Quick unfolding propeller for barrel type launching unmanned aerial vehicle and barrel type launching unmanned aerial vehicle

Abstract

The utility model provides a quick unfolding propeller for a barrel type launching unmanned aerial vehicle and the barrel type launching unmanned aerial vehicle. The propeller comprises a propeller clamp and two blades connected to the two ends, and the propeller clamp comprises a propeller clamp seat, two torsional springs, a first rotating shaft and a second rotating shaft. The torsional spring penetrates through the first rotating shaft and is mounted in the paddle holder, one end of the torsional spring is hooked on the paddle holder, and the other end of the torsional spring is hooked on the paddle. The paddle can rotate around the second rotating shaft relative to the paddle clamping seat under the action of the torsion spring and automatically move from a folding position to an unfolding position, the paddle is parallel to the fuselage of the unmanned aerial vehicle at the folding position, and the paddle is perpendicular to the fuselage at the unfolding position. And the paddle clamp seat is provided with a stop part, and the paddle is limited after being unfolded in place so as to prevent the paddle from unfolding and rotating under the influence of airflow. The paddle does not shake randomly during transportation of the unmanned aerial vehicle; during launching, the blades can be quickly unfolded under the restoring force of the torsional spring; after being unfolded, the paddles are blocked by the blocking parts and cannot rotate and shake in the unfolding direction due to the influence of airflow, and the flight reliability is guaranteed.

Description

Technical Field

[0001] The utility model belongs to the technical field of barrel-type launching unmanned aerial vehicles, and in particular relates to a fast-expanding propeller for barrel-type launching unmanned aerial vehicles and a barrel-type launching unmanned aerial vehicle comprising the propeller. Background Art

[0002] The flight power of small drones is provided by the wind pressure generated by the rotation of the propeller driven by the motor. Generally, an integral propeller is used, which refers to a propeller with two blades connected at the root. Such a power device is not easy to store and transport after installation. Due to the wide blades, it is easy to cause damage to the blade tip and blade edge during storage or transportation, thereby affecting the propeller blade efficiency, reducing the propeller efficiency, and causing the drone's flight performance to decline.

[0003] The canister-launched folding-wing UAV has attracted much attention due to its advantages over fixed-wing UAVs, such as small size, easy to carry, and flexible tactical use. Compared with fixed-wing UAVs, the power system of canister-launched UAVs has higher requirements during installation and transportation. Canister-launched UAVs cannot be equipped with integral propellers due to the size limitation of the launch canister wall. Therefore, the propellers of canister-launched UAVs often use folding blades. When the UAV is in the folded state in the launch canister, the blades are in the stowed position. After the UAV leaves the launch canister, the blades unfold and work.

[0004] For the sake of ease of control, the blades of the current barrel-launched drones are loose and free after installation. When they are in the launch barrel, there is no locking force. During transportation, the blades will shake and collide with the barrel wall, causing damage to both the blades and the barrel wall. After the drone leaves the barrel, the blades are unfolded by the centrifugal force brought by the operation of the motor. Since the motor speed cannot be increased quickly instantly, the blades cannot be thrown away quickly, which cannot meet the demand for rapid deployment of the blades. In addition, since the blades are not locked when they are unfolded, there will be axial airflow causing the blades to shake at the low speed stage of the drone, which can easily affect the thrust and is not conducive to the reliable flight of the drone. Utility Model Content

[0005] The purpose of the utility model is to solve the technical problems existing in the prior art that the propeller blades of a barrel-launched UAV are loose and free after installation, resulting in damage to the blades and the barrel wall during transportation of the UAV, the blades cannot be quickly deployed, and the thrust is easily affected by the axial airflow after deployment. A fast-deployable propeller for a barrel-launched UAV and a barrel-launched UAV including the propeller are provided.

