阅读说明：本技术 一种无人驾驶测试用防护装置及其更换方法 (Protection device for unmanned driving test and replacement method thereof ) 是由 王双庆 于 2021-10-20 设计创作，主要内容包括：本发明涉及无人驾驶技术领域,具体为一种无人驾驶测试用防护装置,包括飞行机主体,所述飞行机主体一端的四边皆固定连接有缓冲机构,所述缓冲机构的一侧皆固定连接有防碰撞机构,所述飞行机主体的另一端设置有缓冲降落机构,所述弹簧的另一端与夹块的一端固定连接。本发明小降落伞和大降落伞在受到下坠时风力的影响快速的向外延展开启,可有效的对飞行机主体失控后的下坠力进行良好的缓冲作用,避免飞行机主体在直接在失控后,快速的向地面坠落,造成飞行机主体损坏,通过起落时防护固定条的向外自动张开,可有效的减少机体与路面的接触范围,减少倾斜时,机体直接与路面相抵触,造成的损失。(The invention relates to the technical field of unmanned driving, in particular to a protective device for an unmanned driving test, which comprises a main body of the aircraft, wherein four sides of one end of the main body of the aircraft are fixedly connected with buffer mechanisms, one sides of the buffer mechanisms are fixedly connected with anti-collision mechanisms, the other end of the main body of the aircraft is provided with a buffer descending mechanism, and the other end of a spring is fixedly connected with one end of a clamping block. The small parachute and the large parachute of the invention can be rapidly extended and opened outwards under the influence of wind power when falling, the good buffering effect can be effectively carried out on the falling force of the out-of-control main body of the aircraft, the damage of the main body of the aircraft caused by the rapid falling of the main body of the aircraft to the ground after the out-of-control is avoided, the contact range of the main body and the road surface can be effectively reduced by the outward automatic opening of the protective fixing strips during rising and falling, and the loss caused by the direct contact of the main body and the road surface during the inclination can be reduced.)

1. A protector for unmanned aerial vehicle testing, comprising an aircraft body (100), characterized in that: the four sides of one end of the aircraft main body (100) are fixedly connected with buffer mechanisms (300), one side of each buffer mechanism (300) is fixedly connected with an anti-collision mechanism (200), the other end of the aircraft main body (100) is provided with a buffering descending mechanism (500), one end of each buffering descending mechanism (500) is fixedly connected with the aircraft main body (100) through a quick replacement structure (400), each buffering descending mechanism (500) comprises a storage control bin (510), one end of each storage control bin (510) is provided with a second storage groove (512), a first storage groove (511) is formed in each storage control bin (510), inner walls of two sides of one end of each first storage groove (511) are provided with control grooves (513), the middle end of the inner wall of one end of each first storage groove (511) is fixedly connected with a tensioning mechanism (520), and one end of each tensioning mechanism (520) is connected with one end of a large parachute (514), the inside of groove (512) is accomodate to the second is provided with little parachute (515), and the one end of little parachute (515) passes second and accomodates groove (512) and extend to the inside of first groove (511) of accomodating and be connected with the one end of big parachute (514), the one end of little parachute (515) is provided with fixed plate (516), little parachute (515) are located the inside of fixed plate (516), the both sides of fixed plate (516) one end all are connected with the one end of spring, the other end of spring all is connected with the inner wall of second groove (512) one end of accomodating, motor (517) are installed to one side of first groove (511) one end inner wall of accomodating, the opposite side of first groove (511) one end inner wall of accomodating is provided with spacing rotor plate (527), and the one end of spacing rotor plate (527) is connected with the inner wall of first groove (511) of accomodating through embedded bearing, spacing rotor plate (527) one end and motor (517) output shaft one end all fixedly connected with dwang (519) in the surface, and dwang (519) are close to all fixedly connected with of one end of one side each other and are to touch piece (524), the one end of touch piece (524) all contacts with the surface of fixed plate (516) the surface of collecting control storehouse (510) output shaft and the surface of motor (517) have all cup jointed first gear (518).

2. The protection device for the unmanned aerial vehicle test of claim 1, wherein: a third gear (526) is sleeved at one end of the surface of the tensioning mechanism (520), a limiting rotating plate (527) is sleeved at the other end of the surface of the tensioning mechanism (520), sliding blocks are fixedly connected to both sides of one end of the third gear (526), sliding grooves matched with the sliding blocks are formed in the surface of one end of the limiting rotating plate (527), second gears (525) are arranged on both sides of the third gear (526), one end of a central shaft of each second gear (525) is connected with the inner wall of the first accommodating groove (511) through an embedded bearing, the first gear (518) and the limiting rotating plate (527) are meshed with the second gear (525), the second gears (525) are meshed with the third gear (526), an inserting block (528) is fixedly connected to one end of the accommodating control bin (510), and second buffer grooves (529) are formed in the surfaces of both sides of the inserting block (528), and the inside of second dashpot (529) all is provided with clamp splice (530), and the inside of second dashpot (529) all is provided with the spring, the inner wall of one end of spring and second dashpot (529) is fixed connection mutually, the other end of spring and the one end fixed connection of clamp splice (530).

