CN220263105U - Coaxial double-rotor unmanned aerial vehicle rotor wing condition limiting oar presss from both sides mechanism - Google Patents

Abstract

The utility model discloses a coaxial double-rotor unmanned aerial vehicle rotor wing condition limiting oar clamp mechanism, which comprises an unmanned aerial vehicle rotor wing and a condition limiting oar clamp; the conditional spacing oar clip comprises a spacing oar clip main body, a boss, a circular bottom groove, a secondary unfolding limit part and a rotor wing lifting limit part; one side of the limiting oar clamp main body is connected with an unmanned aerial vehicle rotor wing; the middle part of the upper end of the other side of the limiting paddle clamp main body is provided with a connecting through hole with the front end and the rear end communicated; a boss is arranged at the lower end of the other side of the limiting paddle clamp main body; the lower end of the end face of the other side of the limiting oar clamp main body is provided with a secondary unfolding limiting part, the lower end of the end face of the other side of the limiting oar clamp main body, which is positioned at the secondary unfolding limiting part, is provided with a circular bottom groove, and the top end of the end face of the other side of the limiting oar clamp main body is provided with a rotor wing lifting limiting part. The rotor wing condition limiting oar clamping mechanism of the coaxial double-rotor unmanned aerial vehicle provided by the utility model can realize that the lower rotor wing of the unmanned aerial vehicle is unfolded twice, so that the risk of pitching the upper rotor wing and the lower rotor wing of the unmanned aerial vehicle is effectively avoided.

Description

Coaxial double-rotor unmanned aerial vehicle rotor wing condition limiting oar presss from both sides mechanism

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a coaxial double-rotor unmanned aerial vehicle rotor wing condition limiting oar clamping mechanism.

Background

When the coaxial double-rotor unmanned aerial vehicle (hereinafter referred to as unmanned aerial vehicle) takes off by using a foot rest, the upper rotor and the lower rotor can be manually unfolded, and an automatic rotor unfolding mechanism is not required to be specially designed.

Along with unmanned aerial vehicle's continuous development to and various application scenario put forward more adaptability requirements to unmanned aerial vehicle, especially when putting forward to unmanned aerial vehicle and possessing a launch canister transmission function, require unmanned aerial vehicle's rotor to need be in folding state of accomodating before taking off, and unmanned aerial vehicle is launched the back, require the rotor to expand automatically, but this process exists the difficult problem in: the upper rotor wing and the lower rotor wing are designed to be coaxial up and down, and the distance between the upper rotor wing and the lower rotor wing is smaller; the rotor wing of the unmanned aerial vehicle is unfolded at one time from the folding storage state simultaneously or with a time difference. The disadvantage of this approach is that: when the upper rotor wing and the lower rotor wing are simultaneously unfolded once or are sequentially unfolded once respectively by a time difference, when the upper rotor wing and the lower rotor wing rotate in the same direction, the upper rotor wing and the lower rotor wing can be interfered with each other because of the instant waving of the rotor wings and the disturbance of incoming flow, and the upper rotor wing and the lower rotor wing can be influenced in a large unpredictable and uncontrollable way, so that the upper rotor wing and the lower rotor wing still have a large pitching risk. The damaged rotor wing after pitching directly influences the unmanned aerial vehicle flight, and the probability of occurrence of crash is large.

Disclosure of Invention

In view of this, the utility model provides a coaxial double-rotor unmanned aerial vehicle rotor wing condition limiting paddle clamp mechanism.

In order to achieve the above purpose, the present utility model adopts the following technical scheme:

a rotor wing condition limiting paddle clamp mechanism of a coaxial double-rotor unmanned aerial vehicle comprises an unmanned aerial vehicle rotor wing and a condition limiting paddle clamp; the condition limiting paddle clamp comprises a limiting paddle clamp main body, a boss, a circular bottom groove, a secondary unfolding limiting part and a rotor wing lifting limiting part; one side of the limiting oar clamp main body is connected with an unmanned aerial vehicle rotor wing; the middle part of the upper end of the other side of the limiting paddle clamp main body is provided with a connecting through hole with front and rear ends communicated; a boss is arranged at the lower end of the other side of the limiting paddle clamp main body; the rotor wing lifting limiting device is characterized in that a secondary unfolding limiting part is arranged at the lower end of the end face of the other side of the limiting paddle clamp main body, a circular bottom groove is formed in the lower end of the end face of the other side of the limiting paddle clamp main body, which is located at the secondary unfolding limiting part, and a rotor wing lifting limiting part is arranged at the top end of the end face of the other side of the limiting paddle clamp main body.

