CN117799886A - Building design survey aircraft and application method thereof - Google Patents
Building design survey aircraft and application method thereof Download PDFInfo
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- CN117799886A CN117799886A CN202410232027.7A CN202410232027A CN117799886A CN 117799886 A CN117799886 A CN 117799886A CN 202410232027 A CN202410232027 A CN 202410232027A CN 117799886 A CN117799886 A CN 117799886A
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- inner cavity
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- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000004140 cleaning Methods 0.000 claims abstract description 41
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 85
- 230000000903 blocking effect Effects 0.000 claims description 12
- 238000002347 injection Methods 0.000 claims description 12
- 239000007924 injection Substances 0.000 claims description 12
- 238000009434 installation Methods 0.000 claims description 5
- 238000010248 power generation Methods 0.000 claims description 5
- 238000013016 damping Methods 0.000 description 12
- 230000009286 beneficial effect Effects 0.000 description 9
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 8
- 235000017491 Bambusa tulda Nutrition 0.000 description 8
- 241001330002 Bambuseae Species 0.000 description 8
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 8
- 239000011425 bamboo Substances 0.000 description 8
- 239000000428 dust Substances 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000009736 wetting Methods 0.000 description 1
Abstract
The invention belongs to the technical field of aircrafts and discloses a building design survey aircraft and a use method thereof, wherein the building design survey aircraft comprises an aircraft body, a piston cylinder I is fixedly connected to an inner cavity of the aircraft body, a return spring is fixedly connected to an inner cavity of the piston cylinder I, a piston rod I is fixedly connected to one side of the return spring, which is close to the center of the aircraft body, a movable rod is fixedly connected to one side of the piston rod I, which is far away from the piston cylinder I, a rack is fixedly connected to one side of the movable rod, which is close to the center of the aircraft body, gears are fixedly connected to the left side and the right side of the inner cavity of the aircraft body, ball screws are fixedly connected to the bottom ends of the gears, cleaning components are meshed on the surfaces of the ball screws, and guide rods are movably sleeved in the inner cavity of the cleaning components. After the aircraft surveys a distance, the surveying equipment can be automatically cleaned after a flat ground falls, so that the aircraft does not return to the departure place, and the surveying efficiency is greatly improved.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a building design survey aircraft and a use method thereof.
Background
In building design, the geological and geographical environment features of the construction site need to be surveyed, and because the construction site of the building is relatively large, if the construction site of the building is surveyed in a manual mode, the aircraft is used, the site to be surveyed is surveyed, in order to ensure the accuracy of building design survey, the aircraft is often not at too high a height to be surveyed, and therefore, when the aircraft surveys on places with relatively large dust, such as the side of a building site with less smoke or a building such as a mine site, dust of the aircraft is attached to the surface of surveying equipment on the aircraft, so that the surface of the surveying equipment of the aircraft is generally wiped when the aircraft returns, and when the building is surveyed, the place needed to be surveyed is relatively long, the efficiency of the survey is influenced if the aircraft returns to be cleaned, and the normal use of the surveying equipment is influenced if the surface of the surveying equipment is not cleaned.
Disclosure of Invention
The present invention is directed to a survey aircraft for architectural design and a method of using the same, which solves the problems set forth in the background art.
In order to achieve the above object, the present invention provides the following technical solutions: the utility model provides a building design surveys aircraft, includes the aircraft body, the inner chamber fixedly connected with piston section of thick bamboo of aircraft body first, the inner chamber fixedly connected with reset spring of piston section of thick bamboo first, one side fixedly connected with piston rod first near aircraft body center department of reset spring, one side fixedly connected with movable rod of piston rod first keeps away from the piston section of thick bamboo first, one side fixedly connected with rack that the movable rod is close to aircraft body center department, the equal fixedly connected with gear in the left and right sides of aircraft body inner chamber, the bottom fixedly connected with ball of gear, ball's surface engagement has cleaning assembly, the guide bar has been cup jointed in cleaning assembly's inner chamber activity, the inner chamber fixedly connected with water tank of aircraft body, the bottom fixedly connected with control tube of water tank, control tube rear side fixedly connected with installation tube, the inner chamber fixedly connected with spring that opens and shuts, one side fixedly connected with breakwater of installation tube is kept away from to the spring, one side fixedly connected with drain pipe of control tube is kept away from to the drain pipe.