[0006] To achieve the above purpose, the technical solution provided by the utility model is:

[0007] A fast-expanding propeller for a barrel-type launching UAV, which is special in that it comprises a propeller clamp and two propeller blades symmetrically connected at both ends of the propeller clamp, wherein the propeller clamp comprises a propeller clamp seat, two torsion springs, two first rotating shafts and two second rotating shafts;

[0008] The paddle clamp seat is used to be connected to the motor shaft of the drone extending along the length direction of the drone at the tail of the drone body, so as to rotate under the drive of the motor;

[0009] Two torsion springs respectively pass through the two first rotating shafts and are symmetrically installed in the paddle clamp seat at both ends of the paddle clamp seat, one end of the torsion spring is hooked on the paddle clamp seat, and the other end is hooked on the paddle blade;

[0010] The second rotating shaft is located outside the first rotating shaft in the width direction of the UAV, and the two propeller blades are respectively connected to the propeller clamp seat through the second rotating shaft, and can rotate around the second rotating shaft relative to the propeller clamp seat under the action of the torsion spring, and automatically move from the stowed position to the deployed position. In the stowed position, the propeller blades are parallel to the fuselage of the UAV, and in the deployed position, the propeller blades are perpendicular to the fuselage;

[0011] The paddle clamp seat is provided with a stopper, which is used to limit the position of the paddle after the paddle is unfolded to prevent the paddle from unfolding and rotating under the influence of airflow.

[0012] Furthermore, the paddle clamp seat is provided with a motor shaft mounting hole extending along the length direction of the UAV and a motor shaft fastening hole extending perpendicular to the motor shaft mounting hole. The motor shaft of the UAV is inserted into the motor shaft mounting hole and is locked by a set screw passing through the motor shaft fastening hole.

[0013] Furthermore, the pulp clamp seat is an integrally processed component, with grooves processed at both ends, the torsion spring is located in the groove, and the first rotating shaft and the second rotating shaft pass through two side walls of the groove.

[0014] Furthermore, the stopping portion is a bottom wall of the groove.

[0015] Furthermore, the first rotating shaft and the second rotating shaft are both bolts, which are fixed by matching nuts.

[0016] Furthermore, the axis of the first rotating shaft and the axis of the second rotating shaft are located in the same plane.

[0017] Furthermore, a weight-reducing hole is provided on the pulp clamp seat.

[0018] A barrel-launched UAV is special in that it comprises a fuselage, wings, and the above-mentioned fast-deployable propeller for the barrel-launched UAV.

[0019] The advantages of the utility model are:

[0020] 1. The utility model is used for the rapid deployment propeller of the barrel-type launching UAV. The torsion spring and the blade are connected to the paddle clamp seat. One end of the torsion spring is hooked on the paddle clamp seat, and the other end is hooked on the blade. The blade can rotate relative to the paddle clamp seat under the action of the torsion spring and automatically move from the stowed position to the deployed position. Therefore, when the propeller is in the stowed position in the launch tube, the torsion spring is twisted and compressed, and the blade is subjected to the torsion force of the torsion spring, so it is tightened and located in the launch tube under the constraint of the tube wall. The blade will not shake at will during the transportation of the UAV; when the UAV is launched, the blade can be quickly deployed under the action of the torsion spring restoring force, meeting the UAV flight's demand for rapid deployment of the blade; after the blade is deployed, it is blocked by the stopper. In the low-speed rotation stage, the blade will not rotate and shake in the deployment direction due to the influence of airflow, and the blade thrust is not easily affected by airflow, which can ensure the reliability of the UAV flight.

[0021] 2. The propeller clamp seat of the utility model is an integrally processed component, and grooves are respectively provided at both ends to realize the installation of the stopper, the torsion spring and the propeller blade, so that the propeller can be easily disassembled and assembled with high efficiency.

[0022] 3. Compared with the existing barrel-launched UAV, the barrel-launched UAV of the utility model is equipped with a quick-deployment propeller, so that the propeller blades can be locked in the stowed position, the blades can be quickly deployed during launch, and the positioning and locking can be achieved after deployment. This ensures the integrity of the UAV blades, reduces the difficulty of transporting the UAV, and the UAV can quickly build up power. At the same time, the flight reliability of the UAV is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The features and advantages of the present invention will become more easily understood through the following description with reference to the accompanying drawings, which are not drawn to scale and some features are enlarged or reduced to show details of specific components. In the accompanying drawings:

[0024] Figure 1 It is a schematic stereoscopic diagram of the fast-deployable propeller for the barrel-launched UAV of the utility model when the blades are in the stowed position;

[0025] Figure 2 It is a schematic stereoscopic diagram of the fast-deployable propeller for the barrel-launched UAV of the utility model when the blades are in the deployed position;

[0026] Figure 3 yes Figure 1 A cross-sectional view showing a torsion spring mounting structure;

[0027] Figure 4 It is a schematic three-dimensional diagram of the pulp clamp seat in the utility model. Figure 1 ;

[0028] Figure 5 It is a schematic three-dimensional diagram of the pulp clamp seat in the utility model. Figure 2 ;

[0029] Figure 6 It is a schematic three-dimensional diagram of the torsion spring in the utility model.

