阅读说明：本技术 一种可旋转式多功能无人机尾翼 (Rotatable multi-functional unmanned aerial vehicle fin ) 是由 丁锋 杨少华 于 2021-09-26 设计创作，主要内容包括：本申请涉及一种可旋转式多功能无人机尾翼,属于无人机的领域,所述无人机尾翼可拆卸安装在无人机尾部,所述无人机尾翼包括一个水平尾翼和两个侧翼,两个所述侧翼转动设置于水平尾翼的两端。本申请减小了无人机尾翼受损的可能性。(The application relates to a multi-functional unmanned aerial vehicle fin of rotatable formula belongs to unmanned aerial vehicle's field, unmanned aerial vehicle fin demountable installation is at the unmanned aerial vehicle afterbody, the unmanned aerial vehicle fin includes a tailplane and two flanks, two the flank rotates and sets up in the both ends of tailplane. This application has reduced the impaired possibility of unmanned aerial vehicle fin.)

1. The utility model provides a multi-functional unmanned aerial vehicle fin of rotatable formula sets up in unmanned aerial vehicle afterbody, its characterized in that: unmanned aerial vehicle fin demountable installation is in unmanned aerial vehicle afterbody, the unmanned aerial vehicle fin includes a tailplane (1) and two flank (2), two flank (2) are rotated and are set up in the both ends of tailplane (1).

2. The rotatable multi-functional unmanned aerial vehicle fin of claim 1, characterized in that: the unmanned aerial vehicle tail part is provided with an installation rod (4) used for connecting an unmanned aerial vehicle tail wing, the unmanned aerial vehicle tail wing comprises an installation part (21) used for connecting the installation rod (4), an insertion rod (210) is fixedly connected to the installation part (21), the installation rod (4) is provided with a jack for the insertion of the insertion rod (210), and the installation rod (4) is further provided with a locking part (41) used for limiting the insertion rod (210) to be separated from the jack;

or the unmanned aerial vehicle afterbody is provided with installation pole (4) that are used for connecting the unmanned aerial vehicle fin, the unmanned aerial vehicle fin is including installation department (21) that are used for connecting installation pole (4), the rigid coupling has inserted bar (210) on installation pole (4), be provided with on installation department (21) and supply inserted bar (210) to insert the jack of establishing, still be provided with retaining member (41) that are used for restricting inserted bar (210) and break away from the jack on installation pole (4).

3. The rotatable multi-functional unmanned aerial vehicle fin of claim 2, characterized in that: retaining member (41) slide the cover and establish on installation pole (4), retaining member (41) with threaded connection can be dismantled in installation department (21), be provided with clamping piece (42) that restriction retaining member (41) break away from installation pole (4) on installation pole (4), when retaining member (41) threaded connection was on installation department (21), retaining member (41) and clamping piece (42) joint.

4. The rotatable multi-functional unmanned aerial vehicle fin of claim 1, characterized in that: the side wing (2) comprises a vertical tail wing (22), and when the fixing piece (3) limits the rotation of the side wing (2), the vertical tail wing (22) is vertical to the horizontal tail wing (1).

5. The rotatable multi-functional unmanned aerial vehicle fin of claim 1, characterized in that: the side wing (2) comprises a supporting tail wing (23) used for supporting the unmanned aerial vehicle, and the supporting tail wing (23) can be detachably supported on the ground.

6. The rotatable multi-functional unmanned aerial vehicle fin of claim 1, characterized in that: fixing pieces (3) used for limiting the rotation of the side wings (2) are arranged at two ends of the horizontal tail wing (1), each fixing piece (3) comprises a buckle (31) and a fixture block (30), the buckles (31) are fixedly connected to the side wings (2), the fixture blocks (30) are fixedly connected to the horizontal tail wing (1), and the buckles (31) are detachably buckled on the fixture blocks (30);

or both ends of horizontal tail wing (1) all are provided with and are used for restricting flank (2) pivoted mounting (3), mounting (3) are including buckle (31) and fixture block (30), buckle (31) rigid coupling is on horizontal tail wing (1), fixture block (30) rigid coupling is on flank (2), buckle (31) can be dismantled to detain and establish on fixture block (30).