Preferably, one side of the limiting paddle clamp main body is integrally connected with the unmanned aerial vehicle rotor wing.

Preferably, the tail end of one side of the limiting paddle clamp main body is longitudinally penetrated and provided with a rotor wing mounting groove; the integrated embedding of link of unmanned aerial vehicle rotor is located in the rotor mounting groove.

Preferably, the one side of spacing oar clamp main part is connected with can dismantle between the unmanned aerial vehicle rotor.

Preferably, a rotor wing mounting groove is longitudinally formed in the tail end of one side of the limiting oar clamp main body in a penetrating manner, and a rotor wing mounting through hole with front and rear ends penetrating through is formed in the limiting oar clamp main body at a position corresponding to the rotor wing mounting groove; the connecting end of the unmanned aerial vehicle rotor wing is embedded into the rotor wing mounting groove; the rotor wing mounting hole of the limiting oar clamp main body is communicated with the mounting hole of the rotor wing connecting end of the unmanned aerial vehicle, and the bolts are connected with the inner threads of the mutually communicated mounting holes and are fastened by nuts.

Preferably, the end face of the other side of the limiting paddle clamp main body is an arc-shaped end face.

Preferably, the secondary expansion limiting part is an arc limiting part protruding out of the end face of the other side of the limiting paddle clamp main body.

Preferably, the rotor upward-lifting limiting part is a square upward-lifting limiting part protruding out of the end face of the other side of the limiting paddle clamp main body; the outer end face of the square lifting limiting part is obliquely upwards arranged from the outer side to the inner side.

Preferably, the front end surface of the other side of the limiting paddle clamp main body is provided with a weight reducing groove.

Compared with the prior art, the utility model has the beneficial effects that:

(1) After the unmanned aerial vehicle launches from the section of thick bamboo, after upper rotor and lower rotor accomplish once expansion simultaneously, upper rotor expands to 80, and lower rotor is because of the restriction of secondary expansion limit part, can only expand 45, because of upper and lower rotor has the angle of expansion difference at this moment, so can high-efficient avoiding upper and lower rotor to beat the oar because of the same direction rotation;

(2) When the rotation speed of the upper rotor wing and the lower rotor wing is increased, the upper rotor wing is thrown to a horizontal angle due to centrifugal force, the lower rotor wing is also swung upwards due to centrifugal force, when the upward swinging force of the lower rotor wing reaches a threshold value, the lower rotor wing passes through the secondary unfolding limit part to limit the upper rotor wing and the lower rotor wing to reach a horizontal position, and during the period, the upper rotor wing and the lower rotor wing reach high rotation speed and are thrown to the horizontal state, at the moment, the possibility of pitching does not exist, so that the secondary unfolding mechanism of the lower rotor wing realizes the purpose of not pitching during the period from the moment of launching to the moment of completely unfolding the rotor wings of the unmanned aerial vehicle;

(3) The conditional limiting paddle clamp mechanism has the advantages of smart and simple design, small volume and light weight.

Drawings

FIG. 1 is a schematic view of a three-dimensional structure of a conditional stop paddle clip of the present utility model;

FIG. 2 is a schematic view of a three-dimensional structure of a conditional stop paddle clip of the present utility model;

FIG. 3 is a front view of a conditional stop paddle clip of the present utility model;

FIG. 4 is a top view of a conditional stop paddle clip of the present utility model;

FIG. 5 is a cross-sectional view taken along A-A in FIG. 4;

FIG. 6 is a schematic diagram of the overall structure of the present utility model;

FIG. 7 is a schematic view of the lower rotor housing configuration of the present utility model;

figure 8 is a schematic view of the first deployment completion of the lower rotor of the present utility model;

figure 9 is a schematic view of the lower rotor of the present utility model in a second deployment configuration;

figure 10 is a schematic view of the lower rotor in a second deployment completion status of the present utility model;

fig. 11 is a schematic view of the lower limit state structure of the lower rotor flap angle of the present utility model;

fig. 12 is a schematic view of the structure of the lower rotor flap angle upper limit state of the present utility model.