[0030] In the figure: 1-paddle clamp; 2-paddle blade; 3-paddle clamp seat, 31-stopper, 32-first rotating shaft mounting hole, 33-second rotating shaft mounting hole, 34-motor shaft mounting hole, 35-motor shaft fastening hole, 36-groove, 361-side wall of the groove, 362-bottom wall of the groove, 37-weight reduction hole; 4-torsion spring. DETAILED DESCRIPTION

[0031] The present invention will be described in detail below with reference to the accompanying drawings by means of exemplary embodiments of the present invention. It should be noted that the following detailed description of the present invention is only for the purpose of illustration, and is not intended to limit the present invention.

[0032] The utility model provides a fast-deployable propeller for a barrel-launched UAV and a barrel-launched UAV comprising the propeller. The fast-deployable propeller is used to be installed at the tail of the fuselage of the barrel-launched UAV. When the UAV is stored in the launching barrel, the blades are in a retracted state to save space; when the UAV is launched from the barrel, the blades are unfolded and rotated under the drive of a motor, providing propulsion for the UAV flight.

[0033] First, the fast-deployable propeller for barrel-type launching UAV provided by the utility model is described.

[0034] Reference Figure 1 and Figure 2 As an exemplary embodiment of the utility model, a fast-deployable propeller for a barrel-launched UAV includes a paddle clamp 1 and two paddle blades 2 symmetrically connected at both ends of the paddle clamp 1. The paddle clamp 1 can be connected to the motor shaft of the UAV. In this embodiment, the motor shaft extends along the length direction of the UAV. The paddle blades 2 can be connected to the motor shaft of the UAV. Figure 1 Stowed position shown Figure 2 When the drone is in the launch tube, it is in the deployed position. Figure 1 When the drone leaves the launch tube, it is in Figure 2 In the state, the propeller rotates together with the propeller clamp 1 under the drive of the UAV motor to provide propulsion. In this embodiment, the propeller rotates in a plane perpendicular to the fuselage.

[0035] Now combine Figure 3The paddle clamp 1 includes a paddle clamp seat 3, two torsion springs 4, two first rotating shafts (not shown in the figure) and two second rotating shafts (not shown in the figure). The paddle clamp seat 3 is used to be fixed to the motor shaft of the drone, the two torsion springs 4 are used to provide the deployment power of the two blades 2, and the two first rotating shafts and the two second rotating shafts are the rotation axes of the torsion springs 4 and the blades 2 respectively.

[0036] like Figure 4 and Figure 5 As shown, the slurry clamp seat 3 may be roughly rectangular, and is used to be connected to the motor shaft of the drone extending along the length direction of the drone, especially connected to be symmetrical about the axis in the length direction of the drone, so as to rotate in a plane perpendicular to the fuselage under the drive of the motor. In particular, the slurry clamp seat 3 is installed so that its own length direction is perpendicular to the length direction of the drone, and the length of the slurry clamp seat 3 may be slightly smaller than the cross-sectional size of the fuselage, so as to facilitate storage in the launch tube.

[0037] In some embodiments, to facilitate the fixed connection of the paddle clamp seat 3, the paddle clamp seat 3 is provided with a motor shaft mounting hole 34 extending along the length direction of the UAV and a motor shaft fastening hole 35 extending perpendicular to the motor shaft mounting hole 34. The motor shaft of the UAV is inserted into the motor shaft mounting hole 34 and is locked by a set screw passing through the motor shaft fastening hole 35, thereby achieving secondary fastening of the motor shaft and ensuring flight reliability.

[0038] The structure of torsion spring 4 is Figure 6 As shown in the figure, two torsion springs 4 pass through two first rotating shafts respectively and are symmetrically installed in the pulp clamp seat 3 at both ends of the pulp clamp seat 3. The first rotating shaft is installed in the symmetrical first rotating shaft installation holes 32 at both ends of the pulp clamp seat 3. One end of the torsion spring 4 is hooked on the pulp clamp seat 3, and the other end is hooked on the blade 2 to provide a torsional force to the blade 2.