3. The protection device for the unmanned aerial vehicle test of claim 1, wherein: the tensioning mechanism (520) comprises a second contraction bin (521), a second contraction rod (522) is inserted into one end of the second contraction bin (521), one end of the second contraction rod (522) penetrates through the second contraction bin (521) to extend into the second contraction bin (521), a pull ring (523) is fixedly connected to the other end of the second contraction rod (522), a spring is sleeved on the surface of the second contraction rod (522), one end of the spring is fixedly connected with the surface of the second contraction rod (522), and the other end of the spring is fixedly connected with the inner wall of the second contraction bin (521); both sides of one end of the second contraction rod (522) are fixedly connected with sliding blocks, and sliding grooves matched with the sliding blocks are formed in the inner walls of both sides of the second contraction bin (521).

4. The protection device for the unmanned aerial vehicle test of claim 1, wherein: the buffer mechanism (300) comprises a first contraction bin (310), wherein one end of each first contraction bin (310) is inserted with a first contraction rod (311), one end of each first contraction rod (311) extends into the first contraction bin (310), one end of one side of each first contraction bin (310) is provided with a first buffer groove (313), one side of each first buffer groove (313) is inserted with a fixing rod (314), one end of each fixing rod (314) extends to the outer side of the first contraction bin (310) through penetrating through the first contraction bin (310), the surfaces of the fixing rods (314) are all sleeved with springs, one ends of the springs are fixedly connected with the surfaces of the fixing rods (314), the other ends of the springs are fixedly connected with the inner walls of the first buffer grooves (313), one ends of the surfaces of the first contraction rods (311) are all sleeved with springs, and one ends of the springs are fixedly connected with the surfaces of the first contraction rods (311), the other end of the spring is fixedly connected with the surface of the contact plate (312); one side of one end of the first contraction rod (311) is in an inclined plane shape, and one end of the middle part of the fixing rod (314) is in an inclined plane shape.

5. The protection device for the unmanned aerial vehicle test of claim 4, wherein: both sides of one end of the first contraction rod (311) are fixedly connected with sliding blocks, and sliding grooves matched with the sliding blocks are formed in the inner walls of both sides of the first contraction cabin (310).

6. The protection device for the unmanned aerial vehicle test of claim 4, wherein: the anti-collision mechanism (200) comprises two groups of fixed plates (210), one side of each group of fixed plates (210) is fixedly connected with one side of the first contraction cabin (310), the middle parts of the fixing plates (210) are fixedly connected with shaft rod pieces (211), the surfaces of the shaft rod pieces (211) are sleeved with protective fixing strips (212), the surfaces of the shaft rod pieces (211) are all sleeved with torsion spring pieces (213), and one end of the torsion spring piece (213) is connected with the surface of the shaft rod piece (211), the other end of the torsion spring piece (213) is connected with the inner wall of the protective fixing strip (212), the surface of one end of the protection fixing strip (212) is uniformly and fixedly connected with a protection touch plate (214), one side of the protection fixing strip (212) is fixedly connected with a fixing port (215), one end of the fixing rod (314) passes through the first contraction cabin (310) and extends to the inside of the fixing port (215).

7. The protection device for the unmanned aerial vehicle test of claim 6, wherein: the protection touch plate (214) is arc-shaped, and the protection touch plate (214) and the protection fixing strip (212) form a sledge shape and are outwards scattered.

8. The protection device for the unmanned aerial vehicle test of claim 4, wherein: the other end of the first contraction rod (311) is fixedly connected with a contact plate (312), and the diameter of the contact plate (312) is larger than that of the first contraction rod (311).

9. The protection device for the unmanned aerial vehicle test of claim 1, wherein: quick replacement structure (400) are including fixed storehouse (410), and the inner wall of institute both sides has all been seted up and has been removed storehouse (411), the surface of fixed storehouse (410) both sides all is inserted and is equipped with and presses movable block (412), the one end of pressing movable block (412) all passes fixed storehouse (410) and extends to the inside of removing storehouse (411), the one end of inserted block (528) extends to the inside of fixed storehouse (410), the one end of clamp splice (530) extends to the inside of removing storehouse (411).

