CN211943717U - Damping device for four-rotor aircraft - Google Patents

Abstract

The utility model discloses a damping device for a four-rotor aircraft, which comprises a bracket and an underframe; the utility model drives the tray to rotate directionally on the bracket through the motor, thereby the rotary vane can effectively achieve the effect of effective damping protection when the rotary vane is driven to rotate by the motor through the connecting action of the ejector rod and the fixed plate and the damping protection action of the four positioning springs and the four positioning rods arranged between the fixed plate and the tray, thereby further realizing the shock absorption and protection function of the rotary vane in the rotating state when the aircraft falls to the ground, meanwhile, the bottom plate is arranged below the underframe through the limiting spring, and the limiting spring is positioned through the limiting rod and the limiting block, so that the effective damping protection effect is realized when the bottom plate and the underframe are displaced relatively, thereby effectively protecting the rotary vane to avoid the damage caused by the falling overlarge impact and reducing the service life of the rotary vane.

Description

Damping device for four-rotor aircraft

Technical Field

The utility model relates to a damping device technical field specifically is a damping device for four rotor crafts.

Background

The quadcopter is a system with 6 degrees of freedom of movement (translation and rotation along 3 axes respectively) in space, but only 4 degrees of freedom of control (the rotation speed of four motors) and is therefore called an under-actuated system (the complete actuation system is only when the degrees of freedom of control are equal to the degrees of freedom of movement), but for attitude control itself (the rotation along 3 axes respectively), it is really completely actuated, compared with a helicopter, the quadcopter can realize fewer flight attitudes, but basic forward, backward, translation and other states can be realized, but the mechanical structure of the quadcopter is far simpler than that of the helicopter, the maintenance and replacement costs are also very small, which makes the quadcopter have greater application advantages than the helicopter, but the quadcopter in the prior art has certain disadvantages in the actual operation process, for example:

in the prior art, the four-rotor aircraft is easy to damage the four-rotor rotary blades of the aircraft due to large impact force when falling to the ground due to improper operation and control of a user in the actual operation process, so that the requirements of the prior art are met.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a four damping device for rotor craft to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a damping device for four rotor crafts, includes support and chassis, bolt fixedly connected with motor is passed through to the inside one end of support, motor power take off runs through the support and passes through bolt fixedly connected with tray, all weld all around at tray upper surface middle part has positioning spring, four positioning spring top welding has the fixed plate, bolt fixedly connected with ejector pin is passed through at fixed plate upper surface middle part, bolt fixedly connected with spiral leaf is passed through on the ejector pin top, chassis lower surface middle part is close to both ends department and all welds there is spacing spring, two spacing spring bottom welding has the bottom plate.

Preferably, the support is L-shaped, and honeycomb holes are formed in one end of the lower surface of the support and are located on the same plane as the motor.

Preferably, the support still includes supporting mechanism, motor power take off peripheral both sides the support upper surface all is through bolt fixedly connected with supporting mechanism, supporting mechanism upper surface inlays and has the ball, supporting mechanism pass through the ball with tray roll connection.

Preferably, the tray still includes the locating lever, the equal screw thread of tray upper surface middle part four corners department is pegged graft and is had the locating lever, four the locating lever top all runs through the fixed plate, and with fixed plate sliding connection, the locating lever top is through bolt fixedly connected with locating piece, the locating lever with positioning spring pegs graft.

Preferably, the bottom plate still includes the gag lever post, the equal screw thread grafting of bottom plate upper surface middle part near both ends department has the gag lever post, the gag lever post top is run through the chassis and is passed through bolt fixedly connected with stopper, the gag lever post with spacing spring grafting.

Preferably, the rubber pads are adhered to the lower surface of the bottom plate, the number of the supports is four, the four supports are fixedly connected to four peripheral corners of the aircraft through bolts, the number of the bottom frames is two, and the two bottom frames are fixedly connected to two sides of the middle of the lower surface of the aircraft through bolts.

