阅读说明：本技术 一种便于安装固定减速效果好的无人机着陆减速阻尼装置 (Unmanned aerial vehicle landing deceleration damping device convenient to install, fix and have good deceleration effect ) 是由 吴宗霞 于 2020-07-14 设计创作，主要内容包括：本发明公开了一种便于安装固定减速效果好的无人机着陆减速阻尼装置,包括安装架、主架构组件、防沉组件和缓冲组件,所述主架构组件的上方设置有动力舱,且主架构组件位于安装架的外侧,所述防沉组件的上方设置有气体发生器,且防沉组件位于安装架的两侧,所述缓冲组件包括固定杆、安装块、螺纹孔、上轴柱、固定卡口、脚架、轴块、摆动孔、下轴柱、泡沫球、阻尼器、减震弹簧、挡板和轴套,所述固定杆的顶端设置有安装块,且安装块的中部横向贯穿设置有螺纹孔,所述固定杆的右上方设置有上轴柱,且固定杆的左下方贯穿设置有固定卡口,使用者可以通过缓冲组件以及防沉组件,是无人机的降落更加的安全与稳定。(The invention discloses an unmanned aerial vehicle landing deceleration damping device convenient to install, fix and good in deceleration effect, which comprises an installation frame, a main framework assembly, an anti-sinking assembly and a buffer assembly, wherein a power cabin is arranged above the main framework assembly, the main framework assembly is positioned on the outer side of the installation frame, a gas generator is arranged above the anti-sinking assembly, the anti-sinking assembly is positioned on two sides of the installation frame, the buffer assembly comprises a fixed rod, an installation block, a threaded hole, an upper shaft column, a fixed bayonet, a foot rest, a shaft block, a swinging hole, a lower shaft column, a foam ball, a damper, a damping spring, a baffle plate and a shaft sleeve, the top end of the fixed rod is provided with the installation block, the middle part of the installation block is transversely provided with the threaded hole in a penetrating manner, the upper shaft column is arranged on the right upper part of the fixed rod, the fixed bayonet is arranged on the left lower, the landing of the unmanned aerial vehicle is safer and more stable.)

1. The utility model provides an unmanned aerial vehicle landing deceleration damping device convenient to installation is fixed slow down effectually, includes mounting bracket (1), body frame component (2), prevents sinking subassembly (3) and buffer assembly (4), its characterized in that: the power cabin (201) is arranged above the main framework component (2), the main framework component (2) is located on the outer side of the mounting frame (1), the gas generator (302) is arranged above the anti-sinking component (3), the anti-sinking component (3) is located on two sides of the mounting frame (1), the fixing rod (401) is arranged above the buffering component (4), the buffering component (4) is located on two sides of the bottom of the mounting frame (1), the buffering component (4) comprises the fixing rod (401), an installation block (402), a threaded hole (403), an upper shaft column (404), a fixing bayonet (405), a foot stool (406), a shaft block (407), a swing hole (408), a lower shaft column (409), a foam ball (410), a damper (411), a damping spring (412), a baffle (413) and a shaft sleeve (414), the installation block (402) is arranged at the top end of the fixing rod (401), and the middle part of the mounting block (402) transversely penetrates through and is provided with a threaded hole (403), the upper right side of the fixing rod (401) is provided with an upper shaft column (404), and the lower left side of the fixing rod (401) penetrates through and is provided with a fixing bayonet (405).

2. The landing deceleration damping device of the unmanned aerial vehicle, which is convenient to install and fix and has good deceleration effect, according to claim 1, is characterized in that: the fixing rod is characterized in that a foot rest (406) is arranged below the fixing rod (401), shaft blocks (407) are arranged on the front side and the rear side of the top end of the foot rest (406), the shaft blocks (407) are embedded in fixing bayonets (405) on the fixing rod (401), a swing hole (408) is formed in the middle of the foot rest (406), a lower shaft column (409) is arranged in the middle of the swing hole (408), and a foam ball (410) is arranged at the bottom of the foot rest (406).