10. A method for replacing a protective device for an unmanned driving test is characterized by comprising the following steps: the method comprises the following specific operation steps:

the method comprises the following steps: when the main body (100) of the aircraft encounters a sudden dangerous situation in the flying process, the large parachute (514) and the small parachute (515) are opened outwards, after the main body (100) of the aircraft lands, a user needs to replace the buffering landing mechanism (500), the user presses the pressing block (412) with one hand, and after the pressing block (412) is stressed, the pressing block quickly abuts against the clamping block (530) in the moving bin (411);

step two: after the moving bin (411) is abutted to the clamping block (530), the moving bin is quickly stressed to contract towards the inside of the second buffer groove (529), and a spring in the second buffer groove (529) is extruded;

step three: after the clamping block (530) is completely contracted into the second buffer groove (529), a user can pull the containing control bin (510) to pull the inserting block (528) out of the fixed bin (410), and the user finishes replacing the buffer descending mechanism (500).

Technical Field

The invention relates to the technical field of unmanned driving, in particular to a protection device for an unmanned driving test and a replacement method thereof.

Background

An unmanned plane, called unmanned plane for short, is an unmanned plane operated by radio remote control equipment and a self-contained program control device, or autonomously, either completely or intermittently, by an on-board computer, a drone is often more suitable for tasks that are too foolproof, dirty, or dangerous than a manned aircraft, the drone being able to operate in a very efficient manner, depending on the field of application, the unmanned aerial vehicle can be divided into military use and civil use, the unmanned aerial vehicle is divided into a reconnaissance plane and a target drone, the unmanned aerial vehicle is applied to the industry in the civil use, and is really just needed by the unmanned aerial vehicle;

before unmanned aerial vehicle comes into use, unmanned aerial vehicle manufacturer often can carry out accurate calculation to unmanned aerial vehicle's flight power and flying distance, when unmanned aerial vehicle can fly at effective remote control within range, the flight rate is high-efficient, the operating rate is very fast, if unmanned aerial vehicle is at long-time flight in-process, by external signal of telecommunication interference, when remote control system or unmanned aerial vehicle's flying distance had surpassed self remote control maximum distance, unmanned aerial vehicle often can cause the crash under external or self factor, in the high altitude, unmanned aerial vehicle directly falls, can form very fast acceleration of gravity, when colliding with the opposite face, produce powerful striking, cause unmanned aerial vehicle's damage very easily.

Disclosure of Invention

The invention aims to provide a protective device for unmanned aerial vehicle test and a replacement method thereof, and aims to solve the problems that if an unmanned aerial vehicle is interfered by an external electric signal in the long-time flight process, a remote control system is disturbed, or the flight distance of the unmanned aerial vehicle exceeds the maximum distance of the remote control of the unmanned aerial vehicle, the unmanned aerial vehicle often crashes under external or self factors, and the unmanned aerial vehicle directly falls in high altitude, forms faster gravity acceleration and generates strong impact when colliding with an opposite surface.

In order to achieve the purpose, the invention provides the following technical scheme: a protective device for unmanned driving test and a replacement method thereof comprise a main body of the aircraft, wherein four sides of one end of the main body of the aircraft are fixedly connected with a buffer mechanism, one side of the buffer mechanism is fixedly connected with an anti-collision mechanism, the other end of the main body of the aircraft is provided with a buffering descending mechanism, one end of the buffering descending mechanism is fixedly connected with the main body of the aircraft through a quick replacement structure, the buffering descending mechanism comprises a storage control bin, one end of the storage control bin is provided with a second storage groove, the interior of the storage control bin is provided with a first storage groove, the inner walls of two sides of one end of the first storage groove are provided with control grooves, the middle end of the inner wall of one end of the first storage groove is fixedly connected with a tensioning mechanism, one end of the tensioning mechanism is connected with one end of a large parachute, and the interior of the second storage groove is provided with a small parachute, and the one end of little parachute passes the second and accomodates the inside that the groove extended to the first groove of accomodating and is connected with the one end of big parachute, the one end of little parachute is provided with fixed plate, little parachute is located the inside of fixed plate, the both sides of fixed plate one end all are connected with the one end of spring, the other end of spring all is connected with the inner wall that the groove one end was accomodate to the second, the motor is installed to the first one side of accomodating groove one end inner wall, the first opposite side of accomodating groove one end inner wall is provided with spacing rotor plate, and the one end of spacing rotor plate is connected with the first inner wall of accomodating the groove through embedded bearing, the surperficial all fixedly connected with dwang of spacing rotor plate one end and motor output shaft one end, and the dwang is close to the all fixedly connected with of one end of one side each other and supports the touch piece, the one end that supports touch piece all contacts with the surface of fixed plate the surface of accomodating control storehouse output shaft and the surface of motor all have cup jointed first gear .