7. The rotatable multi-functional unmanned aerial vehicle fin of claim 6, characterized in that: the clamping block (30) is provided with an inclined plane (300) for guiding the clamping buckle (31) to be buckled on the clamping block (30).

8. The rotatable multi-functional unmanned aerial vehicle fin of claim 1, characterized in that: and an elevator (11) is arranged on one side of the horizontal tail wing (1) far away from the mounting rod (4).

9. The rotatable multi-functional unmanned aerial vehicle fin of claim 8, characterized in that: the two elevators (11) are arranged, and the two elevators (11) are arranged along the length direction of the horizontal tail wing (1).

10. The rotatable multi-functional unmanned aerial vehicle fin of claim 1, characterized in that: the side wings (2) are hinged with the horizontal tail wing (1) through a rotating shaft (205), and a driving piece (5) used for driving the rotating shaft (205) to rotate is installed on the horizontal tail wing (1).

Technical Field

The application relates to the field of unmanned aerial vehicles, especially, relate to a multi-functional unmanned aerial vehicle fin of rotatable formula.

Background

A drone is an unmanned aerial vehicle that is operated using a radio remote control device and a self-contained program control device.

Hang down fixed wing unmanned aerial vehicle belongs to unmanned aerial vehicle's one kind, and it has combined the advantage that many rotor unmanned aerial vehicle can the VTOL on fixed wing unmanned aerial vehicle's the basis, has just superimposed many rotor unmanned aerial vehicle specific rotor system to fixed wing unmanned aerial vehicle on one's body, constitutes independent system of taking off in order to provide lift-off power. After the drooping fixed wing unmanned aerial vehicle reaches the takeoff height through the rotor system, the ailerons are used, the wing flaps guide the airflow direction, the flight mode of the unmanned aerial vehicle is changed, and finally the flight mode of the fixed wing unmanned aerial vehicle is adopted.

In view of the above-mentioned related technologies, the inventor believes that most of unmanned aerial vehicles with tail wings on the market are damaged due to the fact that the tail wings easily collide with other objects in the transportation process of the unmanned aerial vehicles because the occupied space of the tail wings is large.

Disclosure of Invention

In order to reduce the impaired possibility of unmanned aerial vehicle fin, this application provides a rotatable formula multi-functional unmanned aerial vehicle fin.

The application provides a pair of multi-functional unmanned aerial vehicle fin of rotatable formula adopts following technical scheme:

the utility model provides a multi-functional unmanned aerial vehicle fin of rotatable formula, unmanned aerial vehicle fin demountable installation is in unmanned aerial vehicle afterbody, the unmanned aerial vehicle fin includes a tailplane and two flanks, two the flank rotates and sets up in tailplane's both ends.

Through adopting above-mentioned technical scheme, when the staff need transport or accomodate unmanned aerial vehicle, dismantle the unmanned aerial vehicle fin from the unmanned aerial vehicle afterbody earlier, then rotate the flank, reduce the whole space that occupies of unmanned aerial vehicle fin, the taking in of the unmanned aerial vehicle fin of being convenient for has reduced the damaged possibility of unmanned aerial vehicle fin because of the collision, the unmanned aerial vehicle's of being convenient for transportation.

Optionally, the tail of the unmanned aerial vehicle is provided with an installation rod for connecting an unmanned aerial vehicle empennage, the unmanned aerial vehicle empennage comprises an installation part for connecting the installation rod, the installation part is fixedly connected with an insertion rod, the installation rod is provided with an insertion hole for the insertion rod to be inserted, and the installation rod is further provided with a locking member for limiting the insertion rod to be separated from the insertion hole;

or the unmanned aerial vehicle afterbody is provided with the installation pole that is used for connecting the unmanned aerial vehicle fin, the unmanned aerial vehicle fin is including the installation department that is used for connecting the installation pole, the rigid coupling has the inserted bar on the installation pole, be provided with on the installation department and supply the inserted bar to insert the jack of establishing, still be provided with the retaining member that is used for restricting the inserted bar and breaks away from the jack on the installation pole.