In the figure: 1. unmanned aerial vehicle rotor; 2. a condition limiting paddle clamp; 21. a limiting paddle clamp body; 201. an arc end surface; 22. a connecting through hole; 23. a boss; 24. a circular bottom groove; 25. a secondary unfolding limit part; 26. a rotor wing lifting limit part; 27. a rotor mounting slot; 28. a rotor mounting through hole; 29. a weight reduction groove; 3. a bolt; 4. and (3) a nut.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments.

In the description of the present utility model, unless otherwise indicated, the meaning of "a plurality" is two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front," "rear," "head," "tail," and the like are used as an orientation or positional relationship based on that shown in the drawings, merely to facilitate description of the utility model and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the utility model. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present utility model, it should be noted that, unless explicitly specified and limited otherwise, the terms "connected," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.

Examples:

as shown in fig. 1-12, a coaxial dual rotor unmanned aerial vehicle rotor condition limiting paddle clamp mechanism comprises an unmanned aerial vehicle rotor 1 and a condition limiting paddle clamp 2.

The conditional limiting paddle clamp 2 comprises a limiting paddle clamp main body 21, a rotor mounting groove 27, a rotor mounting hole, a boss 23, a round bottom groove 24, a secondary unfolding limiting part 25 and a rotor lifting limiting part 26.

A rotor wing mounting groove 27 is longitudinally formed in the tail end of one side of the limiting oar clamp main body 21 in a penetrating manner, and a rotor wing mounting through hole 28 with front and rear ends penetrating through is formed in the limiting oar clamp main body 21 at a position corresponding to the rotor wing mounting groove 27; the connecting end of the unmanned aerial vehicle rotor wing 1 is embedded in the rotor wing mounting groove 27; the rotor mounting hole of spacing oar clamp main part 21 link up each other with the mounting hole of unmanned aerial vehicle rotor 1 link end, and link up mounting hole internal thread connection each other has bolt 3, and bolt 3 is with nut 4 fastening.

The middle part of the upper end of the other side of the limiting paddle clamp main body 21 is provided with a connecting through hole 22 with front and rear ends communicated. The lower end of the other side of the limiting paddle clamp main body 21 is provided with a boss 23.

The other side end face of the limiting paddle clamp main body 21 is an arc-shaped end face 201; the lower end of the end face of the other side of the limiting paddle clamp main body 21 is provided with a secondary unfolding limiting part 25, and the secondary unfolding limiting part 25 is an arc limiting part. The lower end of the other side end face of the limiting paddle clamp main body 21, which is positioned at the secondary unfolding limiting part 25, is provided with a circular bottom groove 24. A rotor wing lifting limiting part 26 is arranged at the top end of the other side end surface of the limiting oar clamp main body 21; the rotor upward-lifting limiting part 26 is a square upward-lifting limiting part, and the outer end surface of the square upward-lifting limiting part is obliquely upwards arranged from the outer side to the inner side.

The weight-reducing groove 29 is formed in the front end face of the other side of the limiting paddle clamp main body 21, so that the weight of the whole condition limiting paddle clamp 2 is light.

Because the design of the condition limiting paddle clamp 2 is simple, the processing of the condition limiting paddle clamp 2 is easy to realize, and therefore, the condition limiting paddle clamp 2 with the same specification can realize 100% interchange.

The condition limiting paddle clamp 2 is small in size, light in weight, easy to implement in processing technology and low in production cost.

When assembled: the condition limiting paddle clamps 2 are inserted into the mounting grooves of the unmanned aerial vehicle body, the connecting through holes 22 of the condition limiting paddle clamps 2 are communicated with the mounting through holes in the mounting grooves of the unmanned aerial vehicle body, and rotating shafts are arranged in the mutually communicated connecting through holes 22 and the mounting through holes in a penetrating manner; the rotor mounting groove 27 of the condition limiting paddle clamp 2 is internally threaded with a lower rotor.

When unmanned aerial vehicle is in the transmission section of thick bamboo, its upper and lower rotor all by folding accomodate in the transmission section of thick bamboo, unmanned aerial vehicle's upper rotor compresses its torsional spring (the upper rotor only needs the torsional spring to expand once, this is this scheme of conventional art and does not do not give in detail), but the boss 23 compression unmanned aerial vehicle body position arm of condition spacing oar clamp 2 can elastically stretch out and draw back first subassembly, as shown in figure 7 a department (in figure 7 a department is the position that can elastically stretch out and draw back first subassembly on the unmanned aerial vehicle body position arm), but elastically stretch out and draw back first subassembly is compressed for the first time, makes upper and lower rotor all be in vertical state, accomodates in the transmission section of thick bamboo.