[0039] The second rotating shaft is located outside the first rotating shaft in the width direction of the UAV, and the two blades 2 are connected to the paddle clamp seat 3 through the second rotating shaft respectively. The second rotating shaft is installed through the symmetrical second rotating shaft mounting holes 33 at both ends of the paddle clamp seat 3. In other words, the second rotating shaft mounting hole 33 is located outside the first rotating shaft mounting hole 32 in the width direction of the UAV. In particular, the axis of the first rotating shaft mounting hole 32 and the axis of the second rotating shaft mounting hole 33 are located in the same plane, that is, the axis of the first rotating shaft and the axis of the second rotating shaft are located in the same plane. The blade 2 can rotate around the second rotating shaft relative to the paddle clamp seat 3 under the action of the torsion spring 4, and automatically moves from the stowed position to the unfolded position. In the stowed position, the blade 2 is parallel to the fuselage of the UAV, and in the unfolded position, the blade 2 is perpendicular to the fuselage, and rotates in a plane perpendicular to the fuselage together with the paddle clamp seat 3 driven by the motor.

[0040] With the above structure, since the blades need to rely on the restoring force of the torsion spring to unfold after leaving the launch tube, the blades are subject to the torsional compression torque of the torsion spring when they are in the launch tube and in the retracted state, and are in the launch tube under the constraint of the tube wall. In addition, the blades are located in the tube parallel to the fuselage, so during the transportation of the UAV, the blades are not easy to shake relative to the tube wall and cause damage to the blade tip, blade edge and tube wall. At the same time, after the UAV leaves the tube, the blades are quickly unfolded by the restoring force of the torsion spring, and the unfolding speed is greatly improved compared to the unfolding by the centrifugal force generated by the rotation of the motor shaft. In addition, it should be understood that the "width direction of the UAV" mentioned in this article is only an example for the convenience of description, and it does not limit the blade clamp seat to be installed to extend along the width direction of the UAV, and its installation orientation can be in any direction.

[0041] The paddle clamp seat 3 is provided with a stopper 31, which is used to limit the paddle blade 2 after the paddle blade 2 is fully deployed, so as to prevent the paddle blade 2 from performing a rotational movement under the influence of the airflow. If the stopper 31 is not provided to block the paddle clamp seat 3 in the deployed position, then in the low-speed rotation stage, the paddle blade may rotate and shake in the deployment direction under the action of the airflow in the flight direction of the drone, overcoming the torsion force of the torsion spring, resulting in unstable thrust and affecting the flight reliability of the drone.

[0042] like Figure 5 As clearly shown in the figure, in an exemplary embodiment of the present utility model, in order to facilitate the disassembly and assembly of the propeller and improve the disassembly and assembly efficiency, the propeller clamp seat 3 is designed as an integrally processed component, and grooves 36 are symmetrically processed at both ends. The torsion spring 4 is located in the groove 36. The groove 36 is composed of two side walls 361 and a bottom wall 362. The first rotating shaft and the second rotating shaft pass through the two side walls 361 of the groove 36. Preferably, the stopper 31 can be the bottom wall 362 of the groove 36, and specifically, the outer end inclined surface of the bottom wall 362 in the length direction of the propeller clamp seat 3 cooperates with the blade 2 to block the blade.

[0043] In a specific embodiment, the first rotating shaft and the second rotating shaft are both bolts, which are fixed by matching nuts, and the bolt heads and the nuts are respectively located on two sides of the pulp clamp seat.

[0044] In addition, in order to reduce the overall weight of the propeller, the propeller clamp seat 3 can adopt a hollow design in the middle, and a weight-reducing hole 37 is opened on the propeller clamp seat 3. Two of them can be symmetrically arranged about the motor shaft mounting hole 34. The cross-sectional shape can be circular or rectangular, etc., and can optionally extend along the length direction of the UAV to reduce flight resistance.

[0045] As described above, the utility model is used for the rapid deployment propeller of the barrel-launched UAV. When the propeller is in the stowed position in the launch barrel, the torsion spring is twisted and compressed, and the blades are subjected to the torsion force of the torsion spring, so they are tightened and located in the launch barrel under the constraint of the barrel wall, and the blades will not shake at will during the transportation of the UAV; when the UAV is launched, the blades can be quickly deployed under the action of the torsion spring restoring force, meeting the demand of the UAV flight for rapid deployment of the blades; after the blades are deployed, they are blocked by the stopper. In the low-speed rotation stage, the blades will not rotate and shake in the deployment direction due to the influence of airflow, and the blade thrust is not easily affected by airflow, which can ensure the reliability of the UAV flight.

