阅读说明：本技术 一种遥感无人机结构 (Remote sensing unmanned aerial vehicle structure ) 是由 倪超 于 2021-01-05 设计创作，主要内容包括：本发明涉及无人机,更具体的说是一种遥感无人机结构,包括飞行支架、摆动机构、飞行臂和飞行机构,所述摆动机构设置有两个,飞行臂设置有两个,飞行机构设置有两个,两个摆动机构均连接在飞行支架上,两个飞行臂分别连接在两个摆动机构上,两个飞行机构分别连接在两个摆动机构和两个飞行臂上,可以通过支撑机构对装置进行地面上的支撑,摆动机构驱动飞行臂进行多位置的摆动,飞行臂带动飞行机构进行收展,进而在摆动机构和飞行臂的带动下飞行机构进行多方位运动,可以大幅度的改变飞行机构的位置,同时冲击机构在装置的起飞和飞行过程中,启动辅助飞行的作用,使得装置可以进行弹射起飞,并且可以在飞行中突然加速。(The invention relates to an unmanned aerial vehicle, in particular to a remote sensing unmanned aerial vehicle structure, which comprises two flying supports, two swinging mechanisms, two flying arms and two flying mechanisms, wherein the two swinging mechanisms are arranged on the two flying arms, the two flying mechanisms are connected on the flying supports, the two flying arms are respectively connected on the two swinging mechanisms, the two flying mechanisms are respectively connected on the two swinging mechanisms and the two flying arms, the device can be supported on the ground through a supporting mechanism, the swinging mechanisms drive the flying arms to swing at multiple positions, the flying arms drive the flying mechanisms to fold and unfold, and then the flying mechanisms move in multiple directions under the driving of the swinging mechanisms and the flying arms, the positions of the flying mechanisms can be greatly changed, and simultaneously, the impact mechanisms start the function of assisting in flying in the taking off and flying processes of the device, so that the device can perform catapult take-off and can suddenly accelerate in flight.)

1. The utility model provides a remote sensing unmanned aerial vehicle structure, includes flight support (1), swing mechanism (3), flight arm (4) and flight mechanism (5), its characterized in that: the aircraft is characterized in that the two swing mechanisms (3) are arranged, the two flying arms (4) are arranged, the two flying mechanisms (5) are arranged, the two swing mechanisms (3) are connected to the flying support (1), the two flying arms (4) are connected to the two swing mechanisms (3) respectively, and the two flying mechanisms (5) are connected to the two swing mechanisms (3) and the two flying arms (4) respectively.

2. The remote sensing unmanned aerial vehicle structure of claim 1, wherein: the flying support (1) comprises side supports (101), connecting supports (102), a clearance ball cavity (103) and auxiliary wings (104), wherein the number of the side supports (101) is two, the connecting supports (102) are fixedly connected between the middle parts of the two side supports (101), the auxiliary wings (104) are fixedly connected between the rear ends of the two side supports (101), and the clearance ball cavity (103) is fixedly connected to the outer sides of the two side supports (101).

3. The remote sensing unmanned aerial vehicle structure of claim 2, wherein: swing mechanism (3) are including swing motor I (301), swing support (302), sideslip motor (303), sideslip slider (304), rotate support (305) and slide cartridge (306), fixedly connected with swing support (302) on the output shaft of swing motor I (301), fixedly connected with sideslip motor (303) on swing support (302), there are sideslip slider (304) through threaded connection on the output shaft of sideslip motor (303), sideslip slider (304) sliding connection is on swing support (302), it is connected with rotation support (305) to rotate on sideslip slider (304), fixedly connected with slide cartridge (306) on rotation support (305), two swing motor I (301) of fixedly connected with on linking bridge (102).

4. The remote sensing unmanned aerial vehicle structure of claim 3, wherein: flight arm (4) are including sliding column (401), clearance spheroid (402), articulated support (403), receive and expand motor I (404) and receive and expand arm (405), sliding column (401) are gone up gapped spheroid (402) of fixed connection, the tip fixedly connected with articulated support (403) of sliding column (401), articulated support (403) are gone up fixedly connected with and are received and expanded motor I (404), fixedly connected with receive and expand arm (405) on the output shaft of receive and expand motor I (404), equal sliding connection has sliding column (401) on two sliding tubes (306), two clearance spheroid (402) are clearance fit respectively in two clearance ball cavitys (103).