3. The landing deceleration damping device of the unmanned aerial vehicle, which is convenient to install and fix and has good deceleration effect, according to claim 1, is characterized in that: be provided with attenuator (411) between dead lever (401) and foot rest (406), and damping spring (412) have been cup jointed to the outside of attenuator (411), damping spring (412)'s both ends all are connected with baffle (413), and the outside of baffle (413) is installed axle sleeve (414), axle sleeve (414) on damping spring (412) top cup joint in last jack-post (404) outside, and axle sleeve (414) the bottom of damping spring (412) cup joint in the jack-post (409) outside down.

4. The landing deceleration damping device of the unmanned aerial vehicle, which is convenient to install and fix and has good deceleration effect, according to claim 1, is characterized in that: install between piece (402) and mounting bracket (1) through bolted connection, constitute detachable construction, install piece (402) and screw hole (403), dead lever (401), upper shaft post (404) and fixed bayonet (405) between be the integral type structure, foot rest (406) are inside through axle piece (407) gomphosis in fixed bayonet (405), constitute rotatable structure, be the integral type structure between foot rest (406) and axle piece (407), swing hole (408) and lower shaft post (409), be bolted connection between attenuator (411) and baffle (413), be the welding between baffle (413) and axle sleeve (414), axle sleeve (414) and last shaft post (404) and lower shaft post (409) between be cup jointed, constitute rotatable structure.

5. The landing deceleration damping device of the unmanned aerial vehicle, which is convenient to install and fix and has good deceleration effect, according to claim 1, is characterized in that: the main framework component (2) comprises a power cabin (201), a navigator (202), a signal patch (203), a rotor rod (204), a motor (205), a propeller (206), a shaft cap (207), a control box (208), a connecting rod (209), a holder (210) and a holder protective cover (211), wherein the power cabin (201) is installed at the top of the installation rack (1), the navigator (202) is arranged at the top of the power cabin (201), the signal patch (203) is arranged on the front side of the middle part above the installation rack (1), the rotor rods (204) are arranged on two sides of the installation rack (1), the end part of the rotor rod (204) is connected with the motor (205), the output end of the motor (205) is connected with the propeller (206), the shaft cap (207) is arranged above the propeller (206), the control box (208) is installed at the bottom of the installation rack (1), and the below of control box (208) is provided with connecting rod (209), the bottom of connecting rod (209) is connected with cloud platform (210), and the outside of cloud platform (210) is provided with cloud platform protection casing (211).

6. The landing deceleration damping device of the unmanned aerial vehicle convenient to install and fix and having good deceleration effect according to claim 5, is characterized in that: all through bolted connection between power compartment (201) and mounting bracket (1) and navigator (202), constitute detachable construction, formula structure as an organic whole between rotor pole (204) and mounting bracket (1), be bolted connection between control box (208) and connecting rod (209) and cloud platform (210), be bonding between cloud platform protection casing (211) and control box (208).

7. The landing deceleration damping device of the unmanned aerial vehicle, convenient to install and fix, and good in deceleration effect according to claim 1, is characterized in that: prevent heavy subassembly (3) including gasbag box (301), gas generator (302), irritate gas mouth (303), play export (304) and gasbag (305), the both sides of mounting bracket (1) all are provided with gasbag box (301), and the top of gasbag box (301) is connected with gas generator (302), the upper surface of gasbag box (301) runs through and is provided with irritates gas mouth (303), and the bottom of irritate gas mouth (303) is connected with gasbag (305), the outside of gasbag box (301) is provided with and plays export (304).

8. The landing deceleration damping device of the unmanned aerial vehicle, which is convenient to install and fix and has good deceleration effect, according to claim 7, is characterized in that: be bolted connection between gasbag box (301) and mounting bracket (1), constitute detachable construction, be bolted connection between gasbag box (301) and gas generator (302), gasbag box (301) with irritate gas mouth (303) and play export (304) formula structure as an organic whole.

9. The landing deceleration damping device of the unmanned aerial vehicle, which is convenient to install and fix and has good deceleration effect, according to claim 1, is characterized in that: the rotor rod (204), the air bag box (301) and the fixing rod (401) are symmetrically arranged and are symmetrical about a vertical central line of the mounting frame (1).

