes self-locking.

[0021] Combination Figure 2 The support 3 includes a central cuboid and two wedge-shaped locking elements 7 arranged above and below. The locking elements 7 have a circular groove of the same diameter in the center. The rotating shaft 4 and the support 3 with the locking elements 7 are mechanically connected by a keyway.

[0022] Combination Figure 3 The gun-launched unmanned aerial vehicle (UAV) of the present invention includes a UAV body and a foldable tail fin for stabilizing flight when the UAV leaves the muzzle of a gun. The gun-launched UAV body consists of a communication system 8, a power system 9, a servo system 10, a battery system 11, an optoelectronic system 12, a damage system 13, a launch system 14, and a foldable tail fin device 15. The power system 9, servo system 10, battery system 11, optoelectronic system 12, and damage system 13 each have a central circular hole. The communication system 8 and the launch system 14 are respectively connected to the beginning and end of a long cylindrical shaft. The power system 9, servo system 10, battery system 11, optoelectronic system 12, and damage system 13 are arranged from head to tail inside the UAV and connected by the long cylindrical shaft that connects the communication system 8 and the launch system 14, passing through the circular holes.

[0023] Combination Figure 4Furthermore, the communication system 8 is used to synchronize the UAV's position and heading, facilitating flight mission planning by the control center, and includes a positioning module and a flight control module; the power system 9 is used to drive the UAV, with the upper and lower wings of the UAV connected to the motor spindle, and includes a motor module and a wing connection module; the servo system 10 is used for UAV attitude and motion control, including an attitude control module and a motion control module; the battery system 11 is used to provide operating energy for the UAV, providing energy support during the UAV's cruise phase, and includes a power supply module and a power distribution module; the photoelectric system 12 is used to collect data from the UAV. Images and locations of the reconnaissance targets are uploaded to the control center, which can provide guidance for guided weapons when necessary. The damage system 13 mainly carries explosives or electromagnetic shielding devices and is located at the tail of the long cylindrical shaft. It is used to perform damage tasks assigned by the control center and mainly includes damage modules. The launch system 14 is used to propel the UAV to the designated combat area and provide initial kinetic energy to the UAV. It mainly includes high and low pressure booster modules. The folding tail fin device 15 is used to make the projectile fly more stably along the desired trajectory. It is directly connected to the launch system 14 and is located at the tail of the UAV.

[0024] Combination Figure 5 When not in use, the drone is folded and placed in the muzzle. When the folding wing 1 is folded, the torsion spring 5 that is sleeved on the pivot 4 is compressed. At this time, the folding wing 1 is in contact with the fuselage, and the torsion spring 5 is in a torsional energy storage state. At this time, the drone can be loaded into the firing muzzle and constrained by the barrel wall.

[0025] After the drone is launched by the launch system 14, the folding wing 1 is separated from the muzzle and is instantly twisted by the torsion spring 5. The torsion spring 5 immediately releases potential energy and uses the torsional torque to rotate the folding wing 1 to the unfolded position. When the end face of the locking tongue 2 is inserted into the notch of the fuselage 6, the folding wing 1 self-locks and completes the unfolding of the folding wing 1.

[0026] In summary, the folding tail fin of this invention facilitates the folding and storage of the UAV during transport and storage, resulting in high space utilization and convenient transportation and storage. The folding fin can be directly retracted and covered on the outer wall of the fuselage, allowing it to be directly loaded into a mortar for firing without assembly or adjustment, effectively reducing pre-launch preparation time. Operation is simple, and no launch site or runway is required during launch, reducing dependence on launch sites. It can be rapidly deployed in harsh battlefield environments, greatly improving the flexibility and combat capability of the UAV in complex battlefield environments.

[0027] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0028] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these modifications and improvements all fall within the protection scope of this application. Therefore, the protection scope of this application should be determined by the appended claims.