5. The remote sensing unmanned aerial vehicle structure of claim 4, wherein: flight mechanism (5) are including taking up and spreading out motor II (501), flight arm (502), take up and spread pivot (503), flight motor I (504) and flight spiral I (505), it connects to take up and spread motor II (501) and take up and spread pivot (503) transmission, fixedly connected with flight arm (502) on taking up and spread pivot (503), two flight motor I (504) of fixedly connected with on flight arm (502), equal fixedly connected with flight spiral I (505) on the output shaft of two flight motor I (504), equal fixedly connected with takes up and spreads out motor II (501) on two articulated brackets (403), the output shaft of taking up and spreading out motor II (501) and the coaxial setting of output shaft of taking up and spreading out motor I (404), it rotates to connect on taking up and spreading out arm (405) to take up and spread pivot (503).

6. The remote sensing unmanned aerial vehicle structure of claim 5, wherein: the remote sensing unmanned aerial vehicle structure still includes supporting mechanism (2), supporting mechanism (2) are including supporting motor (201), a support section of thick bamboo (202), support holder (203) and support arm (204), support motor (201) fixed connection is on linking bridge (102), a support section of thick bamboo (202) are provided with two, equal fixedly connected with support holder (203) on two support sections of thick bamboo (202), both ends are all rotated around two support holders (203) and are connected with support arm (204), fixedly connected with torsional spring between support arm (204) and the support holder (203), two support sections of thick bamboo (202) are all connected with the output shaft transmission of support motor (201), two support sections of thick bamboo (202) rotate respectively and are connected on two collateral branch framves (101).

7. The remote sensing unmanned aerial vehicle structure of claim 6, wherein: the remote sensing unmanned aerial vehicle structure still includes impact mechanism (6), impact mechanism (6) are including swing motor II (601), impact cavity (602), flying motor II (603), flight spiral II (604), air compressing mechanism (605) and jam post (606), swing motor II (601) fixed connection is on linking bridge (102), impact cavity (602) and rotate to be connected between two collateral branch framves (101), the output shaft transmission of impact cavity (602) and swing motor II (601) is connected, two flying motor II (603) of fixedly connected with on impact cavity (602), equal fixedly connected with flight spiral II (604) on the output shaft of two flying motor II (603), fixedly connected with air compressing mechanism (605) on flying motor II (603), fixedly connected with jam post (606) in flying motor II (603).

8. The remote sensing unmanned aerial vehicle structure of claim 7, wherein: remote sensing unmanned aerial vehicle structure still includes stop gear (7), stop gear (7) include telescopic machanism (701), block up stopper (702) and fumarole (703), telescopic machanism (701) fixed connection is on assaulting cavity (602), fixedly connected with blocks up stopper (702) on telescopic machanism's (701) flexible end, be provided with fumarole (703) on blocking up stopper (702), block up stopper (702) and block up the lower extreme at assaulting cavity (602), block up post (606) and block up in fumarole (703).

Technical Field

The invention relates to an unmanned aerial vehicle, in particular to a remote sensing unmanned aerial vehicle structure.

Background

For example, the publication number CN211893673U discloses an unmanned aerial vehicle flight anti-collision device, which comprises an unmanned aerial vehicle body, wherein an anti-collision body is fixedly mounted at the top of the unmanned aerial vehicle body, a first bolt is movably arranged at the top of the anti-collision body, a connecting rod is movably arranged at the bottom of the unmanned aerial vehicle body, a sliding ring is movably arranged on the outer wall of the connecting rod, a first anti-collision rod is fixedly mounted outside the sliding ring, the first anti-collision rod is distributed on the outer wall of the sliding ring in a cross shape, a first anti-collision ring is fixedly mounted on the outer wall of the first anti-collision rod, an electric telescopic device is fixedly mounted at the bottom of the connecting rod, a second anti-collision ring is fixedly arranged at the bottom of the electric telescopic device, a second anti-collision rod is fixedly mounted on the inner wall of the; the utility model has the defect that the position of the flying arm can not be greatly changed.

Disclosure of Invention

The invention aims to provide a remote sensing unmanned aerial vehicle structure which can greatly change the position of a flying arm.

The purpose of the invention is realized by the following technical scheme:

the utility model provides a remote sensing unmanned aerial vehicle structure, includes flight support, swing mechanism, flight arm and flight mechanism, swing mechanism is provided with two, and the flight arm is provided with two, and flight mechanism is provided with two, and two swing mechanisms all connect on flight support, and two flight arms are connected respectively on two swing mechanisms, and two flight mechanisms are connected respectively on two swing mechanisms and two flight arms.