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle landing deceleration damping device convenient to install and good in deceleration effect.

Background

Unmanned aerial vehicle is called unmanned aerial vehicle for short, and is abbreviated as UAV in English, and is an unmanned aerial vehicle operated by utilizing a radio remote control device and a self-contained program control device, or is operated by an onboard computer completely or intermittently and autonomously, most of the existing unmanned aerial vehicle devices are provided with fixed rigid undercarriage, but the speed is not easy to be accurately controlled when the unmanned aerial vehicle lands, the landing impact force of the unmanned aerial vehicle is large, certain influence and damage are caused to the internal precise structure of the unmanned aerial vehicle, and therefore the unmanned aerial vehicle landing deceleration damping device convenient to install and fix and good in deceleration effect is required to be designed.

Disclosure of Invention

The invention aims to provide an unmanned aerial vehicle landing deceleration damping device convenient to mount and good in fixed deceleration effect, and aims to solve the problems that most of unmanned aerial vehicle devices provided in the background technology are only provided with fixed rigid undercarriages, but the speed of the unmanned aerial vehicle during landing is not easy to accurately control, the unmanned aerial vehicle is easy to have large landing impact force, and certain influence and damage are caused on the internal precise structure of the unmanned aerial vehicle.

In order to achieve the purpose, the invention provides the following technical scheme: an unmanned aerial vehicle landing deceleration damping device convenient to mount, fix and good in deceleration effect comprises a mounting frame, a main framework component, an anti-sinking component and a buffer component, wherein a power cabin is arranged above the main framework component, the main frame component is positioned at the outer side of the mounting frame, a gas generator is arranged above the anti-sinking component, the anti-sinking components are positioned at the two sides of the mounting rack, the fixing rods are arranged above the buffer components, the buffer components are positioned at the two sides of the bottom of the mounting rack, the buffer component comprises a fixed rod, a mounting block, a threaded hole, an upper shaft column, a fixed bayonet, a foot rest, a shaft block, a swinging hole, a lower shaft column, a foam ball, a damper, a damping spring, a baffle plate and a shaft sleeve, the mounting block is arranged at the top end of the fixed rod, and the middle part of the mounting block transversely penetrates through and is provided with a threaded hole, the upper right side of the fixing rod is provided with an upper shaft column, and the lower left side of the fixing rod penetrates through and is provided with a fixing bayonet.

Preferably, a foot rest is arranged below the fixed rod, shaft blocks are arranged on the front side and the rear side of the top end of the foot rest, the shaft blocks are embedded in the fixed bayonet on the fixed rod, a swing hole is formed in the middle of the foot rest, a lower shaft column is arranged in the middle of the swing hole, and a foam ball is arranged at the bottom of the foot rest.

Preferably, a damper is arranged between the fixed rod and the foot rest, a damping spring is sleeved outside the damper, two ends of the damping spring are connected with baffle plates, a shaft sleeve is installed on the outer side of each baffle plate, the shaft sleeve on the top end of the damping spring is sleeved on the outer side of the upper shaft column, and the shaft sleeve on the bottom end of the damping spring is sleeved on the outer side of the lower shaft column.

Preferably, through bolted connection between installation piece and the mounting bracket, constitute detachable construction, be the integral type structure between installation piece and screw hole, dead lever, last jack-post and the fixed bayonet socket, the foot rest passes through the jack-post gomphosis inside fixed bayonet socket, constitutes rotatable structure, be the integral type structure between foot rest and jack-post, swing hole and the jack-post down, be bolted connection between attenuator and the baffle, be the welding between baffle and the axle sleeve, the axle sleeve is cup jointed with last jack-post and down between the jack-post, constitutes rotatable structure.

Preferably, the body frame component includes piggyback pod, navigator, signal paster, rotor pole, motor, screw, axle cap, control box, connecting rod, cloud platform and cloud platform protection casing, the piggyback pod is installed at the top of mounting bracket, and the top of piggyback pod is provided with the navigator, the top middle part front side of mounting bracket is provided with the signal paster, and the both sides of visiting of going up of mounting bracket all are provided with the rotor pole, the end connection of rotor pole has the motor, and the output of motor is connected with the screw, the top of screw is provided with the axle cap, the control box is installed to the bottom of mounting bracket, and the below of control box is provided with the connecting rod, the bottom of connecting rod is connected with the cloud platform, and the outside of cloud platform is provided with the cloud platform protection casing.