[0046] Next, the barrel-type launching UAV provided by the utility model is described.

[0047] As an exemplary embodiment of the utility model, the barrel-launched UAV includes a fuselage, wings located on both sides of the fuselage, and the above-mentioned quick-deployable propeller for the barrel-launched UAV connected to the tail of the fuselage. The installation structure of the quick-deployable propeller on the UAV can refer to the above description of the propeller and will not be repeated here.

[0048] Compared with the existing barrel-launched UAV, the barrel-launched UAV of the utility model has an additional fast-deployable propeller, which makes it possible to lock the propeller blades in the stowed position, quickly deploy the blades during launch, and position and lock them after deployment, thereby ensuring the integrity of the UAV blades, reducing the difficulty of transporting the UAV, allowing the UAV to quickly build up power, and at the same time improving the flight reliability of the UAV.

[0049] Finally, it should be noted that the features mentioned and / or shown in the above description of the exemplary embodiments of the utility model can be combined in the same or similar manner into one or more other embodiments, combined with the features in other embodiments or replace the corresponding features in other implementations. The technical solutions obtained by these combinations or replacements should also be deemed to be included in the protection scope of the utility model.

Claims

1. A fast-deployable propeller for a barrel-launched UAV, characterized in that: It comprises a paddle clamp and two paddle blades symmetrically connected at two ends of the paddle clamp, wherein the paddle clamp comprises a paddle clamp seat, two torsion springs, two first rotating shafts and two second rotating shafts; The paddle clamp seat is used to be connected to a motor shaft of the drone extending along the length direction of the drone at the tail of the drone body, so as to rotate under the drive of the motor; Two torsion springs are respectively passed through two first rotating shafts and symmetrically installed in the paddle clamp seat at two ends of the paddle clamp seat, one end of the torsion spring is hooked on the paddle clamp seat, and the other end is hooked on the paddle blade; The second rotating shaft is located outside the first rotating shaft in the width direction of the UAV, and the two blades are respectively connected to the paddle clamp seat through the second rotating shaft, and can rotate around the second rotating shaft relative to the paddle clamp seat under the action of the torsion spring, and automatically move from a stowed position to an unfolded position, in which the blades are parallel to the fuselage of the UAV, and in which the blades are perpendicular to the fuselage; The paddle clamp seat is provided with a stopper, which is used to limit the position of the paddle after the paddle is unfolded to a certain position, so as to prevent the paddle from unfolding and rotating under the influence of airflow.

2. The fast-deployable propeller for launching a UAV in a canister according to claim 1, characterized in that: The paddle clamp seat is provided with a motor shaft mounting hole extending along the length direction of the UAV and a motor shaft fastening hole extending perpendicular to the motor shaft mounting hole. The motor shaft of the UAV is inserted into the motor shaft mounting hole and is locked by a set screw passing through the motor shaft fastening hole.

3. The fast-deployable propeller for launching a UAV in a cylinder according to claim 1 or 2, characterized in that: The pulp clamp seat is an integrally processed component, with grooves processed at both ends, the torsion spring is located in the groove, and the first rotating shaft and the second rotating shaft pass through two side walls of the groove.

4. The fast-deployable propeller for launching a UAV in a canister according to claim 3, characterized in that: The stopping portion is the bottom wall of the groove.

5. The fast-deployable propeller for launching a UAV in a cylinder according to claim 1 or 2, characterized in that: The first rotating shaft and the second rotating shaft are both bolts fixed by matching nuts.

6. The fast-deployable propeller for launching a UAV in a canister according to claim 1 or 2, characterized in that: The axis of the first rotating shaft and the axis of the second rotating shaft are located in the same plane.

7. The fast-deployable propeller for launching a UAV in a canister according to claim 1 or 2, characterized in that: The pulp clamp seat is provided with a weight-reducing hole.

8. A canister-type launching UAV, characterized in that: The invention comprises a fuselage, wings, and a fast-deployable propeller for launching a tube-type unmanned aerial vehicle as claimed in any one of claims 1 to 7.

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