Through adopting above-mentioned technical scheme, realize the location of unmanned aerial vehicle fin and unmanned aerial vehicle fin through the cooperation of jack and inserted bar, then realize the fixed of unmanned aerial vehicle fin through the retaining member to install the unmanned aerial vehicle fin at unmanned aerial vehicle's tail end, the installation step is simple, and the staff of being convenient for installs the operation, convenient and fast.

Optionally, the retaining member is slided the cover and is established on the installation pole, the retaining member with threaded connection can be dismantled to the installation department, be provided with the screens piece that the restriction retaining member breaks away from the installation pole on the installation pole, when retaining member threaded connection was on the installation department, retaining member and screens piece joint.

By adopting the technical scheme, the fixed connection of the mounting rod and the mounting part is realized in a threaded connection mode, and the stability of the fixed connection of the mounting rod and the mounting part is improved.

Optionally, the side wing includes a vertical tail that is perpendicular to the horizontal tail when the fixing member limits the rotation of the side wing.

Through adopting above-mentioned technical scheme, use vertical fin to improve the stability of unmanned aerial vehicle flight.

Optionally, the flank includes the support fin that is used for supporting unmanned aerial vehicle, the support fin can be dismantled and support on the ground.

By adopting the technical scheme, when the unmanned aerial vehicle flies, the support empennages at the two ends of the horizontal empennage improve the stability of the unmanned aerial vehicle; when unmanned aerial vehicle descends, support subaerial through supporting the fin, reduced the impaired possibility of unmanned aerial vehicle.

Optionally, the two ends of the horizontal tail wing are respectively provided with a fixing piece for limiting the rotation of the side wing, each fixing piece comprises a buckle and a fixture block, the buckle is fixedly connected to the side wing, the fixture block is fixedly connected to the horizontal tail wing, and the buckle is detachably buckled on the fixture block;

or the both ends of horizontal tail all are provided with and are used for restricting flank pivoted mounting, the mounting includes buckle and fixture block, the buckle rigid coupling is on horizontal tail, the fixture block rigid coupling is on the flank, the buckle can be dismantled to detain and establish on the fixture block.

Through adopting above-mentioned technical scheme, when unmanned aerial vehicle fin ann reprints unmanned aerial vehicle afterbody, realize flank and horizontal fin's relatively fixed through the cooperation of buckle and fixture block, restricted the rotation of flank, improved the stability of unmanned aerial vehicle fin.

Optionally, an inclined surface for guiding the buckle to be buckled on the clamping block is arranged on the clamping block.

Through adopting above-mentioned technical scheme, when the staff rotated the flank, made the buckle to the direction that is close to the fixture block when removing, through the guide on inclined plane, the buckle is automatic to be detained and is established on the fixture block, convenient and fast.

Optionally, one side of the horizontal tail wing, which is far away from the mounting rod, is provided with an elevator.

Through adopting above-mentioned technical scheme, realize through the elevator on the horizontal fin, the staff of being convenient for controls unmanned aerial vehicle's lift, has improved the stability of unmanned aerial vehicle flight.

Optionally, the number of the elevators is two, and the two elevators are arranged along the length direction of the horizontal tail wing.

Through adopting above-mentioned technical scheme, through the setting that uses two elevators, the staff of being convenient for controls unmanned aerial vehicle's direction of flight, has improved the stability of unmanned aerial vehicle flight.

Optionally, the lateral wing is hinged to the horizontal tail wing through a rotating shaft, and a driving piece for driving the rotating shaft to rotate is mounted on the horizontal tail wing.

Through adopting above-mentioned technical scheme, use the driving piece to realize flank pivoted automated control, need not staff's manual rotation flank, convenient and fast.