As a further optimization of the technical scheme, the remote sensing unmanned aerial vehicle structure comprises two flying supports, two connecting supports, a gap ball cavity and two auxiliary wings, wherein the connecting supports are fixedly connected between the middle parts of the two flying supports, the auxiliary wings are fixedly connected between the rear ends of the two flying supports, and the gap ball cavity is fixedly connected to the outer sides of the two flying supports.

According to the remote sensing unmanned aerial vehicle structure, the swing mechanism comprises a swing motor I, a swing support, a transverse moving motor, a transverse moving sliding block, a rotating support and a sliding cylinder, the swing support is fixedly connected to an output shaft of the swing motor I, the transverse moving motor is fixedly connected to the swing support, the transverse moving sliding block is connected to the output shaft of the transverse moving motor through threads, the transverse moving sliding block is connected to the swing support in a sliding mode and is connected to the transverse moving sliding block in a rotating mode, the rotating support is fixedly connected to the sliding cylinder, and the connecting support is fixedly connected with the two swing motors I.

As a further optimization of the technical scheme, the remote sensing unmanned aerial vehicle structure comprises a flight arm, a gap ball, a hinged support, a folding and unfolding motor I and a folding and unfolding arm, wherein the gap ball is fixedly connected to the flight arm, the hinged support is fixedly connected to the end of the flight arm, the folding and unfolding motor I is fixedly connected to the hinged support, the folding and unfolding arm is fixedly connected to an output shaft of the folding and unfolding motor I, the sliding cylinders are both slidably connected to the sliding columns, and the two gap balls are respectively in clearance fit in two gap ball cavities.

According to the technical scheme, the remote sensing unmanned aerial vehicle structure comprises a folding and unfolding motor II, a flight arm, a folding and unfolding rotating shaft, a flight motor I and a flight screw I, wherein the folding and unfolding motor II is in transmission connection with the folding and unfolding rotating shaft, the flight arm is fixedly connected to the folding and unfolding rotating shaft, the flight arm is fixedly connected with the two flight motors I, the flight screw I is fixedly connected to output shafts of the two flight motors I, the folding and unfolding motor II is fixedly connected to two hinged supports, the output shaft of the folding and unfolding motor II and the output shaft of the folding and unfolding motor I are coaxially arranged, and the folding and unfolding rotating shaft is rotatably connected to the folding and unfolding arm.

As a further optimization of the technical scheme, the remote sensing unmanned aerial vehicle structure further comprises a supporting mechanism, the supporting mechanism comprises a supporting motor, two supporting cylinders, two supporting supports and two supporting arms, the supporting motor is fixedly connected to the connecting support, the two supporting cylinders are fixedly connected to the two supporting cylinders, the supporting arms are rotatably connected to the front end and the rear end of the two supporting supports, torsion springs are fixedly connected between the supporting arms and the supporting supports, the two supporting cylinders are in transmission connection with output shafts of the supporting motors, and the two supporting cylinders are rotatably connected to the two side supports respectively.

According to the technical scheme, the remote sensing unmanned aerial vehicle structure further comprises an impact mechanism, the impact mechanism comprises a swing motor II, an impact cavity, a flight motor II, a flight screw II, an air compressing mechanism and a blocking column, the swing motor II is fixedly connected to a connecting support, the impact cavity is rotatably connected between two side supports, the impact cavity is in transmission connection with an output shaft of the swing motor II, the impact cavity is fixedly connected with the two flight motors II, the output shafts of the two flight motors II are fixedly connected with the flight screw II, the air compressing mechanism is fixedly connected to the flight motor II, and the blocking column is fixedly connected to the interior of the flight motor II.

As a further optimization of the technical scheme, the remote sensing unmanned aerial vehicle structure further comprises a blocking mechanism, wherein the blocking mechanism comprises a telescopic mechanism, a blocking plug and an air vent, the telescopic mechanism is fixedly connected to the impact cavity, the telescopic end of the telescopic mechanism is fixedly connected with the blocking plug, the blocking plug is provided with the air vent, the blocking plug is blocked at the lower end of the impact cavity, and the blocking plug is blocked in the air vent.