Preferably, the number of the moving rods is two, the two moving rods are respectively positioned at the front side and the rear side of the inner cavity of the aircraft body, the right side of the moving rod positioned at the front side is fixedly connected with an pushing plate, and the bottom end of the pushing plate is conical.
Preferably, one side of the movable rod, which is close to the center of the inner cavity of the aircraft body, is fixedly connected with a solar panel, support rods are fixedly installed on the front side and the rear side of the aircraft body, a sliding groove is formed in one side, which is far away from the movable rod, of the solar panel, and the solar panel is in sliding connection with the support rods through the sliding groove.
Preferably, the mounting plate is all fixedly installed to the left and right sides of aircraft body, the bottom fixed mounting of mounting plate is connected with piston section of thick bamboo two, piston section of thick bamboo two is four altogether the bottom of the equal fixed mounting of piston section of thick bamboo two at the mounting plate, the inner chamber fixedly connected with bradyseism spring of piston section of thick bamboo two, bradyseism spring's bottom fixedly connected with piston rod two, the bottom fixedly connected with supporting legs of piston rod two, the top fixedly connected with connecting pipe of piston section of thick bamboo two is first, the top fixedly connected with of connecting pipe is blocked up the pipe, the top fixedly connected with connecting pipe of blocking up the pipe is second.
Preferably, survey equipment is arranged at the bottom end of the aircraft body, a propeller is arranged at the top end of the aircraft body, and storage holes are formed in the left side and the right side of the aircraft body.
Preferably, the cleaning component consists of four cleaning rods and four connecting rings, the four connecting rings are respectively meshed with the surface of the ball screw and movably sleeved on the surface of the guide rod, and the bottom end of the guide rod is fixedly provided with a disc.
Preferably, the front side fixedly connected with water injection pipe of water tank, the water injection pipe is L pipe, the water injection pipe link up with the inner chamber of water tank.
Preferably, one side of the water baffle, which is close to the push-away plate, is a conical plate, a round hole is formed in the front end of the water baffle, and a nozzle is arranged at the bottom end of the water outlet pipe.
The invention also provides a use method of the building design survey aircraft, which comprises the following steps:
the aircraft body drives take-off by starting the propeller, surveys by surveying equipment, when the aircraft body falls, the supporting feet are in contact with the ground, and the piston cylinder II is pressed down by the weight of all parts, so that the piston rod II is driven to extrude air in the inner cavity of the piston cylinder II, the air in the inner cavity of the piston cylinder II is slowly injected into the inner cavity of the piston cylinder I through the connecting pipe I, the connecting pipe II and the blocking pipe, and the piston rod in the inner cavity of the piston cylinder I is driven to move outwards of the aircraft body;
firstly, driving the push plate to move, extruding the water baffle through the push plate, so that the water baffle moves towards the direction of the installation pipe, enabling the round hole of the water baffle to move to the middle part of the control pipe, discharging water in the inner cavity of the water tank from the control pipe to the inner cavity of the drain pipe, discharging the water to the surface of the cleaning component through the water outlet pipe, wetting the cleaning component, driving the gear to rotate when the rack is contacted with the gear, driving the ball screw to rotate through the rotation of the gear, and enabling the cleaning component to move downwards along the axial direction of the ball screw and the guide rod, so that the surface of the surveying equipment is cleaned through the cleaning component;
when the first piston rod moves, the moving rod is driven to move, so that the solar panel is driven to move out of the inner cavity of the aircraft body from the storage hole, and solar power generation is performed;
when the aircraft body lands, the piston rod II is subjected to damping through the tension of the damping spring and the air in the inner cavity of the piston cylinder II, and the aircraft body lands slowly, and when the aircraft body takes off, the piston rod II is driven to reset through the tension of the damping spring, so that the first gear shifting piston rod is reset, and the solar panel is stored in the inner cavity of the aircraft body.