In summary, the present application includes at least one of the following beneficial technical effects:

1. when workers need to transport or store the unmanned aerial vehicle, the unmanned aerial vehicle empennage is firstly detached from the tail of the unmanned aerial vehicle, and then the side wings are rotated, so that the space occupied by the unmanned aerial vehicle empennage is reduced, the storage of the unmanned aerial vehicle empennage is facilitated, the possibility of damage of the unmanned aerial vehicle empennage due to collision is reduced, and the transportation of the unmanned aerial vehicle is facilitated;

2. the positioning of the unmanned aerial vehicle empennage and the unmanned aerial vehicle empennage is realized through the matching of the jacks and the inserted rods, and then the fixation of the unmanned aerial vehicle empennage is realized through the locking pieces, so that the unmanned aerial vehicle empennage is installed at the tail end of the unmanned aerial vehicle, the installation steps are simple, the installation operation of workers is convenient and rapid;

3. when unmanned aerial vehicle fin ann reprints unmanned aerial vehicle afterbody, realize flank and tailplane's relatively fixed through the cooperation of buckle and fixture block, restricted the rotation of flank, improved the stability of unmanned aerial vehicle fin.

Drawings

Fig. 1 is a schematic structural diagram of a rotatable multifunctional unmanned aerial vehicle empennage provided in embodiment 1 of the present application.

Fig. 2 is an exploded view of the connection between the tail wing and the mounting rod of the unmanned aerial vehicle in embodiment 1 of the present application.

Fig. 3 is an enlarged schematic view of a portion a in fig. 2.

Fig. 4 is a schematic view showing the bottom structure of the tail wing of the unmanned aerial vehicle according to embodiment 1.

Fig. 5 is an enlarged schematic view of a portion B in fig. 4.

Fig. 6 is an enlarged schematic view of a portion C in fig. 1.

Fig. 7 is a schematic view showing the bottom structure of the tail wing of the unmanned aerial vehicle according to embodiment 2.

Fig. 8 is an enlarged schematic view of a portion D in fig. 7.

Fig. 9 is a schematic structural view of the unmanned aerial vehicle according to embodiment 2, after the horizontal stabilizer outer shell is removed from the empennage.

Fig. 10 is an enlarged schematic view of portion E of fig. 9.

Description of reference numerals: 1. a horizontal rear wing; 10. horizontally stabilizing the flour; 100. a first mounting table; 1000. a support block; 101. a first mounting groove; 102. digging grooves; 11. an elevator; 2. a side wing; 20. a connecting portion; 200. a first end corner; 201. a second end corner; 202. a third end corner; 2020. a second mounting groove; 203. a second mounting table; 204. a hinge; 205. a rotating shaft; 206. a first gear; 21. an installation part; 210. inserting a rod; 211. a first connecting member; 22. a vertical tail; 23. supporting the tail wing; 3. a fixing member; 30. a clamping block; 300. a bevel; 31. buckling; 310. a clamping hole; 4. mounting a rod; 40. a second connecting member; 41. a locking member; 42. a clamping piece; 5. a drive member; 50. a second gear.

Detailed Description

The present application is described in further detail below with reference to figures 1-10.

The embodiment of the application discloses rotatable multi-functional unmanned aerial vehicle fin.

Example 1:

referring to fig. 1 and 2, a rotatable formula multi-functional unmanned aerial vehicle fin can dismantle the afterbody that sets up in unmanned aerial vehicle. The utility model provides a rotatable formula multi-functional unmanned aerial vehicle fin, includes horizontal tail 1, has a flank 2 at horizontal tail 1's both ends articulated respectively, still is provided with respectively at horizontal tail 1's both ends and is used for restricting 2 pivoted mountings 3 of flank.

Referring to fig. 2 and 3, unmanned aerial vehicle includes the fuselage and is fixed in two installation poles 4 of fuselage both sides, two installation poles 4 parallel arrangement, and the length direction of installation pole 4 is on a parallel with the length direction of fuselage. The side wing 2 comprises a connecting portion 20, an installation portion 21 is arranged at one end, close to the installation rod 4, of the connecting portion 20, an insertion rod 210 is fixedly connected to the installation portion 21, the length direction of the insertion rod 210 is parallel to the length direction of the installation rod 4, an insertion hole for the insertion rod 210 to be inserted is formed in one end, close to the installation portion 21, of the installation rod 4, and the insertion rod 210 can be detachably inserted into the insertion hole. Through inserting two inserted bars 210 with horizontal fin 1 both ends and locating in two jacks, realize the location of unmanned aerial vehicle fin and installation pole 4, the staff of being convenient for follow-up fixed of carrying out the unmanned aerial vehicle fin.