The remote sensing unmanned aerial vehicle structure has the beneficial effects that:

according to the remote sensing unmanned aerial vehicle structure, the device can be supported on the ground through the supporting mechanism, the swinging mechanism drives the flight arm to swing in multiple positions, the flight arm drives the flight mechanism to fold and unfold, and then the flight mechanism moves in multiple directions under the driving of the swinging mechanism and the flight arm, so that the position of the flight mechanism can be greatly changed, and meanwhile, the impact mechanism starts the function of auxiliary flight in the take-off and flight processes of the device, so that the device can take-off in an ejection mode, and can be suddenly accelerated in flight.

Drawings

The invention is described in further detail below with reference to the accompanying drawings and specific embodiments.

FIG. 1 is a schematic structural diagram I of the whole structure of the remote sensing unmanned aerial vehicle;

FIG. 2 is a schematic diagram of the overall structure of the remote sensing unmanned aerial vehicle structure of the invention;

FIG. 3 is a schematic view of the flight support structure of the present invention;

FIG. 4 is a schematic structural view of the support mechanism of the present invention;

FIG. 5 is a schematic view of the swing mechanism of the present invention;

FIG. 6 is a schematic view of the flight arm configuration of the present invention;

FIG. 7 is a schematic view of the flight mechanism of the present invention;

FIG. 8 is a schematic view of the impact mechanism of the present invention;

FIG. 9 is a cross-sectional structural schematic view of the impact mechanism of the present invention;

fig. 10 is a schematic view of the blocking mechanism of the present invention.

In the figure: a flight support 1; side brackets 101; a connecting bracket 102; a gap ball cavity 103; the auxiliary wings 104; a support mechanism 2; a support motor 201; a support cylinder 202; a support bracket 203; a support arm 204; a swing mechanism 3; a swing motor I301; a swing bracket 302; a traverse motor 303; a traversing slide block 304; a rotating bracket 305; a slide cylinder 306; a flying arm 4; a sliding post 401; a gap sphere 402; a hinge bracket 403; a folding and unfolding motor I404; a retracting arm 405; a flying mechanism 5; a folding motor II 501; a flying arm 502; a retracting and expanding rotating shaft 503; a flight motor I504; a flight helix I505; an impact mechanism 6; a swing motor II 601; an impingement cavity 602; a flight motor II 603; a flight spiral II 604; a pneumatic mechanism 605; a plugging post 606; a blocking mechanism 7; a telescoping mechanism 701; a plug 702; gas injection holes 703.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings.

In the description of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "top", "bottom", "inner", "outer" and "upright", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, it should be noted that unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, directly or indirectly connected through an intermediate medium, and may be a communication between two members. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In addition, in the description of the present invention, the meaning of "a plurality", and "a plurality" is two or more unless otherwise specified.

The first embodiment is as follows:

the embodiment is described below with reference to fig. 1 to 10, and a remote sensing unmanned aerial vehicle structure includes a flight support 1, two swing mechanisms 3, two flight arms 4 and two flight mechanisms 5, where the two swing mechanisms 3 are provided, the two flight arms 4 are provided, the two flight mechanisms 5 are provided, both the two swing mechanisms 3 are connected to the flight support 1, the two flight arms 4 are respectively connected to the two swing mechanisms 3, and the two flight mechanisms 5 are respectively connected to the two swing mechanisms 3 and the two flight arms 4; can carry out subaerial support to the device through supporting mechanism 2, swing mechanism 3 drive flight arm 4 carries out the swing of multiposition, flight arm 4 drives flight mechanism 5 and takes up and expands, and then flight mechanism 5 carries out diversified motion under the drive of swing mechanism 3 and flight arm 4, change flight mechanism 5's position that can be by a wide margin, simultaneously impact mechanism 6 is at taking off and the flight in-process of device, start the effect of supplementary flight, make the device can launch and take off, and can accelerate suddenly in flight.

The second embodiment is as follows:

the following describes the present embodiment with reference to fig. 1 to 10, and the present embodiment further describes the first embodiment, where the flight support 1 includes two side supports 101, two connecting supports 102, a gap ball cavity 103 and two auxiliary wings 104, the connecting supports 102 are fixedly connected between the middle portions of the two side supports 101, the auxiliary wings 104 are fixedly connected between the rear ends of the two side supports 101, and the gap ball cavity 103 is fixedly connected to the outer sides of the two side supports 101.