The beneficial effects of the invention are as follows:
1. when the aircraft body falls to the ground, air in the inner cavity of the piston cylinder II is extruded by the piston rod II to slowly extrude into the inner cavity of the piston cylinder I from the connecting pipe I and the connecting pipe II and the blocking pipe, so that the piston rod I in the inner cavity of the piston cylinder I is driven to move, the push-away plate is firstly driven to push away the water baffle plate, water in the inner cavity of the water tank is discharged from the control pipe to the inner cavity of the drain pipe, and then the water is discharged to the top end of the cleaning assembly through the water outlet pipe, so that the cleaning assembly is wetted, after the moving rod moves to a certain distance, the push-away plate is separated from the water baffle plate, the rack is contacted with the gear, so that the ball screw is driven to rotate, and the cleaning assembly moves downwards, so that dust on the surface of the surveying equipment is cleaned, and after the aircraft falls to a certain distance again, the surveying equipment can be cleaned automatically after the aircraft falls to a flat ground, so that the efficiency of surveying is greatly improved.
2. According to the invention, when the aircraft body falls, the supporting legs are contacted with the ground, and the weight of the aircraft body and all parts drives the piston cylinder II to be pressed down, so that the piston rod II moves in the inner cavity of the cushioning spring, the piston cylinder II is driven to slowly squeeze air into the inner cavity of the piston cylinder I from the connecting pipe I, the connecting pipe II and the blocking pipe, so that the piston rod I is driven to move, and the two solar panels are pushed out of the inner cavity of the aircraft body from the containing holes, so that the solar panels work, the solar panels are automatically unfolded when the aircraft body falls, solar power generation is performed, and the solar panels are automatically contained when the aircraft falls off.
3. According to the invention, when the aircraft body descends, the tension of the damping spring and the blocking pipe block the air in the second inner cavity of the piston cylinder, so that the pressure in the second inner cavity of the piston cylinder is increased, the aircraft body slowly descends, and the situation that the aircraft body is in hard contact with the ground due to large weight of the aircraft body when the aircraft body descends, so that the components in the aircraft body are vibrated and damaged for a long time is avoided.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view of a shock absorbing spring connection according to the present invention;
FIG. 3 is an enlarged schematic view of the invention at A in FIG. 2;
FIG. 4 is a schematic diagram of the connection of the water tank of the present invention;
FIG. 5 is a schematic view of the connection of the water baffle plate according to the present invention;
fig. 6 is a schematic view showing the connection of the drain pipe according to the structure of the present invention.
In the figure: 1. an aircraft body; 2. a first piston cylinder; 3. a return spring; 4. a first piston rod; 5. a moving rod; 6. a rack; 7. a gear; 8. a ball screw; 9. a cleaning assembly; 10. a guide rod; 11. a water tank; 12. a control tube; 13. installing a pipe; 14. an opening and closing spring; 15. a water baffle; 16. pushing away the plate; 17. a drain pipe; 18. a water outlet pipe; 19. a solar panel; 20. a support rod; 21. a chute; 22. a water injection pipe; 23. a mounting plate; 24. a piston cylinder II; 25. a damping spring; 26. a piston rod II; 27. supporting feet; 28. a first connecting pipe; 29. blocking the tube; 30. a second connecting pipe; 31. a survey apparatus; 32. a propeller; 33. and a storage hole.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1 to 6, the embodiment of the invention provides a building design survey aircraft and a use method thereof, the building design survey aircraft comprises an aircraft body 1, wherein an inner cavity of the aircraft body 1 is fixedly connected with a piston cylinder one 2, an inner cavity of the piston cylinder one 2 is fixedly connected with a return spring 3, one side of the return spring 3, which is close to the center of the aircraft body 1, is fixedly connected with a piston rod one 4, one side of the piston rod one 4, which is far away from the piston cylinder one 2, is fixedly connected with a movable rod 5, one side of the movable rod 5, which is close to the center of the aircraft body 1, is fixedly connected with a rack 6, both the left side and the right side of the inner cavity of the aircraft body 1 are fixedly connected with gears 7, the bottom end