Preferably, all pass through bolted connection between nacelle and mounting bracket and the navigator, constitute detachable construction, formula structure as an organic whole between rotor pole and the mounting bracket, be bolted connection between control box and connecting rod and the cloud platform, be bonding between cloud platform protection casing and the control box.

Preferably, prevent sinking the subassembly and include gasbag box, gas generator, gas filling port, bullet export and gasbag, the both sides of mounting bracket all are provided with the gasbag box, and the top of gasbag box is connected with gas generator, the upper surface of gasbag box runs through and is provided with the gas filling port, and the bottom of gas filling port is connected with the gasbag, the outside of gasbag box is provided with the bullet export.

Preferably, be bolted connection between gasbag box and the mounting bracket, constitute detachable construction, be bolted connection between gasbag box and the gas generator, gasbag box and gas filling opening and bullet export formula structure as an organic whole.

Preferably, the rotor rod, the airbag box and the fixing rod are symmetrically arranged and are symmetrical about a vertical center line of the mounting frame.

Compared with the prior art, the invention has the following beneficial effects:

1. according to the main frame component, the signal receiving part is the signal patch, so that the equipment can be greatly lightened, and meanwhile, the signal patch is arranged on the outer side of the mounting frame, so that the signal receiving rate of the equipment in the flight process can be effectively improved.

2. The main framework component is provided with the holder protective cover outside the holder, and the holder protective cover is made of transparent plastic, so that multiple protection effects such as water resistance, dust prevention, scratch prevention and the like can be provided for the holder under the condition of not influencing the operation of the holder.

3. The anti-sinking assembly is arranged, the gas generator and the air bag are arranged in the anti-sinking assembly, the gas generator can be controlled to rapidly inflate the air bag when the unmanned aerial vehicle meets special conditions, the periphery of the body is wrapped, abnormal landing of the body can be effectively protected, and the air bag in the anti-sinking assembly can provide buoyancy for the body when the body needs to be forced to land on the water surface.

4. The buffer assembly of the invention can weaken the impact force of part of the landing machine body to the tight body by the angle conversion mode through the rotary connection between the fixed rod and the foot rest, and simultaneously, the shock absorption spring and the damper are arranged between the fixed rod and the foot rest, which is beneficial to greatly reducing the impact shock received by the landing machine body.

5. The foam ball is arranged at the bottom of the foot rest in the buffer assembly, so that the vibration of the machine body can be reduced when the equipment lands, and meanwhile, the light foam ball is selected, so that the weight of the equipment can be effectively reduced.

Drawings

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

FIG. 2 is an enlarged structural view of the structure at the position A of the present invention;

FIG. 3 is a schematic structural view of the fixing rod unit of the present invention;

FIG. 4 is a schematic structural view of a foot rest assembly of the present invention;

FIG. 5 is a schematic view of the construction of the damping spring assembly of the present invention;

FIG. 6 is a schematic view of a buffer assembly according to the present invention.

In the figure: 1. a mounting frame; 2. a main architecture component; 201. a power compartment; 202. a navigator; 203. signal paster; 204. a rotor lever; 205. an electric motor; 206. a propeller; 207. a shaft cap; 208. a control box; 209. a connecting rod; 210. a holder; 211. a holder shield; 3. an anti-settling component; 301. an airbag case; 302. a gas generator; 303. an air filling port; 304. a projectile port; 305. an air bag; 4. a buffer assembly; 401. fixing the rod; 402. mounting blocks; 403. a threaded hole; 404. an upper jack post; 405. fixing the bayonet; 406. a foot rest; 407. a shaft block; 408. a swing hole; 409. a lower shaft column; 410. a foam ball; 411. a damper; 412. a damping spring; 413. a baffle plate; 414. and a shaft sleeve.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative efforts based on the embodiments of the present invention belong to the protection scope of the present invention.