The third concrete implementation mode:

the embodiment is described below with reference to fig. 1 to 10, and the embodiment further describes the second embodiment, where the swing mechanism 3 includes a swing motor i 301, a swing bracket 302, a traverse motor 303, a traverse slider 304, a rotating bracket 305, and a sliding cylinder 306, the swing bracket 302 is fixedly connected to an output shaft of the swing motor i 301, the traverse motor 303 is fixedly connected to the swing bracket 302, the traverse slider 304 is connected to an output shaft of the traverse motor 303 through a thread, the traverse slider 304 is slidably connected to the swing bracket 302, the traverse slider 304 is rotatably connected to the rotating bracket 305, the sliding cylinder 306 is fixedly connected to the rotating bracket 305, and the two swing motors i 301 are fixedly connected to the connecting bracket 102; after the device takes off, the swing motor I301 is started, the output shaft of the swing motor I301 drives the swing bracket 302 to rotate, the swing bracket 302 drives the traverse sliding block 304 and the rotating bracket 305 to rotate, the rotating bracket 305 drives the sliding cylinder 306 to rotate, the sliding cylinder 306 drives the sliding column 401 to rotate, a limiting bulge is arranged on the sliding column 401, the limiting bulge is not shown in the figure and mainly limits the rotation of the sliding column 401, so that the sliding column 401 can only slide in the sliding cylinder 306, the sliding cylinder 306 drives the sliding column 401 to rotate, the flying arm 4 deflects, the flying arm 4 drives the flying mechanism 5 to deflect, the traverse motor 303 is started, the output shaft of the traverse motor 303 drives the traverse sliding block 304 to lift through threads, the traverse sliding block 304 drives the rotating bracket 305 to move, the rotating bracket 305 drives the sliding cylinder 306 to move, and the sliding column 401 slides in the sliding cylinder 306, the deflection angle of the flying arm 4 is adjusted, and the swing mechanism 3 can drive the flying arm 4 to deflect in multiple ranges and multiple angles.

The fourth concrete implementation mode:

the following describes the present embodiment with reference to fig. 1 to 10, and the present embodiment further describes the third embodiment, where the flight arm 4 includes a sliding column 401, a gap ball 402, a hinged support 403, a folding and unfolding motor i 404 and a folding and unfolding arm 405, the sliding column 401 is fixedly connected with the gap ball 402, the end of the sliding column 401 is fixedly connected with the hinged support 403, the hinged support 403 is fixedly connected with the folding and unfolding motor i 404, the output shaft of the folding and unfolding motor i 404 is fixedly connected with the folding and unfolding arm 405, the two sliding cylinders 306 are both slidably connected with the sliding column 401, and the two gap balls 402 are respectively in clearance fit in the two gap ball cavities 103.

The fifth concrete implementation mode:

the following describes the present embodiment with reference to fig. 1 to 10, and the present embodiment further describes the fourth embodiment, where the flight mechanism 5 includes a folding and unfolding motor ii 501, a flight arm 502, a folding and unfolding rotating shaft 503, a flight motor i 504 and a flight screw i 505, the folding and unfolding motor ii 501 is in transmission connection with the folding and unfolding rotating shaft 503, the flight arm 502 is fixedly connected to two flight motors i 504, the flight screws i 505 are fixedly connected to output shafts of the two flight motors i 504, the folding and unfolding motor ii 501 is fixedly connected to two hinge supports 403, the output shaft of the folding and unfolding motor ii 501 and the output shaft of the folding and unfolding motor i 404 are coaxially arranged, and the folding and unfolding rotating shaft 503 is rotatably connected to the folding and unfolding arm 405; start the I404 of exhibition of receiving and releasing motor, the output shaft of the I404 of exhibition of receiving and releasing motor drives the arm 405 of receiving and releasing to rotate, the arm 405 of receiving and releasing drives the flight mechanism 5 and moves, and then the state of adjusting the exhibition of receiving and releasing of flight mechanism 5, start the II 501 of exhibition of receiving and releasing motor, the output shaft of the II 501 of exhibition of receiving and releasing motor drives the pivot 503 of receiving and releasing and rotates, the pivot 503 of receiving and releasing drives the flight arm 502 and moves, and then the state of receiving and releasing of further adjustment flight mechanism 5, and then flight mechanism 5 carries out diversified motion under the drive of swing mechanism 3 and flight arm 4, change flight mechanism 5's position by a wide.