of the gears 7 is fixedly connected with a ball screw 8, the surface of the ball screw 8 is meshed with a cleaning assembly 9, the inner cavity of the cleaning assembly 9 is movably sleeved with a guide rod 10, the inner cavity of the aircraft body 1 is fixedly connected with a water tank 11, the bottom end of the water tank 11 is fixedly connected with a control pipe 12, the rear side of the control pipe 12 is fixedly connected with a mounting pipe 13, the inner cavity of the mounting pipe 13 is fixedly connected with an opening and closing spring 14, one side of the piston rod 4, one side of the piston rod 14 is far away from the piston rod 2 is fixedly connected with a water baffle 15, one side of the opening and closing spring 12 is far from the mounting pipe 12 is fixedly connected with a water outlet pipe 17, which is far from the bottom end of the water outlet pipe is fixedly connected with a water outlet pipe 18;
the working principle and beneficial effects of the technical scheme are as follows: when the aircraft body 1 falls to the ground, air in the inner cavity of the piston cylinder II 24 is extruded through the piston rod II 26 to be slowly extruded into the inner cavity of the piston cylinder I2 from the connecting pipe I28, the connecting pipe II 30 and the blocking pipe 29, so that the piston rod I4 in the inner cavity of the piston cylinder I2 is driven to move, firstly, the push-away plate 16 is driven to push away the water baffle 15, so that water in the inner cavity of the water tank 11 is discharged from the control pipe 12 to the inner cavity of the drain pipe 17, and then is discharged to the top end of the cleaning assembly 9 through the water outlet pipe 18, so that the cleaning assembly 9 is wetted, after the moving rod 5 moves to a certain distance, the push-away plate 16 is separated from the water baffle 15, the rack 6 is contacted with the gear 7, so that the ball screw 8 is driven to rotate, so that the cleaning assembly 9 is driven to move downwards, dust on the surface of the surveying equipment 31 is cleaned, and after the aircraft is surveyed for a certain distance again, the surveying equipment 31 can be automatically cleaned after a flat ground fall, so that the efficiency of surveying is greatly improved.
As shown in fig. 2, in one embodiment, two moving rods 5 are provided, the two moving rods 5 are respectively located at the front side and the rear side of the inner cavity of the aircraft body 1, the pushing plate 16 is fixedly connected to the right side of the moving rod 5 located at the front side, and the bottom end of the pushing plate 16 is conical;
the working principle and beneficial effects of the technical scheme are as follows: through the setting of two movable rods 5 for when two movable rods 5 remove, can drive two sun panels 19 to the left and right sides of aircraft body 1 and remove the expansion, the push-open plate 16 of rethread movable rod 5 bottom, when aircraft body 1 lands, push-open plate 16 first contacts with water baffle 15, and the water baffle 15 is jacked up for after the water is discharged to the top of clean subassembly 9 from outlet pipe 18, make clean subassembly 9 go on going up and down again and clear up survey equipment 31.
As shown in fig. 2, in one embodiment, a solar panel 19 is fixedly connected to one side of the movable rod 5, which is close to the center of the inner cavity of the aircraft body 1, support rods 20 are fixedly installed on the front side and the rear side of the aircraft body 1, a sliding groove 21 is formed in one side of the solar panel 19, which is far away from the movable rod 5, and the solar panel 19 is in sliding connection with the support rods 20 through the sliding groove 21;
the working principle and beneficial effects of the technical scheme are as follows: when the aircraft body 1 falls, the supporting feet 27 are contacted with the ground, the weight of the aircraft body 1 and all components is used for driving the piston cylinder II 24 to be pressed down, so that the piston rod II 26 moves in the inner cavity of the cushioning spring 25, the piston cylinder II 24 is driven to slowly squeeze air into the inner cavity of the piston cylinder I2 from the connecting pipe I28, the connecting pipe II 30 and the blocking pipe 29, the piston rod I4 is driven to move, the two solar panels 19 are pushed out of the inner cavity of the aircraft body 1 from the containing holes 33, the solar panels 19 are enabled to work, the solar panels 19 are automatically unfolded when the aircraft body 1 falls, solar power generation is performed, the solar panels 19 are automatically contained when the aircraft body 1 takes off, and the solar panels 19 are electrically connected with electric elements for storing electric energy inside the aircraft body 1.