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

the utility model discloses a motor drive tray is directional to rotate on the support, thereby make the rotary vane can effectually pass through ejector pin and fixed plate's connection effect and the shock attenuation guard action through four positioning spring and four locating levers that are equipped with between fixed plate and tray, realize that the rotary vane can acquire effectual shock attenuation guard's effect when implementing the drive rotation through the motor, thereby make the aircraft further realize when falling to subaerial the shock attenuation guard action of rotary vane under being in the rotation state to the rotary vane, thereby realize realizing effectual shock attenuation guard effect with bottom plate and chassis when carrying out relative displacement through the bottom plate that spacing spring was equipped with and through gag lever post and stopper implementation location thereby the realization of spacing spring in the chassis below, thereby make the aircraft realize when falling subaerial shock attenuation guard vane and then effectually play the damage that the protection rotary vane avoids leading to because of the too big impact of whereabouts and reduce the life of rotary vane and then effectually remedy among the prior art Is not sufficient.

Drawings

FIG. 1 is a schematic view of the partial sectional structure of the front view of the present invention;

FIG. 2 is an enlarged schematic view of the structure at A in FIG. 1;

FIG. 3 is an enlarged view of the structure at B in FIG. 1;

fig. 4 is a schematic top view of the present invention;

fig. 5 is a schematic view of the structure of the present invention.

In the figure: 1. a support; 11. a motor; 12. a tray; 13. a support mechanism; 14. a positioning spring; 15. a fixing plate; 16. positioning a rod; 17. positioning blocks; 18. a top rod; 19. rotating leaves; 2. a chassis; 21. a limiting spring; 22. a base plate; 23. a rubber pad; 24. a limiting rod; 25. and a limiting block.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-5, the present invention provides a technical solution: a damping device for a four-rotor aircraft comprises supports 1 and chassis 2, wherein the supports 1 are provided with four supports 1, the four supports 1 are fixedly connected at four peripheral corners of the aircraft through bolts, the chassis 2 are provided with two supports 2, the two chassis 2 are fixedly connected at two sides of the middle part of the lower surface of the aircraft through bolts, one end inside the support 1 is fixedly connected with a motor 11 through bolts, the type of the motor 11 is KR60A or C micro motor, the motor 11 is electrically connected with the aircraft, the support 1 is L-shaped, one end of the lower surface of the support 1 is provided with a honeycomb hole, the honeycomb hole and the motor 11 are positioned on the same plane, the heat dissipation effect on the motor 11 can be effectively realized through the honeycomb hole, the power output end of the motor 11 penetrates through the supports 1 and is fixedly connected with a tray 12 through bolts, and fillets are arranged at four corners of the tray 12, the upper surfaces of the brackets 1 on two sides of the periphery of the power output end of the motor 11 are fixedly connected with supporting mechanisms 13 through bolts, balls are inlaid on the upper surfaces of the supporting mechanisms 13, the supporting mechanisms 13 are in rolling connection with the tray 12 through the balls, so that the tray 12 can effectively realize the effect of stable rotation, positioning springs 14 are welded on the periphery of the middle part of the upper surface of the tray 12, fixing plates 15 are welded at the top ends of the four positioning springs 14, the effective damping effect can be effectively realized between the fixing plates 15 and the tray 12 through the positioning springs 14, positioning rods 16 are inserted into four corners of the middle part of the upper surface of the tray 12 through threads, the top ends of the four positioning rods 16 penetrate through the fixing plates 15 and are in sliding connection with the fixing plates 15, the displacement direction of the fixing plates 15 during movement can be effectively limited through the positioning rods 16, and positioning blocks 17 are fixedly connected with, the displacement position of the fixed plate 15 can be effectively limited through the positioning block 17, the positioning rod 16 is connected with the positioning spring 14 in an inserted manner, the middle part of the upper surface of the fixed plate 15 is fixedly connected with the ejector rod 18 through a bolt, the top end of the ejector rod 18 is fixedly connected with the rotary vane 19 through a bolt, the middle part of the lower surface of the chassis 2 close to two ends is welded with the limiting springs 21, the bottom ends of the two limiting springs 21 are welded with the bottom plate 22, the shock absorption effect on the chassis 2 can be effectively realized through the limiting springs 21 and the bottom plate 22, the rubber pad 23 is adhered to the lower surface of the bottom plate 22, the protection effect on the bottom plate 22 can be effectively realized through the rubber pad 23, the limiting rods 24 are inserted in threads at the middle part of the upper surface of the bottom plate 22 close to two ends, the displacement angle when the bottom plate 22 and the chassis 2, the limiting rod 24 is inserted into the limiting spring 21.