Referring to fig. 2 and 3, a first connecting member 211 is fixedly sleeved on one end of the mounting portion 21 close to the mounting rod 4, and an external thread is provided on an outer wall of the first connecting member 211. A second connecting member 40 is fixedly connected to one end of the mounting rod 4 close to the mounting portion 21 in a sleeved mode, a locking member 41 is slidably sleeved on the second connecting member 40, an internal thread is arranged on the inner wall of the locking member 41, and the locking member 41 can be detachably connected to the first connecting member 211 in a threaded mode. A blocking member 42 for preventing the locking member 41 from separating from the mounting rod 4 is fixedly sleeved on the second connecting member 40, and the blocking member 42 is positioned at one end of the second connecting member 40 close to the mounting portion 21. The inner diameter of the opening of the locking member 41 at the end close to the mounting portion 21 is larger than the outer diameter of the locking member 42, and the inner diameter of the opening of the locking member 41 at the end away from the mounting portion 21 is smaller than the outer diameter of the locking member 42. When retaining member 41 threaded connection is on first connecting piece 211, screens 42 and retaining member 41 joint to fix installation department 21 at the tail end of installation pole 4, thereby install the tail end at unmanned aerial vehicle with the unmanned aerial vehicle fin.

Referring to fig. 2 and 4, the horizontal rear wing 1 has a long plate shape as a whole, and the length direction of the horizontal rear wing 1 is parallel to the arrangement direction of the two mounting bars 4. Horizontal tail 1 includes horizontal stabilizer 10 and sets up two elevators 11 that deviate from unmanned aerial vehicle fuselage one side at horizontal tail 1, and two elevators 11 arrange along horizontal tail 1's length direction. Through mutually supporting of two elevators 11, stability when having improved unmanned aerial vehicle flight.

Referring to fig. 4 and 5, two groups of first installation platforms 100 are fixedly connected to the bottom surface of the horizontal stabilizing surface 10, the two groups of first installation platforms 100 are distributed at two ends of the horizontal stabilizing surface 10, each group of first installation platforms 100 includes two first installation platforms 100, the four first installation platforms 100 are distributed in a rectangular shape, and the bottom surfaces of the four first installation platforms 100 are located in the same plane.

Referring to fig. 4 and 5, three end corners, a first end corner 200, a second end corner 201, and a third end corner 202, are provided on the circumferential wall of the connection part 20. A vertical tail fin 22 is fixedly connected to the first end corner 200, a supporting tail fin 23 is fixedly connected to the second end corner 201, and the third end corner 202 is hinged to the horizontal stabilizer 10. Two second installation platforms 203 are fixedly connected to one side of the third corner 202 close to the first installation platform 100, and each second installation platform 203 corresponds to one first installation platform 100. A hinge 204 is mounted on each pair of the first mounting platform 100 and the second mounting platform 203, and the first mounting platform 100 is hinged to the second mounting platform 203 through the hinge 204, so that the side wing 2 is hinged to the horizontal rear wing 1.

Referring to fig. 1 and 6, a first mounting groove 101 is formed at each of both ends of the top surface of the horizontal stabilizer 10, and a second mounting groove 2020 is formed at the third corner 202 near the first mounting groove 101. When the end surface of the third end corner 202 is fitted to the end surface of the horizontal stabilizer 10, the first mounting groove 101 communicates with the second mounting groove 2020. The fixing member 3 includes a latch 30 and a catch 31, and the latch 30 is fixedly connected to the bottom wall of the first mounting groove 101. The buckle 31 is fixedly connected to the bottom wall of the second mounting groove 2020 through three screws, a clamping hole 310 adapted to the clamping block 30 is formed at one end of the buckle 31 away from the second mounting groove 2020, and an inclined surface 300 for facilitating the buckle 31 to be buckled on the clamping block 30 is arranged on the clamping block 30. When the worker rotates the lateral wing 2 to make the first installation groove 101 and the second installation groove 2020 approach each other, the end of the buckle 31 far away from the second installation groove 2020 enters the first installation groove 101 and then contacts the inclined surface 300 of the latch 30, the lateral wing 2 continues to rotate, and the end of the buckle 31 far away from the second installation groove 2020 continues to move along the inclined surface 300 until the buckle 31 is buckled on the latch 30 through the buckle hole 310, so that the lateral wing 2 and the horizontal rear wing 1 are relatively fixed.