As shown in fig. 2, in one embodiment, mounting plates 23 are fixedly mounted on the left and right sides of the aircraft body 1, piston cylinders two 24 are fixedly mounted and connected to the bottom ends of the mounting plates 23, four piston cylinders two 24 are provided, the four piston cylinders two 24 are fixedly mounted at the bottom ends of the mounting plates 23, an inner cavity of the piston cylinders two 24 is fixedly connected with a damping spring 25, the bottom ends of the damping spring 25 are fixedly connected with piston rods two 26, the bottom ends of the piston rods two 26 are fixedly connected with supporting legs 27, the top ends of the piston cylinders two 24 are fixedly connected with connecting pipes one 28, the top ends of the connecting pipes one 28 are fixedly connected with a blocking pipe 29, and the top ends of the blocking pipes 29 are fixedly connected with connecting pipes two 30;
the working principle and beneficial effects of the technical scheme are as follows: the two piston barrels II 24 are installed through the installation plate 23 at the top, the piston rods II 26 are supported through the tension of the damping springs 25, so that when the aircraft body 1 falls, the aircraft body 1 can slowly fall through the air in the inner cavities of the piston barrels II 24 and the tension of the damping springs 25, the aircraft body 1 can flexibly land, and through the arrangement of the four piston barrels II 24, the aircraft body 1 can drive the four piston rods II 26 to move in the inner cavities of the piston barrels II 24 during falling, and therefore all the air in the inner cavities of the four piston barrels II 24 is extruded into the inner cavities of the two piston barrels I2, the piston rods I4 in the inner cavities of the piston barrels I2 can stably move, and the two solar panels 19 can be driven to the maximum range, so that enough power is provided for realizing the subsequent functions, and the complete realization of the subsequent functions is ensured.
As shown in fig. 2, in one embodiment, a surveying device 31 is disposed at the bottom end of the aircraft body 1, a propeller 32 is disposed at the top end of the aircraft body 1, and receiving holes 33 are formed on both left and right sides of the aircraft body 1;
the working principle and beneficial effects of the technical scheme are as follows: the survey equipment 31 at the bottom end of the aircraft body 1 carries out architectural design survey, and then the aircraft is driven to fly by the propeller 32 at the top end of the aircraft body 1.
As shown in fig. 4, in one embodiment, the cleaning assembly 9 is composed of four cleaning rods and four connecting rings, the four connecting rings are respectively meshed with the surface of the ball screw 8 and movably sleeved on the surface of the guide rod 10, and a disc is fixedly arranged at the bottom end of the guide rod 10;
the working principle and beneficial effects of the technical scheme are as follows: the cleaning assembly 9 is composed of four cleaning rods, so that the surfaces of the surveying equipment 31 can be cleaned in the descending process of the four cleaning rods, the surfaces of the four cleaning rods are respectively meshed with the ball screw 8 through the connecting rings and movably sleeved on the surfaces of the guide rods 10, the cleaning assembly 9 can be driven to move through rotation of the ball screw 8, and the cleaning assembly 9 is positioned and guided through the guide rods 10.
As shown in fig. 2, in one embodiment, a water injection pipe 22 is fixedly connected to the front side of the water tank 11, the water injection pipe 22 is an L-shaped circular pipe, and the water injection pipe 22 is communicated with the inner cavity of the water tank 11;
the working principle and beneficial effects of the technical scheme are as follows: the water injection pipe 22 on the front side of the water tank 11 is filled with water from the water tank 11 to the inner cavity of the water injection pipe 22 after the survey is completed.
As shown in fig. 5, in one embodiment, a conical plate is arranged on one side of the water baffle 15, which is close to the push-away plate 16, a round hole is formed in the front end of the water baffle 15, and a nozzle is arranged at the bottom end of the water outlet pipe 18;
the working principle and beneficial effects of the technical scheme are as follows: the side of the water deflector 15, which is close to the push-away plate 16, is a conical plate, so that the push-away plate 16 can move against the water deflector 15 when moving towards the outside of the aircraft body 1 or towards the inside of the aircraft body 1, so that the cleaning assembly 9 is wetted by water or the cleaning assembly 9 is cleaned.