After unmanned aerial vehicle is launched out the section of thick bamboo, because unmanned aerial vehicle breaks away from the section of thick bamboo of launching, the rotor no longer is restrained by the section of thick bamboo inner wall of launching, go up the rotor and be expanded to vertical direction 80 left and right sides position because of torsional spring effect (this is conventional technique this scheme and does not do not give details), but the flexible head subassembly on the unmanned aerial vehicle organism phase arm is released because of elastic potential energy, but flexible head subassembly extension pushes away, but flexible head subassembly pushes the spacing oar clamp 2 of condition and lower rotor upwards wave along the pivot in pushing away the in-process, but flexible head subassembly pushes away to the biggest time, lower rotor first expansion, expansion angle 45, and but the outside end of flexible head subassembly just cooperates with the round bottom groove 24 of condition spacing oar clamp 2 this moment, as shown in the department in fig. 8 b (but this is the flexible head subassembly position on the unmanned aerial vehicle organism position arm in fig. 8), but the secondary expansion spacing portion 25 restriction of condition spacing oar clamp 2 and the continuation of avoiding lower rotor are opened to bigger angle for lower rotor keeps in first expansion angle 45, can realize the secondary spacing to waving down.

After the unmanned aerial vehicle starts the motor, the upper rotor wing and the lower rotor wing start to rotate; the rotation of rotor down makes the spacing oar of condition press from both sides 2 and rotor down produce great centrifugal force, and centrifugal force makes the spacing oar of condition press from both sides 2 and rotor down produce anticlockwise moment, and under the effect of moment, the spacing oar of condition press from both sides 2 and rotor down revolute the rotation axis, but promote and compress unmanned aerial vehicle organism phase position arm on flexible head subassembly. As the centrifugal force increases, the generated torque also increases, and the secondary expansion limiting part 25 of the condition limiting paddle clip 2 pushes the elastically telescopic head assembly on the phase arm of the unmanned aerial vehicle body to compress the elastically telescopic head assembly on the phase arm of the unmanned aerial vehicle body for the second time, as shown in fig. 9 c (the position shown by the elastically telescopic head assembly on the phase arm of the unmanned aerial vehicle body in fig. 9 c); when the torque reaches the threshold value, the secondary expansion limiting part 25 of the condition limiting paddle clamp 2 pushes away the elastically telescopic head assembly completely, the elastically telescopic head assembly is compressed to the low position again, the secondary expansion limiting part 25 of the condition limiting paddle clamp 2 completely passes over the elastically telescopic head assembly, at this time, the elastic potential energy of the elastically telescopic head assembly is released, the elastically telescopic head assembly is sprung open for the second time, the lower rotor wing swings upwards to realize the second expansion of the lower rotor wing, and the lower rotor wing expands to about 90 degrees due to the centrifugal force effect, as shown in d in fig. 10 (d is the position shown by the elastically telescopic head assembly on the body arm of the unmanned aerial vehicle).

After the lower rotor wing is unfolded for the second time, the upper surface of the secondary unfolding limit part 25 of the condition limiting paddle clamp 2 cannot reversely cross the elastic telescopic head assembly, so that the large-angle reverse clockwise waving of the lower rotor wing is prevented, the secondary unfolding limit part 25 of the condition limiting paddle clamp 2 becomes the lower limit of the waving angle of the rotor wing, as shown in fig. 11 (the position e of fig. 11 is the position of the elastic telescopic head assembly on the arm of the unmanned aerial vehicle body); the elastically telescopic head assembly also realizes a three-time limiting function.

After the lower rotor wing is unfolded for the second time, the outer side surface of the rotor wing lifting limit part 26 of the condition limiting paddle clamp 2 cannot pass over the outer side wall of the unmanned aerial vehicle body, so that the lower rotor wing is prevented from continuously swinging anticlockwise at a large angle, the rotor wing lifting limit of the condition limiting paddle clamp 2 is used for limiting the upper limit of the swing angle of the rotor wing, as shown in fig. 12 (the position f in fig. 12 is the position shown by the outer side wall on the arm of the unmanned aerial vehicle body);

from this, but flexible first subassembly on unmanned aerial vehicle organism phase place arm realizes twice elastic potential energy release, but flexible first subassembly is twice compressed, twice is opened by the bullet, and rotor twice is spacing by flexible first subassembly down, realizes rotor once, the segmentation of secondary is expanded down, consequently increases the angle difference after rotor expansion down on the unmanned aerial vehicle, reduces the air current after the unmanned aerial vehicle launches and beats the oar when the rotor is rotated down to the upper and lower rotor that the disturbance of contra-rotating wing brought risk.