Claims

1. A gun-launched unmanned aerial vehicle, characterized in that: Includes the drone airframe and a folding tail fin device (15) for stabilizing the drone's flight when it leaves the muzzle of the gun; The folding tail fin device includes four folding wings (1), a locking tongue (2), a support (3), a rotating shaft (4), and a torsion spring (5). The four supports (3) are evenly distributed on the fuselage (6). The folding wings (1) are on the outside of the fuselage (6), with both the inner and outer surfaces being arc surfaces. They are connected to the supports (3) through the rotating shaft (4). The torsion spring (5) adopts a 45° multi-turn torsion spring structure, which is sleeved on the outside of the rotating shaft (4). One end abuts against the fuselage (6), and the other end abuts against the inner plane of the folding wing (1). The locking tongue (2) is fixed to the folding wing (1). There is a notch at the connection between the support (3) and the fuselage (6). The width of the locking tongue (2) is the same as the width of the notch in the fuselage (6). When the locking tongue (2) is inserted into the notch, it completes self-locking. The UAV body consists of a communication system (8), a power system (9), a servo system (10), a battery system (11), an optoelectronic system (12), a damage system (13), and a launch system (14). The power system (9), servo system (10), battery system (11), optoelectronic system (12), and damage system (13) all have a round hole in the center. The communication system (8) and launch system (14) are respectively connected to the beginning and end of a long cylindrical shaft. The power system (9), servo system (10), battery system (11), optoelectronic system (12), and damage system (13) are arranged inside the UAV from head to tail and are connected by the long cylindrical shaft that connects the communication system (8) and launch system (14) through the round hole. The folding tail fin device (15) is located at the tail of the UAV and is directly connected to the launch system (14). The communication system (8) is used to synchronize the UAV's position and heading, facilitating the control center to formulate flight missions, and includes a positioning module and a flight control module; the power system (9) is used to drive the UAV, with the upper and lower wings of the UAV connected to the motor spindle, and includes a motor module and a wing connection module; the servo system (10) is used for the attitude and motion control of the UAV, and includes an attitude control module and a motion control module; the battery system (11) is used to provide working energy for the UAV and provide energy support during the UAV's cruise phase, and includes a power supply module and a power supply module; the optoelectronic system (12) is used to collect images and locations of the reconnaissance targets and upload them to the control center to provide guidance for guided weapons; the damage system (13) is loaded with explosives or electromagnetic shielding devices and is located at the tail of the long cylindrical shaft to perform damage tasks assigned by the control center, and includes a damage module; the launch system (14) is used to propel the UAV to the designated combat area and provide initial kinetic energy for the UAV, and includes high and low voltage booster modules.

2. The artillery-launched unmanned aerial vehicle according to claim 1, characterized in that: The support (3) includes a cuboid in the middle and two wedge-shaped locking parts (7) arranged on the top and bottom. The locking parts (7) have a circular groove with the same diameter as the shaft at the center. The shaft (4) and the support (3) with the locking parts (7) are connected by a keyway.

3. The artillery-launched unmanned aerial vehicle according to claim 1, characterized in that: When not launched, the UAV is placed in the muzzle in a folded state. At this time, the folding wing (1) is folded, the torsion spring (5) sleeved on the pivot (4) is compressed, the folding wing (1) is in contact with the fuselage, and the torsion spring (5) is in a torsion energy storage state and is constrained by the muzzle wall. After the UAV is launched by the launch system (14), the folding wing (1) is separated from the muzzle and is instantly twisted under the action of the torsion spring (5). The torsion spring (5) immediately releases potential energy and uses the torsional torque to rotate the folding wing (1) to the unfolded position. When the end face of the locking tongue (2) is embedded in the notch of the fuselage (6), the folding wing (1) locks itself and the folding wing (1) unfolds. During flight, the communication system (8) synchronizes the UAV's position and heading, the power system (9) drives the UAV, the servo system (10) controls the UAV's attitude and movement, the battery system (11) provides the UAV with working energy, the optoelectronic system (12) collects images and locations of the target being investigated and uploads them to the control center to provide guidance for the guided weapon, and the damage system (13) completes the damage mission.

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