As shown in fig. 2, in one embodiment, there is also provided a method of using the above-described architectural design survey aircraft, comprising the steps of:
the aircraft body 1 drives take-off by starting the propeller 32 and surveys by the surveying equipment 31, when the aircraft body 1 falls, the supporting feet 27 are in contact with the ground, the piston cylinder II 24 is pressed down by the weight of all components, so that the piston rod II 26 is driven to extrude air in the inner cavity of the piston cylinder II 24, the air in the inner cavity of the piston cylinder II 24 is slowly injected into the inner cavity of the piston cylinder I2 through the connecting pipe I28, the connecting pipe II 30 and the blocking pipe 29, and the piston rod I4 in the inner cavity of the piston cylinder I2 is driven to move to the outer side of the aircraft body 1;
firstly, the push plate 16 is driven to move, the push plate 16 is used for extruding the water baffle 15, so that the water baffle 15 moves towards the direction of the mounting pipe 13, the round hole of the water baffle 15 is shifted to the middle of the control pipe 12, water in the inner cavity of the water tank 11 is discharged from the control pipe 12 to the inner cavity of the drain pipe 17, then the water is discharged to the surface of the cleaning assembly 9 through the water outlet pipe 18, the cleaning assembly 9 is wetted, when the rack 6 is contacted with the gear 7, the gear 7 is driven to rotate, the ball screw 8 is driven to rotate through the rotation of the gear 7, the cleaning assembly 9 moves downwards along the axial directions of the ball screw 8 and the guide rod 10, and the surface of the surveying equipment 31 is cleaned through the cleaning assembly 9;
when the first piston rod 4 moves, the moving rod 5 is driven to move, so that the solar panel 19 is driven to move out of the inner cavity of the aircraft body 1 from the containing hole 33, and solar power generation is performed;
when the aircraft body 1 falls, the piston rod II 26 is subjected to damping through the tension of the damping spring 25 and the air in the inner cavity of the piston cylinder II 24, and the aircraft body 1 slowly falls, and when the aircraft body 1 takes off, the piston rod II 26 is driven to reset through the tension of the damping spring 25, so that the gear shifting piston rod I4 is reset, and the solar panel 19 is stored in the inner cavity of the aircraft body 1.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (9)
1. A building design survey aircraft comprising an aircraft body (1), characterized in that: the utility model discloses a water-retaining device for the aircraft, which comprises an aircraft body (1), an inner cavity fixedly connected with piston tube I (2) of aircraft body (1), an inner cavity fixedly connected with reset spring (3) of piston tube I (2), one side fixedly connected with piston rod I (4) near aircraft body (1) center department of reset spring (3), one side fixedly connected with movable rod (5) of piston tube I (2) is kept away from to piston rod I (4), one side fixedly connected with rack (6) near aircraft body (1) center department of movable rod (5), the left and right sides of aircraft body (1) inner cavity all fixedly connected with gear (7), the bottom fixedly connected with ball screw (8) of gear (7), the surface engagement of ball screw (8) has cleaning subassembly (9), the inner cavity swing joint of cleaning subassembly (9) has guide bar (10), the inner cavity fixedly connected with water tank (11) of aircraft body (1), the bottom fixedly connected with control tube (12) of water tank (11), one side fixedly connected with installation tube (13) near aircraft body (1) center is connected with rack (6), spring (14) fixedly connected with water retaining plate (14), the bottom end of the control pipe (12) is fixedly connected with a drain pipe (17), and one side, away from the control pipe (12), of the drain pipe (17) is fixedly connected with a water outlet pipe (18).
2. The architectural design survey aircraft of claim 1, wherein: the number of the moving rods (5) is two, the two moving rods (5) are respectively positioned at the front side and the rear side of the inner cavity of the aircraft body (1), the right side of the moving rod (5) positioned at the front side is fixedly connected with an pushing plate (16), and the bottom end of the pushing plate (16) is conical.
3. The architectural design survey aircraft of claim 2, wherein: one side that movable rod (5) is close to aircraft body (1) inner chamber center department fixedly connected with solar panel (19), both sides all fixed mounting have bracing piece (20) around aircraft body (1), spout (21) have been seted up to one side that movable rod (5) was kept away from to solar panel (19), solar panel (19) pass through spout (21) and bracing piece (20) sliding connection.