Preferably, a third gear is sleeved at one end of the surface of the tensioning mechanism, a limit rotating plate is sleeved at the other end of the surface of the tensioning mechanism, sliders are fixedly connected to both sides of one end of each third gear, a sliding chute matched with the sliders is formed in the surface of one end of each limit rotating plate, second gears are arranged on both sides of each third gear, one ends of central shafts of the second gears are connected with the inner wall of the first accommodating groove through embedded bearings, the first gears and the limit rotating plates are meshed with the second gears, the second gears are meshed with the third gears, an inserting block is fixedly connected to one end of the accommodating control bin, second buffer grooves are formed in both sides of the inserting block, clamping blocks are arranged inside the second buffer grooves, springs are arranged inside the second buffer grooves, one ends of the springs are fixedly connected with the inner wall of one ends of the second buffer grooves, the other end of the spring is fixedly connected with one end of the clamping block.

Preferably, the tensioning mechanism comprises a second contraction cabin, a second contraction rod is inserted into one end of the second contraction cabin, one end of the second contraction rod penetrates through the second contraction cabin and extends to the inside of the second contraction cabin, a pull ring is fixedly connected to the other end of the second contraction rod, a spring is sleeved on the surface of the second contraction rod, one end of the spring is fixedly connected with the surface of the second contraction rod, and the other end of the spring is fixedly connected with the inner wall of the second contraction cabin.

The both sides of second shrink pole one end all fixedly connected with slider, the inner wall at second shrink storehouse both sides has all been seted up with slider matched with spout.

Preferably, buffer gear includes first shrink storehouse, the one end in first shrink storehouse is all inserted and is equipped with first shrink pole, the one end of first shrink pole all extends to the inside in first shrink storehouse, first dashpot has all been seted up to the one end of first shrink storehouse one side, the dead lever has all been inserted to one side of first dashpot, the one end of dead lever all passes to run through first shrink storehouse and extends to the outside in first shrink storehouse, the surface of dead lever all is equipped with the spring, the one end of spring is connected with the fixed surface of dead lever, the other end of spring all with the inner wall fixed connection of first dashpot, the one end on first shrink pole surface all is equipped with the spring, the one end of spring all is connected with the fixed surface of first shrink pole, the other end of spring all with the fixed surface connection of contact plate. One side of one end of the first contraction rod is in an inclined plane shape, and one end of the middle part of the fixed rod is in an inclined plane shape.

Preferably, both sides of one end of the first contraction rod are fixedly connected with sliding blocks, and sliding grooves matched with the sliding blocks are formed in the inner walls of both sides of the first contraction cabin.

Preferably, anticollision mechanism includes fixed plate, fixed plate is two sets of, and is two sets of one side of fixed plate all with one side fixed connection in first shrink storehouse, the middle part of fixed plate all fixedly connected with axle member, the surface of axle member all overlaps and is equipped with the protection fixed strip, the surface of axle member all overlaps and is equipped with the torsion spring part, and the one end of torsion spring part all is connected with the surface of axle member, the other end of torsion spring part all is connected with the inner wall of protection fixed strip, the even fixedly connected with in surface protection of protection fixed strip one end supports the touch panel, one side fixedly connected with fixed orifices of protection fixed strip, the one end of dead lever is passed first shrink storehouse and is extended to the inside of fixed orifices.

Preferably, the protection touch panel is arc-shaped, and the protection touch panel and the protection fixing strip form a sledge shape and are scattered outwards.

Preferably, the other end of the first shrinkage rod is fixedly connected with a contact plate, and the diameter of the contact plate is larger than that of the first shrinkage rod.

Preferably, the quick replacement structure includes fixed storehouse, and the inner wall of both sides has all been seted up and has been removed the storehouse, the surface of fixed storehouse both sides all is inserted and is equipped with according to the piece, the one end of pressing the piece all passes fixed storehouse and extends to the inside that removes the storehouse, the one end of inserted block extends to the inside in fixed storehouse, the one end of clamp splice extends to the inside that removes the storehouse.

A method for replacing a protective device for an unmanned driving test is characterized by comprising the following steps: the method comprises the following specific operation steps:

the method comprises the following steps: when the main body of the aircraft encounters a sudden dangerous situation in the flying process, the large parachute and the small parachute are opened outwards, after the main body of the aircraft lands on the ground, a user needs to replace the buffering parachute mechanism, the user presses the pressing block with one hand, and after the pressing block is stressed, the pressing block quickly abuts against the clamping block in the moving bin;

step two: after the moving bin is abutted against the clamping block, the moving bin is quickly stressed to contract towards the inside of the second buffer groove, and a spring in the second buffer groove is extruded;

step three: after the clamp splice contracts to the inside of second dashpot completely, the user can pull up the storage control storehouse, extracts the inserted block from the inside in fixed storehouse, and the user accomplishes the change to buffering descending mechanism.