Referring to fig. 1-6, the present invention provides the following technical solutions: an unmanned aerial vehicle landing deceleration damping device convenient to install, fix and have good deceleration effect comprises an installation frame 1, a main framework assembly 2, an anti-sinking assembly 3 and a buffer assembly 4, wherein a power cabin 201 is arranged above the main framework assembly 2, the main framework assembly 2 is positioned on the outer side of the installation frame 1, the main framework assembly 2 comprises the power cabin 201, a navigator 202, a signal patch 203, a rotor rod 204, a motor 205, a propeller 206, a shaft cap 207, a control box 208, a connecting rod 209, a holder 210 and a holder protective cover 211, the power cabin 201 is installed at the top of the installation frame 1, the navigator 202 is arranged at the top of the power cabin 201, the signal patch 203 is arranged on the front side of the middle part above the installation frame 1, the rotor rods 204 are arranged on both sides of the installation frame 1, the motor 205 is connected to the end part of the rotor rods 204, the propeller 206 is connected to the output end part of the motor 205, and the shaft cap 207 is arranged above, control box 208 is installed to the bottom of mounting bracket 1, and is provided with connecting rod 209 below control box 208, and the bottom of connecting rod 209 is connected with cloud platform 210, and the outside of cloud platform 210 is provided with cloud platform protection casing 211.

All through bolted connection between nacelle 201 and mounting bracket 1 and navigator 202, constitute detachable construction, formula structure as an organic whole between rotor pole 204 and the mounting bracket 1, be bolted connection between control box 208 and connecting rod 209 and cloud platform 210, be bonding between cloud platform protection casing 211 and the control box 208.

Adopt signal paster 203 with signal reception part in the main framework subassembly 2, light-weighted equipment can be very big, simultaneously, install signal paster 203 in the outside of mounting bracket 1, can effectively improve the signal reception rate of equipment in the flight process.

The main framework component 2 is provided with the holder protective cover 211 outside the holder 210, and the holder protective cover 211 is made of transparent plastic, so that multiple protection effects such as water resistance, dust resistance, scratch resistance and the like can be provided for the holder 210 without affecting the operation of the holder 210.

Prevent that the top of sinking the subassembly 3 is provided with gas generator 302, and prevent sinking the both sides that subassembly 3 is located mounting bracket 1, prevent sinking subassembly 3 includes gasbag box 301, gas generator 302, irritate gas port 303, play export 304 and gasbag 305, the both sides of mounting bracket 1 all are provided with gasbag box 301, and gasbag box 301's top is connected with gas generator 302, gasbag box 301's upper surface runs through and is provided with irritate gas port 303, and irritate the bottom of gas port 303 and be connected with gasbag 305, gasbag box 301's the outside is provided with and plays export 304.

The air bag box 301 is connected with the mounting frame 1 through bolts to form a detachable structure, the air bag box 301 is connected with the gas generator 302 through bolts, and the air bag box 301, the air filling port 303 and the ejection port 304 are of an integrated structure.

Be provided with in the equipment and prevent sinking subassembly 3, and prevent being provided with gas generator 302 and gasbag 305 in the subassembly 3 that sinks, can meet when the special case at unmanned aerial vehicle, control gas generator 302 carries out quick inflation to gasbag 305 to wrap up the fuselage all around, can protect the abnormal descending of fuselage effectively, include when the fuselage needs carry out the surface of water and compel to land, prevent sinking gasbag 305 in the subassembly 3 and can provide buoyancy for the fuselage.

The top of buffer unit 4 is provided with dead lever 401, and buffer unit 4 is located the bottom both sides of mounting bracket 1, buffer unit 4 includes dead lever 401, installation piece 402, screw hole 403, go up axle column 404, fixed bayonet 405, foot rest 406, axle block 407, swing hole 408, lower axle column 409, foam ball 410, attenuator 411, damping spring 412, baffle 413 and axle sleeve 414, the top of dead lever 401 is provided with installation piece 402, and the middle part of installation piece 402 transversely runs through and is provided with screw hole 403, the upper right side of dead lever 401 is provided with axle column 404, and the left side below of dead lever 401 runs through and is provided with fixed bayonet 405.