4. A architectural design survey aircraft according to claim 3, wherein: the utility model discloses a novel aircraft, including aircraft body (1), piston tube (24) are two in total, four in the bottom fixed mounting of mounting panel (1), the inner chamber fixedly connected with bradyseism spring (25) of piston tube (24), the bottom fixedly connected with piston rod (26) of bradyseism spring (25), the bottom fixedly connected with supporting legs (27) of piston rod (26), the top fixedly connected with connecting pipe (28) of piston tube (24), the top fixedly connected with stopper pipe (29) of connecting pipe (28), the top fixedly connected with connecting pipe (30) of stopper pipe (29).
5. The architectural design survey aircraft of claim 4, wherein: the bottom of aircraft body (1) is provided with surveys equipment (31), the top of aircraft body (1) is provided with screw (32), accomodate hole (33) have all been seted up to the left and right sides of aircraft body (1).
6. The architectural design survey aircraft of claim 5, wherein: the cleaning assembly (9) consists of four cleaning rods and four connecting rings, the four connecting rings are respectively meshed with the surface of the ball screw (8) and movably sleeved on the surface of the guide rod (10), and a disc is fixedly arranged at the bottom end of the guide rod (10).
7. The architectural design survey aircraft of claim 6, wherein: the front side of the water tank (11) is fixedly connected with a water injection pipe (22), the water injection pipe (22) is an L-shaped circular pipe, and the water injection pipe (22) is communicated with the inner cavity of the water tank (11).
8. The architectural design survey aircraft of claim 7, wherein: one side of the water baffle (15) close to the push-away plate (16) is a conical plate, a round hole is formed in the front end of the water baffle (15), and a nozzle is arranged at the bottom end of the water outlet pipe (18).
9. A method of using the architectural design survey aircraft of claim 8, wherein: the method comprises the following steps:
the aircraft body (1) drives take-off by starting the propeller (32) and surveys by the surveying equipment (31), when the aircraft body (1) falls, the supporting feet (27) are in contact with the ground, the piston cylinder II (24) is pressed down by the weight of all components, so that the piston rod II (26) is driven to extrude air in the inner cavity of the piston cylinder II (24), the air in the inner cavity of the piston cylinder II (24) is slowly injected into the inner cavity of the piston cylinder I (2) through the connecting pipe I (28) and the connecting pipe II (30) and the blocking pipe (29), and the piston rod I (4) in the inner cavity of the piston cylinder I (2) is driven to move to the outer side of the aircraft body (1);
firstly, the push plate (16) is driven to move, the push plate (16) is used for extruding the water baffle (15), so that the water baffle (15) is driven to rotate towards the direction of the mounting pipe (13), the round hole of the water baffle (15) is shifted to the middle of the control pipe (12), water in the inner cavity of the water tank (11) is discharged from the control pipe (12) to the inner cavity of the drain pipe (17), then the water is discharged to the surface of the cleaning assembly (9) through the water outlet pipe (18), the cleaning assembly (9) is wetted, when the rack (6) is contacted with the gear (7), the gear (7) is driven to rotate, the ball screw (8) is driven to rotate through the rotation of the gear (7), and the cleaning assembly (9) is driven to move downwards along the axial directions of the ball screw (8) and the guide rod (10), and therefore the surface of the survey equipment (31) is cleaned through the cleaning assembly (9).
When the first piston rod (4) moves, the moving rod (5) is driven to move, so that the solar panel (19) is driven to move out of the inner cavity of the aircraft body (1) from the containing hole (33), and solar power generation is performed;
when the aircraft body (1) descends, the piston rod II (26) is subjected to bradyseism through the tension of the bradyseism spring (25) and the air in the inner cavity of the piston cylinder II (24), and the aircraft body (1) slowly descends, when the aircraft body (1) takes off, the piston rod II (26) is driven to reset through the tension of the bradyseism spring (25), and accordingly the gear shifting piston rod I (4) is reset, and the solar panel (19) is accommodated in the inner cavity of the aircraft body (1).
Priority Applications (1)
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