The sixth specific implementation mode:

the embodiment is described below with reference to fig. 1 to 10, and the embodiment further describes the fifth embodiment, the remote sensing unmanned aerial vehicle structure further includes a support mechanism 2, the support mechanism 2 includes a support motor 201, support cylinders 202, support brackets 203 and support arms 204, the support motor 201 is fixedly connected to the connecting bracket 102, two support cylinders 202 are provided, the support brackets 203 are fixedly connected to the two support cylinders 202, the support arms 204 are rotatably connected to the front and rear ends of the two support brackets 203, a torsion spring is fixedly connected between the support arm 204 and the support bracket 203, the two support cylinders 202 are in transmission connection with the output shaft of the support motor 201, and the two support cylinders 202 are respectively rotatably connected to the two side brackets 101; when the device is used, the device is not taken off on the ground, the four support arms 204 are contacted with the ground to further support the device, the four flight motors I504 are started, output shafts of the four flight motors I504 drive the corresponding flight screws I505 to rotate, and then the device is driven to take off, when the device is required to be taken off, the flight motor II 603 is started, output shafts of the flight motors II 603 drive the flight screws II 604 to rotate, the flight screws II 604 generate downward driving force when rotating, the four support arms 204 are further extruded, torsion springs between the four support arms 204 and the support bracket 203 are compressed, the four flight motors I504 are slowly started, the four flight screws I505 drive the flight screws I505 to rotate, upward lifting force is generated when the flight screws I505 rotate, and downward force generated by the two flight screws II 604 is greater than that of the flight screws I505, and then the torsion spring is continuously compressed, the flying motor II 603 is suddenly disconnected, a band-type brake is arranged in the preferred flying motor II 603, the flying screw II 604 does not rotate any more, the lifting force generated by the flying motor I504 is enough to drive the device to take off, and meanwhile, the force of the torsion spring is released, so that the device is pushed to take off in an ejection mode.

The seventh embodiment:

the following describes this embodiment with reference to fig. 1 to 10, and this embodiment further describes the sixth embodiment, the remote sensing unmanned aerial vehicle structure further includes an impact mechanism 6, the impact mechanism 6 includes a swing motor ii 601, an impact cavity 602, a flying motor ii 603, a flying screw ii 604, an air compressing mechanism 605 and a blocking column 606, the swing motor ii 601 is fixedly connected to the connecting bracket 102, the impact cavity 602 is rotatably connected between the two side brackets 101, the impact cavity 602 is in transmission connection with an output shaft of the swing motor ii 601, the impact cavity 602 is fixedly connected to the two flying motors ii 603, the output shafts of the two flying motors ii 603 are fixedly connected to the flying screw ii 604, the flying motor ii 603 is fixedly connected to the air compressing mechanism 605, and the inside of the flying motor ii 603 is fixedly connected to the blocking column 606.

The specific implementation mode is eight:

the embodiment is described below with reference to fig. 1 to 10, and the seventh embodiment is further described in the embodiment, the remote sensing unmanned aerial vehicle structure further includes a blocking mechanism 7, the blocking mechanism 7 includes a telescoping mechanism 701, a blocking plug 702 and a gas orifice 703, the telescoping mechanism 701 is fixedly connected to the impact cavity 602, the blocking plug 702 is fixedly connected to the telescoping end of the telescoping mechanism 701, the gas orifice 703 is arranged on the blocking plug 702, the blocking plug 702 is blocked at the lower end of the impact cavity 602, and the blocking column 606 is blocked in the gas orifice 703; the air compressing mechanism 605 can be started in the flying and taking-off processes of the device, the air compressing mechanism 605 can be an air pump or other mechanical structures capable of compressing air in a reciprocating mode, the air compressing mechanism 605 mainly has the function that air on the outer side is sucked into the impact cavity 602, the air in the impact cavity 602 is compressed, when sudden acceleration is needed in the taking-off or flying process of the device, the telescopic mechanism 701 is started, the telescopic mechanism 701 can be a hydraulic cylinder or an electric push rod, the telescopic end of the telescopic mechanism 701 drives the blocking plug 702 to move downwards, the blocking plug 702 does not block the lower end of the impact cavity 602, meanwhile, the blocking column 606 exits from the gas jet hole 703, the air in the impact cavity 602 is rapidly discharged to provide impact force in one direction of the device, the technical problem that the helicopter cannot perform rapid impact turning is solved, the swing motor 601 is started, the output shaft of the swing motor II 601 drives the impact cavity 602 to swing, so that the direction of gas injection is adjusted, and different use requirements are met.