A foot rest 406 is arranged below the fixing rod 401, shaft blocks 407 are arranged on the front side and the rear side of the top end of the foot rest 406, the shaft blocks 407 are embedded in a fixing bayonet 405 on the fixing rod 401, a swing hole 408 is arranged in the middle of the foot rest 406, a lower shaft column 409 is arranged in the middle of the swing hole 408, and a foam ball 410 is arranged at the bottom of the foot rest 406.

A damper 411 is arranged between the fixing rod 401 and the foot rest 406, a shock absorbing spring 412 is sleeved outside the damper 411, two ends of the shock absorbing spring 412 are connected with baffle plates 413, shaft sleeves 414 are installed outside the baffle plates 413, the shaft sleeve 414 at the top end of the shock absorbing spring 412 is sleeved outside the upper shaft column 404, and the shaft sleeve 414 at the bottom end of the shock absorbing spring 412 is sleeved outside the lower shaft column 409.

In the buffering assembly 4, through the rotary connection between the fixing rod 401 and the foot rest 406, a part of impact force generated when the body lands can be slightly affected to the tight body through an angle conversion mode, and meanwhile, a damping spring 412 and a damper 411 are installed between the fixing rod 401 and the foot rest 406, so that impact shock received when the body lands can be greatly reduced.

The foam ball 410 is arranged at the bottom of the foot rest 406 in the buffer component 4, so that the vibration of the machine body can be reduced when the equipment lands, and meanwhile, the light foam ball 410 is selected, so that the weight of the equipment can be effectively reduced.

The rotor bar 204, the airbag case 301, and the fixing bar 401 are symmetrically disposed and are symmetrical about a vertical center line of the mounting bracket 1.

The working principle is as follows: to the effectual unmanned aerial vehicle landing speed reduction damping device of fixed speed reduction of being convenient for install of this type, when using, at first insert screw hole 403 and mounting bracket 1 and screw up with the installation piece 402 among the buffer component 4 through the bolt, install buffer component 4 on mounting bracket 1.

When the signal patch 203 receives a landing signal, the signal patch 203 transmits the signal to the control box 208, and then the control box 208 controls the power supply inside the power cabin 201 to adjust the power supply current and voltage to the motor 205, so that the rotating speed of the propeller 206 is changed to realize speed reduction and height reduction, and then the motor 205 rotates to drive the propeller 206 to rotate and enable the unmanned aerial vehicle to fly to a preset landing point through the route guidance of the navigator 202.

Meanwhile, the control box 208 and the holder 210 at the bottom of the connecting rod 209 detect the surrounding airspace and the ground environment, when the unmanned aerial vehicle flies above a predetermined landing point, the power cabin 201 starts to gradually reduce the power voltage supply to the motor 205, and the rotating speed of the propeller 206 is reduced to enable the unmanned aerial vehicle to descend.

When unmanned aerial vehicle contact ground, the foam ball 410 in the buffering subassembly 4 at first absorbs some impact force, later, the unmanned aerial vehicle fuselage continues to push down along with inertia, and the atress takes place the angle transform between dead lever 401 and the foot rest 406, and at this moment, attenuator 411 and damping spring 412 receive the extrusion, and attenuator 411 begins the shrink, and damping spring 412 takes place elastic deformation simultaneously, absorbs the impact force when descending unmanned aerial vehicle.

When unmanned aerial vehicle runs into special circumstances and needs to carry out urgent forced landing, cloud platform 210 real-time supervision ground and peripheral airspace condition, it is too fast to detect unmanned aerial vehicle falling speed when cloud platform 210, unmanned aerial vehicle descending angle is uncontrolled and the below is when situations such as the surface of water, cloud platform 210 sends information to control box 208, this moment, control box 208 switch-on gas generator 302 power, and produce a large amount of gas in the twinkling of an eye, gaseous gas pours into gasbag 305 through the mouth 303 of irritating at gasbag box 301 top, gasbag 305 expands rapidly and pops out by the bullet export 304 in the gasbag box 301 outside, include unmanned aerial vehicle, avoid unmanned aerial vehicle to receive violent striking or to sink into the surface of water.

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.