Compared with the prior art, the invention has the beneficial effects that: the small parachute and the large parachute can be rapidly extended outwards to open under the influence of wind power when falling, the good buffering effect can be effectively realized on the falling force of the out-of-control main body of the aircraft, the main body of the aircraft is prevented from rapidly falling to the ground after being directly out of control, the main body of the aircraft is prevented from being damaged, the contact range of the aircraft body and the road surface can be effectively reduced by the outward automatic opening of the protection fixing strips during rising and falling, and the loss caused by the fact that the aircraft body directly abuts against the road surface during inclination is reduced;

1. by arranging the buffering landing mechanism, if the flight remote control system of the unmanned aerial vehicle is interfered by an external electric signal or the remote control flight distance of the unmanned aerial vehicle exceeds the maximum flight to form in the long-time flight process of the unmanned aerial vehicle, when the unmanned aerial vehicle loses control during control and generates falling force, a user can use another remote control interrupt end to quickly open the motor, after the motor is opened, the motor quickly links the limiting rotating plate, the rotating rod rotates to link the abutting block, the abutting block does not abut against the fixed plate any more, so that the fixed plate is quickly ejected to the external environment, then the small parachute and the large parachute are quickly extended outwards under the influence of wind force during falling to open, the good buffering effect can be effectively performed on the falling force after the main body of the flying machine is out of control, certain resistance is formed, and the main body of the flying machine is prevented from being directly out of control, the quick ground that falls forms great impact, causes the aircraft main part to damage, when meetting proruption situation to the aircraft main part, has carried out good maintenance, very big reinforcing the device in-service use's practical value, made things convenient for user's use, the user uses more simply convenient.

2. By arranging the anti-collision mechanism and the buffer mechanism, when the main body of the aircraft is lifted and descended downwards, the contact plate can be contacted with the ground firstly, after the first contraction rod is stressed, the first contraction rod is contracted into the first contraction cabin quickly and is continuously abutted against the fixed rod, the fixed rod continuously moves towards one side of the first buffer slot, the inside of one end of the fixed rod which is separated from the first buffer slot quickly is not fixed any more, the protection fixing strip can be automatically outwards unfolded through the protection fixing strip, if the main body of the aircraft descends, the main body rises and falls onto a road surface with one uneven end, the main body of the aircraft is directly contacted with the ground, the aircraft is easy to generate certain toppling force, the main body of the aircraft can generate skew and even fall, the contact range between the main body and the road surface can be effectively reduced by outwards automatically unfolding the protection fixing strip when the main body is lifted and falls, the main body of the aircraft directly abuts against the road surface when the inclination is reduced, and the loss is caused, the organism has been protected to the fine for the device's protecting effect becomes better, has strengthened the practical scope of user to the device simultaneously to certain degree.

Drawings

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

fig. 2 is a schematic structural front sectional view of an anti-collision mechanism and a buffer mechanism according to the present invention;

FIG. 3 is a schematic sectional view of the buffering descending mechanism in front view;

FIG. 4 is a schematic sectional elevation view of a quick-change structure according to the present invention;

FIG. 5 is an enlarged view of the structure A in FIG. 3 according to the present invention;

FIG. 6 is a schematic sectional front view of the tension mechanism of the present invention;

FIG. 7 is a schematic view of the present invention in an expanded configuration;

FIG. 8 is an enlarged view of the structure of B in FIG. 7 according to the present invention;

FIG. 9 is an enlarged view of the structure of C in FIG. 7 according to the present invention;

fig. 10 is a schematic front view of the structure of the present invention.

In the figure: 100. an aircraft body; 200. an anti-collision mechanism; 210. fixing the plate; 211. a shaft member; 212. a protective fixing strip; 213. a torsion spring member; 214. a protective touch plate; 215. a fixed port; 300. a buffer mechanism; 310. a first retraction bin; 311. a first retracting lever; 312. a contact plate; 313. a first buffer tank; 314. fixing the rod; 400. a quick replacement structure; 410. fixing the bin; 411. moving the bin; 412. pressing the block; 500. a buffering landing mechanism; 510. a storage control bin; 511. a first receiving groove; 512. a second receiving groove; 513. a control slot; 514. a large parachute; 515. a small parachute; 516. fixing a plate; 517. a motor; 518. a first gear; 519. rotating the rod; 520. a tensioning mechanism; 521. a second shrinking bin; 522. a second retracting lever; 523. a pull ring; 524. a contact block; 525. a second gear; 526. a third gear; 527. a limiting rotating plate; 528. inserting a block; 529. a second buffer tank; 530. and (5) clamping blocks.