The invention relates to a remote sensing unmanned aerial vehicle structure, which has the working principle that:

when the device is used, the device is not taken off on the ground, the four support arms 204 are contacted with the ground to further support the device, the four flight motors I504 are started, output shafts of the four flight motors I504 drive the corresponding flight screws I505 to rotate, and then the device is driven to take off, when the device is required to be taken off, the flight motor II 603 is started, output shafts of the flight motors II 603 drive the flight screws II 604 to rotate, the flight screws II 604 generate downward driving force when rotating, the four support arms 204 are further extruded, torsion springs between the four support arms 204 and the support bracket 203 are compressed, the four flight motors I504 are slowly started, the four flight screws I505 drive the flight screws I505 to rotate, upward lifting force is generated when the flight screws I505 rotate, and downward force generated by the two flight screws II 604 is greater than that of the flight screws I505, then the torsion spring is continuously compressed, the flying motor II 603 is suddenly disconnected, a band-type brake is preferably arranged in the flying motor II 603, the flying screw II 604 does not rotate any more, the lifting force generated by the flying motor I504 is enough to drive the device to take off, and meanwhile, the force of the torsion spring is released, so that the device is pushed to take off in an ejection manner; after the device takes off, the swing motor I301 is started, the output shaft of the swing motor I301 drives the swing bracket 302 to rotate, the swing bracket 302 drives the traverse sliding block 304 and the rotating bracket 305 to rotate, the rotating bracket 305 drives the sliding cylinder 306 to rotate, the sliding cylinder 306 drives the sliding column 401 to rotate, a limiting bulge is arranged on the sliding column 401, the limiting bulge is not shown in the figure and mainly limits the rotation of the sliding column 401, so that the sliding column 401 can only slide in the sliding cylinder 306, the sliding cylinder 306 drives the sliding column 401 to rotate, the flying arm 4 deflects, the flying arm 4 drives the flying mechanism 5 to deflect, the traverse motor 303 is started, the output shaft of the traverse motor 303 drives the traverse sliding block 304 to lift through threads, the traverse sliding block 304 drives the rotating bracket 305 to move, the rotating bracket 305 drives the sliding cylinder 306 to move, and the sliding column 401 slides in the sliding cylinder 306, the deflection angle of the flying arm 4 is adjusted, and the swing mechanism 3 can drive the flying arm 4 to deflect in multiple ranges and multiple angles; starting a folding and unfolding motor I404, wherein an output shaft of the folding and unfolding motor I404 drives a folding and unfolding arm 405 to rotate, the folding and unfolding arm 405 drives a flight mechanism 5 to move so as to adjust the folding and unfolding state of the flight mechanism 5, starting a folding and unfolding motor II 501, an output shaft of the folding and unfolding motor II 501 drives a folding and unfolding rotating shaft 503 to rotate, the folding and unfolding rotating shaft 503 drives the flight arm 502 to move so as to further adjust the folding and unfolding state of the flight mechanism 5, and the flight mechanism 5 is driven by a swinging mechanism 3 and a flight arm 4 to move in multiple directions, so that the position of the flight mechanism 5 can be greatly changed; the air compressing mechanism 605 can be started in the flying and taking-off processes of the device, the air compressing mechanism 605 can be an air pump or other mechanical structures capable of compressing air in a reciprocating mode, the air compressing mechanism 605 mainly has the function that air on the outer side is sucked into the impact cavity 602, the air in the impact cavity 602 is compressed, when sudden acceleration is needed in the taking-off or flying process of the device, the telescopic mechanism 701 is started, the telescopic mechanism 701 can be a hydraulic cylinder or an electric push rod, the telescopic end of the telescopic mechanism 701 drives the blocking plug 702 to move downwards, the blocking plug 702 does not block the lower end of the impact cavity 602, meanwhile, the blocking column 606 exits from the gas jet hole 703, the air in the impact cavity 602 is rapidly discharged to provide impact force in one direction of the device, the technical problem that the helicopter cannot perform rapid impact turning is solved, the swing motor 601 is started, the output shaft of the swing motor II 601 drives the impact cavity 602 to swing, so that the direction of gas injection is adjusted, and different use requirements are met.

It is to be understood that the above description is not intended to limit the present invention, and the present invention is not limited to the above examples, and that various changes, modifications, additions and substitutions which are within the spirit and scope of the present invention and which may be made by those skilled in the art are also within the scope of the present invention.