The present utility model is not limited to the above-mentioned embodiments, and any person skilled in the art, based on the technical solution of the present utility model and the inventive concept thereof, can be replaced or changed within the scope of the present utility model.

Claims (9)

1. The rotor wing condition limiting paddle clamp mechanism of the coaxial double-rotor unmanned aerial vehicle is characterized by comprising an unmanned aerial vehicle rotor wing (1) and a condition limiting paddle clamp (2); the condition limiting paddle clamp (2) comprises a limiting paddle clamp main body (21), a boss (23), a round bottom groove (24), a secondary unfolding limiting part (25) and a rotor wing lifting limiting part (26); one side of the limiting paddle clamp main body (21) is connected with an unmanned aerial vehicle rotor wing (1); the middle part of the upper end of the other side of the limiting paddle clamp main body (21) is provided with a connecting through hole (22) with front and rear ends communicated; a boss (23) is arranged at the lower end of the other side of the limiting paddle clamp main body (21); the rotor wing lifting limiting device is characterized in that a secondary unfolding limiting part (25) is arranged at the lower end of the end face of the other side of the limiting paddle clamp main body (21), a circular bottom groove (24) is formed in the lower end of the end face of the other side of the limiting paddle clamp main body (21) located at the secondary unfolding limiting part (25), and a rotor wing lifting limiting part (26) is arranged at the top end of the end face of the other side of the limiting paddle clamp main body (21).

2. The coaxial dual rotor unmanned aerial vehicle rotor condition limiting paddle clamp mechanism of claim 1, wherein one side of the limiting paddle clamp body (21) is integrally connected with the unmanned aerial vehicle rotor (1).

3. The coaxial double-rotor unmanned aerial vehicle rotor wing condition limiting paddle clamp mechanism according to claim 2, wherein a rotor wing mounting groove (27) is longitudinally formed at one side tail end of the limiting paddle clamp main body (21); the connecting end of the unmanned aerial vehicle rotor wing (1) is integrally embedded into the rotor wing mounting groove (27).

4. The coaxial dual rotor unmanned aerial vehicle rotor condition limiting paddle clamp mechanism of claim 1, wherein one side of the limiting paddle clamp body (21) is detachably connected with the unmanned aerial vehicle rotor (1).

5. The coaxial double-rotor unmanned aerial vehicle rotor wing condition limiting paddle clamp mechanism according to claim 4, wherein a rotor wing mounting groove (27) is longitudinally formed in a penetrating manner at one side tail end of the limiting paddle clamp main body (21), and rotor wing mounting through holes (28) with penetrating front and rear ends are formed in the limiting paddle clamp main body (21) at positions corresponding to the rotor wing mounting groove (27); the connecting end of the unmanned aerial vehicle rotor wing (1) is embedded into a rotor wing mounting groove (27); the rotor wing mounting hole of the limiting oar clamp main body (21) is communicated with the mounting hole of the connecting end of the unmanned aerial vehicle rotor wing (1), the bolts (3) are connected with the inner threads of the mutually communicated mounting holes, and the bolts (3) are fastened through nuts (4).

6. The coaxial dual rotor unmanned aerial vehicle rotor condition limiting paddle clamp mechanism of claim 1, wherein the other side end surface of the limiting paddle clamp body (21) is an arc-shaped end surface (201).

7. The coaxial double-rotor unmanned aerial vehicle rotor condition limiting paddle clamp mechanism according to claim 6, wherein the secondary unfolding limiting portion (25) is an arc limiting portion protruding out of the end face of the other side of the limiting paddle clamp main body (21).

8. The coaxial double-rotor unmanned aerial vehicle rotor condition limiting paddle clamp mechanism according to claim 1 or 7, wherein the rotor upward-lifting limiting part (26) is a square upward-lifting limiting part protruding out of the end face of the other side of the limiting paddle clamp main body (21); the outer end face of the square lifting limiting part is obliquely upwards arranged from the outer side to the inner side.

9. The coaxial double-rotor unmanned aerial vehicle rotor wing condition limiting paddle clamp mechanism according to claim 1, wherein a weight reducing groove (29) is formed in the front end face of the other side of the limiting paddle clamp main body (21).