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 of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring to fig. 1-10, an embodiment of the present invention is shown:

a protective device for unmanned driving test and a replacement method thereof comprise a main body 100 of the aircraft, wherein four sides of one end of the main body 100 of the aircraft are fixedly connected with a buffer mechanism 300, one side of the buffer mechanism 300 is fixedly connected with an anti-collision mechanism 200, the other end of the main body 100 of the aircraft is provided with a buffer descending mechanism 500, one end of the buffer descending mechanism 500 is fixedly connected with the main body 100 of the aircraft through a quick replacement structure 400, the buffer descending mechanism 500 comprises a storage control bin 510, one end of the storage control bin 510 is provided with a second storage groove 512, the interior of the storage control bin 510 is provided with a first storage groove 511, the inner walls of two sides of one end of the first storage groove 511 are provided with control grooves 513, the middle end of the inner wall of one end of the first storage groove 511 is fixedly connected with a tensioning mechanism 520, one end of the tensioning mechanism 520 is connected with one end of a big parachute 514, the interior of the second storage groove 512 is provided with a small parachute 515, one end of the small parachute 515 penetrates through the second accommodating groove 512 and extends to the inside of the first accommodating groove 511 to be connected with one end of the large parachute 514, a fixed plate 516 is arranged at one end of the small parachute 515, the small parachute 515 is located inside the fixed plate 516, two sides of one end of the fixed plate 516 are connected with one end of a spring, the other end of the spring is connected with the inner wall of one end of the second accommodating groove 512, a motor 517 is installed at one side of the inner wall of one end of the first accommodating groove 511, a limiting rotating plate 527 is arranged at the other side of the inner wall of one end of the first accommodating groove 511, one end of the limiting rotating plate 527 is connected with the inner wall of the first accommodating groove 511 through an embedded bearing, a rotating rod 519 is fixedly connected to one end of the limiting rotating plate 527 and one end of an output shaft of the motor 517, a butting block 524 is fixedly connected to one end of the rotating rod 519 close to one side of the other, one end of the butting block 524 is in contact with the surface of the fixed plate 516 and accommodates the surface of the output shaft 510 of the control cabin and the motor 517 The first gear 518 is sleeved, and a third gear 526 is sleeved at one end of the surface of the tensioning mechanism 520.

Further, the other end of the surface of the tensioning mechanism 520 is sleeved with a limit rotating plate 527, both sides of one end of the third gear 526 are fixedly connected with sliders, a sliding groove matched with the slider is formed in the surface of one end of the limit rotating plate 527, both sides of the third gear 526 are provided with second gears 525, one end of the central shaft of the second gear 525 is connected with the inner wall of the first accommodating groove 511 through an embedded bearing, the first gear 518 and the limit rotating plate 527 are engaged with the second gear 525, the second gear 525 is engaged with the third gear 526, one end of the accommodating control bin 510 is fixedly connected with an inserting block 528, the surfaces of the two sides of the inserting block 528 are provided with second buffer grooves 529, and the inside of the second buffer grooves 529 is provided with a clamping block 530, a spring is arranged in each second buffer groove 529, one end of the spring is fixedly connected with the inner wall of one end of the second buffer groove 529, and the other end of the spring is fixedly connected with one end of the clamping block 530;

further, the tensioning mechanism 520 includes a second contracting cabin 521, a second contracting rod 522 is inserted into one end of the second contracting cabin 521, one end of the second contracting rod 522 passes through the second contracting cabin 521 and extends into the second contracting cabin 521, a pull ring 523 is fixedly connected to the other end of the second contracting rod 522, a spring is sleeved on the surface of the second contracting rod 522, one end of the spring is fixedly connected to the surface of the second contracting rod 522, the other end of the spring is fixedly connected to the inner wall of the second contracting cabin 521, when the large parachute 514 extends outwards, a rope lock winding part at one end of the large parachute 514 can rapidly pull the pull ring 523 to enable the second contracting rod 522 to move towards the inside of the second contracting cabin 521 continuously, and the spring is sleeved on the surface of the second contracting rod 522, after the spring is stressed, rapid deformation occurs, therefore, when the large parachute 514 is continuously outwards, the rope of the large parachute 514 can be simply pulled effectively, the tension influence of the rope is avoided, and when the large parachute 514 is directly unfolded, the rope can be effectively tensioned through the relaxation force formed on the rope;

both sides of one end of the second contraction rod 522 are fixedly connected with sliding blocks, the inner walls of both sides of the second contraction cabin 521 are provided with sliding grooves matched with the sliding blocks, when the second contraction rod 522 is continuously stressed to move in the second contraction cabin 521, the sliding blocks rapidly slide in the sliding grooves, and the sliding blocks are matched with the sliding grooves, so that the movement track of the second contraction rod 522 can be effectively limited;