The working principle is as follows: when the shock absorption protective device is used, the tray 12 is driven to rotate on the support 1 in a directional mode through the motor 11, so that the rotary vane 19 can effectively achieve the shock absorption protective effect when the rotary vane 19 is driven to rotate through the motor 11 by means of the connecting effect of the ejector rod 18 and the fixing plate 15 and the shock absorption protective effect of the four positioning springs 14 and the four positioning rods 16 arranged between the fixing plate 15 and the tray 12, the aircraft further achieves the shock absorption protective effect on the rotary vane 19 in a rotating state when falling to the ground, meanwhile, the bottom plate 22 arranged below the bottom frame 2 through the limiting spring 21 and the limiting rod 24 and the limiting block 25 are used for positioning the limiting spring 21, the bottom plate 22 and the bottom frame 2 are used for achieving an effective shock absorption protective effect when the aircraft falls to the ground, and the shock absorption effect is achieved, so that the rotary vane 19 is effectively protected from being damaged due to overlarge impact of falling The service life of the low rotary vane.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims (6)

1. A damping device for a quad-rotor aircraft, comprising:

a support (1);

a chassis (2);

the device comprises a support (1), a motor (11) is fixedly connected to one end of the interior of the support (1) through a bolt, a tray (12) is fixedly connected to the power output end of the motor (11) through the support (1) through a bolt, positioning springs (14) are welded to the periphery of the middle of the upper surface of the tray (12), fixing plates (15) are welded to the top ends of the four positioning springs (14), an ejector rod (18) is fixedly connected to the middle of the upper surface of each fixing plate (15) through a bolt, and a rotary vane (19) is fixedly connected to the top end of each ejector rod (18;

the middle of the lower surface of the bottom frame (2) close to two ends is welded with limiting springs (21), and the bottom ends of the limiting springs (21) are welded with a bottom plate (22).

2. A shock absorbing device for a quad-rotor aircraft according to claim 1, wherein: support (1) is the L type, and support (1) lower surface one end has seted up honeycomb holes, and honeycomb holes with motor (11) are located the coplanar.

3. A shock absorbing device for a quad-rotor aircraft according to claim 2, wherein: the stent (1) further comprises:

a support mechanism (13);

the support is characterized in that the upper surfaces of the supports (1) on the two sides of the periphery of the power output end of the motor (11) are fixedly connected with supporting mechanisms (13) through bolts, balls are inlaid on the upper surfaces of the supporting mechanisms (13), and the supporting mechanisms (13) are connected with the tray (12) in a rolling mode through the balls.

4. A shock absorbing device for a quad-rotor aircraft according to claim 3, wherein: the tray (12) further comprises:

a positioning rod (16);

positioning rods (16) are inserted into four corners of the middle of the upper surface of the tray (12) in a threaded manner, the top ends of the four positioning rods (16) penetrate through the fixing plate (15) and are connected with the fixing plate (15) in a sliding manner, positioning blocks (17) are fixedly connected to the top ends of the positioning rods (16) through bolts, and the positioning rods (16) are inserted into the positioning springs (14).

5. A shock absorbing device for a quad-rotor aircraft according to claim 4, wherein: the base plate (22) further comprises:

a stopper rod (24);

the middle part of the upper surface of the bottom plate (22) is close to two ends and is provided with a limiting rod (24) in a threaded insertion mode, the top end of the limiting rod (24) penetrates through the bottom frame (2) and is fixedly connected with a limiting block (25) through a bolt, and the limiting rod (24) is connected with the limiting spring (21) in an insertion mode.

6. A shock absorbing device for a quad-rotor aircraft according to claim 5, wherein: rubber pad (23) have been pasted to bottom plate (22) lower surface, support (1) are equipped with four altogether, four support (1) are in aircraft peripheral four corners department through bolt fixed connection, chassis (2) are equipped with two altogether, two chassis (2) are in aircraft lower surface middle part both sides department through bolt fixed connection.

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