Referring to fig. 1 and 6, be provided with on the diapire of first mounting groove 101 and be convenient for the staff to scratch the groove 102 of scratching of buckle 31, when the staff need rotate flank 2, stretch into scratching the groove 102 with the finger, scratch buckle 31 hard, make buckle 31 break away from fixture block 30 to relieve flank 2 and horizontal tail wing 1's relatively fixed, the staff of being convenient for rotates flank 2.

Referring to fig. 2 and 6, when the catch 31 is caught on the catch block 30, the vertical rear wing 22 is perpendicular to the horizontal rear wing 1, and the support rear wing 23 is inclined in a direction away from the vertical rear wing 22 and the horizontal rear wing 1. The stability of the unmanned aerial vehicle in flight is enhanced by the vertical tail wings 22 at both ends of the horizontal tail wing 1. Keep away from the one end rigid coupling that supports fin 23 at two installation poles 4 and have a bracing piece, the bracing piece sets up towards ground, and two bracing pieces and two support fin 23 form a support frame, have strengthened unmanned aerial vehicle's stability, have reduced impaired possibility when unmanned aerial vehicle descends.

The implementation principle of the embodiment 1 is as follows: when the staff need accomodate or transport unmanned aerial vehicle, through rotating retaining member 41, make retaining member 41 break away from first connecting piece 211, remove the relatively fixed of installation pole 4 and installation department 21. The bayonet 210 is then withdrawn from the socket to remove the drone tail from the mounting bar 4. Then the staff stretches into the finger and digs into groove 102 and moves buckle 31, make buckle 31 break away from fixture block 30, remove flank 2 and horizontal fin 1's relatively fixed, then the staff will support fin 23 and rotate to the position that is close to horizontal fin 1 through rotating flank 2, reduce the whole space that occupies of unmanned aerial vehicle fin, the staff of being convenient for accomodates the unmanned aerial vehicle fin alone, the risk that the unmanned aerial vehicle fin was collided with has been reduced, thereby the impaired possibility of unmanned aerial vehicle fin has been reduced.

Example 2:

referring to fig. 7 and 8, the present embodiment is different from embodiment 1 in that a hinge 204 and a fixing member 3 are not provided between a horizontal tail wing 1 and a side wing 2 in the present embodiment. A rotation shaft 205 is fixed to the two second mounting platforms 203 of the connecting portion 20, and a longitudinal direction of the rotation shaft 205 is parallel to a longitudinal direction of the insertion rod 210. A supporting block 1000 is fixedly connected to the first mounting platform 100, the rotating shaft 205 is rotatably inserted into the supporting block 1000, and the lateral wing 2 is hinged to the horizontal tail wing 1 through the rotating shaft 205. A first gear 206 is fixedly sleeved on the rotating shaft 205.

Referring to fig. 9 and 10, a driving member 5 for driving the rotation shaft 205 to rotate is installed at each of two ends of the horizontal stabilizer 10, the driving member 5 is a servo motor, an output shaft of the servo motor is parallel to the rotation shaft 205, a second gear 50 is fixedly sleeved on the output shaft of the servo motor, and the first gear 206 and the second gear 50 are engaged with each other. The servo motor provides a driving force to drive the second gear 50 to rotate, the second gear 50 drives the first gear 206 to rotate, and the first gear 206 drives the rotating shaft 205 to rotate, so that the side wing 2 and the horizontal tail wing 1 are driven to rotate relatively.

The implementation principle of the embodiment 2 is as follows: when the staff need accomodate or transport unmanned aerial vehicle, dismantle the back with the unmanned aerial vehicle fin from installation pole 4, rotate through servo motor drive flank 2, realize 2 pivoted electric control of flank, need not staff's manual rotation flank 2, convenient and fast.

The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.