further, the buffer mechanism 300 includes a first shrinkage bin 310, a first shrinkage rod 311 is inserted into one end of the first shrinkage bin 310, one end of the first shrinkage rod 311 extends into the first shrinkage bin 310, a first buffer slot 313 is disposed at one end of one side of the first shrinkage bin 310, a fixing rod 314 is inserted into one side of the first buffer slot 313, one end of the fixing rod 314 passes through the first shrinkage bin 310 and extends to the outside of the first shrinkage bin 310, springs are sleeved on the surfaces of the fixing rods 314, one ends of the springs are fixedly connected with the surface of the fixing rod 314, the other ends of the springs are fixedly connected with the inner wall of the first buffer slot 313, springs are sleeved on one end of the surface of the first shrinkage rod 311, one ends of the springs are fixedly connected with the surface of the first shrinkage rod 311, the other ends of the springs are fixedly connected with the surface of the contact plate 312, when the aircraft main body 100 directly falls down and contacts with the ground, the contact plate 312 can be firstly contacted with the ground to quickly act on the first contraction rod 311, the first contraction rod 311 can be continuously contracted towards the inside of the first contraction cabin 310, after the fixed rod 314 is stressed, the first contraction rod 311 can quickly move towards one side of the first buffer groove 313 and continuously move outwards in the first buffer groove 313, the surface of the fixed rod 314 is sleeved with a spring to quickly deform when the fixed rod 314 moves, and the fixed rod 314 is continuously fixed on the protection fixing strip 212 until one end of the fixed rod 314 leaves the inside of the fixing opening 215;

one side of one end of the first contraction rod 311 is in an inclined plane shape, one end of the middle part of the fixed rod 314 is in an inclined plane shape, and one side of one end of the first contraction rod 311 and one end of the middle part of the fixed rod 314 are in an inclined plane shape;

further, the both sides of first shrink pole 311 one end all fixedly connected with slider, the inner wall of first shrink storehouse 310 both sides all seted up with slider matched with spout, first shrink pole 311 when first shrink storehouse 310 is inside to be moved, drives the slider and slides in the inside of first shrink storehouse 310 simultaneously, cooperatees through slider and spout, can effectually prescribe a limit to the motion trail in first shrink storehouse 310.

Further, the anti-collision mechanism 200 includes two groups of fixing plates 210, where the two groups of fixing plates 210 are provided, one side of each of the two groups of fixing plates 210 is fixedly connected to one side of the first contracting chamber 310, the middle part of each of the fixing plates 210 is fixedly connected to a shaft member 211, the surface of each of the shaft members 211 is sleeved with a protective fixing strip 212, the surface of each of the shaft members 211 is sleeved with a torsion spring member 213, one end of each of the torsion spring members 213 is connected to the surface of the shaft member 211, the other end of each of the torsion spring members 213 is connected to the inner wall of the protective fixing strip 212, the surface of one end of each of the protective fixing strips 212 is uniformly and fixedly connected to a protective touch plate 214, one side of each of the protective fixing strips 212 is fixedly connected to a fixing port 215, one end of each of the fixing rod 314 passes through the first contracting chamber 310 and extends into the fixing port 215, and when one end of the fixing rod 314 leaves the inside of the fixing port 215, the fixing rod 314 is not fixed to the protective fixing strip 212, through the resilience force of the torsion spring piece 213, the protection touch plate 214 and the protection fixing strip 212 can be driven to reset automatically, and the protection touch plate is opened quickly, so that the contact area between the machine body and the ground is effectively reduced.

Further, the protection touch panel 214 is arc-shaped, the protection touch panel 214 and the protection fixing strip 212 form a sledge shape and are scattered outwards, when the aircraft main body 100 descends and falls, the protection touch panel 214 is firstly opened and then directly contacts with the ground, the protection touch panel 214 is arc-shaped, the contact surface of the aircraft body when the aircraft body directly contacts with the ground can be effectively reduced, the protection touch panel 214 and the protection fixing strip 212 form a sledge shape, and when the aircraft main body 100 flies, the resistance generated by the aircraft main body 100 in ascending flight is reduced.

Furthermore, the other end of the first telescopic rod 311 is fixedly connected with a contact plate 312, the diameter of the contact plate 312 is larger than that of the first telescopic rod 311, the contact surface machine of the first telescopic rod 311 contacting with the ground can be greatly increased through the contact plate 312, and the stress effect of the first telescopic rod 311 is increased.

Further, quick replacement structure 400 includes fixed storehouse 410, the inner wall of both sides has all been seted up and has been removed the storehouse 411, the surface of fixed storehouse 410 both sides is all inserted and is equipped with and presses piece 412, the one end that presses piece 412 all passes fixed storehouse 410 and extends to the inside that removes storehouse 411, the one end of inserted block 528 extends to the inside of fixed storehouse 410, the one end of clamp splice 530 extends to the inside that removes storehouse 411, through quick replacement structure 400, user's accessible presses and presses piece 412, make and press piece 412 to be inconsistent with clamp splice 530 fast in the inside that removes storehouse 411, clamp splice 530 atress back, shrink to the inside of second dashpot 529 fast, the user then can dismantle the change to buffering descending mechanism 500 fast.

A method for replacing a protective device for an unmanned driving test is characterized by comprising the following steps: the method comprises the following specific operation steps:

the method comprises the following steps: when the aircraft main body 100 encounters a sudden dangerous situation in the flying process, the large parachute 514 and the small parachute 515 are opened outwards, and after the aircraft main body 100 falls to the ground, a user needs to replace the buffering parachute mechanism 500, the user presses the pressing block 412 with one hand, and after the pressing block 412 is stressed, the pressing block is quickly abutted against the clamping block 530 in the moving bin 411;

step two: after the moving bin 411 is abutted to the clamping block 530, the moving bin is quickly stressed to contract towards the inside of the second buffer groove 529, and a spring in the second buffer groove 529 is extruded;

step three: after the clamping block 530 is completely retracted into the second buffer slot 529, the user can pull the storage control chamber 510 to pull the inserting block 528 out of the fixed chamber 410, and the user completes the replacement of the buffer descending mechanism 500.

The working principle is as follows: when a user uses the device, the user firstly needs to connect the motor 517 with an external remote control switch electric signal, if the main body 100 of the aircraft suddenly encounters external electric signal interference or the aircraft body remote control interval exceeds the maximum stroke and falls, the user can quickly press the external switch electric signal to turn on the motor 517, when the motor 517 is turned on, the output shaft of the motor 517 quickly drives the output shaft to quickly rotate in the first accommodating groove 511, the rotation quickly drives the first gear 518 to do equidirectional motion simultaneously, so that the first gear 518 is continuously meshed with the second gear 525 to interlock the first gear, when the second gear 525 rotates, the second gear 525 can be quickly meshed with the third gear 526, so that the third gear 526 can perform high-degree rotary motion on the surface of the second contracting cabin 521, when the third gear 526 rotates, the limit rotary plate 527 on the other side can be quickly abutted, after the output end of the motor 517 is turned on, the limiting rotation plate 527 simultaneously moves in the same direction, the abutting block 524 can simultaneously rotate, the abutting block 524 continuously leaves the inside of the second accommodating groove 512 and is not abutted to one end of the fixed plate 516 any more, until the abutting block 524 rotates to place the inside of the control groove 513, the small parachute 515 can rapidly perform spring reset after being not extruded any more, strong spring force rapidly ejects the fixed plate 516 outwards, the small parachute 515 rapidly receives external wind force in the inside of the second accommodating groove 512 and rapidly extends outwards, the large parachute 514 is driven to extend outwards and simultaneously, when the large parachute 514 extends outwards, a rope lock winding part at one end of the large parachute 514 can rapidly pull the pull ring 523 to move the second contraction rod 522 continuously in the inside of the second contraction cabin 521, and the spring is sleeved on the surface of the second contraction rod 522, after the spring is stressed, the spring is quickly deformed, so that when the large parachute 514 continuously outwards stretches, the rope of the large parachute 514 can be effectively and simply pulled, the tension influence of rope retraction is avoided, and when the large parachute 514 is directly unfolded, the rope can be effectively tensioned through the relaxation force formed on the rope;

if the aircraft main body 100 falls on the ground with an uneven road surface during normal use at ordinary times, when the aircraft main body 100 directly falls down to contact with the ground, the contact plate 312 can firstly contact with the ground, after the contact plate 312 is stressed, the first contraction rod 311 is quickly acted, the first contraction rod 311 is continuously contracted towards the inside of the first contraction cabin 310, when the first contraction rod 311 moves to a certain position in the first contraction cabin 310, the first contraction rod 311 is continuously abutted against the fixed rod 314 in the first contraction cabin 310, after the fixed rod 314 is stressed, the first contraction rod 311 quickly moves towards one side of the first buffer groove 313, the first buffer groove 313 is continuously pulled outwards, when the fixed rod 314 moves, the surface of the fixed rod 314 is sleeved with a spring, the fixed rod is quickly deformed until one end of the fixed rod 314 leaves the inside of the fixed port 215, and the fixed rod 314 does not fix the protection fixed strip 212, through torsion spring member 213's resilience force, can drive fast and protect and support touch panel 214 and protect fixed strip 212 automation and reset, open outside the quick shape, after the direct uneven road surface of aircraft main part 100 contacts, when taking place to empty, protect fixed strip 212 and outwards open fast, protect fixed strip 212 at first can with road surface mutual contact, reduce the area of aircraft main part 100 directness and road surface contact, avoid directly empting, easily cause the damage of aircraft main part 100 screw machine and organism.

It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.