CN113148213B - Unmanned aerial vehicle catapult point structure - Google Patents
Unmanned aerial vehicle catapult point structure Download PDFInfo
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- CN113148213B CN113148213B CN202110474700.4A CN202110474700A CN113148213B CN 113148213 B CN113148213 B CN 113148213B CN 202110474700 A CN202110474700 A CN 202110474700A CN 113148213 B CN113148213 B CN 113148213B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention provides an unmanned aerial vehicle ejection point structure, and belongs to the technical field of unmanned aerial vehicles. The problem that the existing catapulting unmanned aerial vehicle is insufficient in take-off stability is solved. The unmanned aerial vehicle comprises a machine body, wherein the ejection point structure comprises an adjusting piece and an ejection body positioned in the machine body, the ejection body is arranged along the front-back direction of the machine body, the rear end of the ejection body is hinged with the machine body, the rear end of the ejection body is fixedly connected with a striking table and the striking table is positioned outside the machine body, the inner end of the adjusting piece penetrates through the machine body and is connected with the front end of the ejection body, and the adjusting piece can drive the ejection body to rotate around a hinge point so that the central axis of the ejection body passes through the center of gravity of the unmanned aerial vehicle. The unmanned aerial vehicle catapulting point structure has the advantages that the rocket thrust line is aligned with the gravity center of the unmanned aerial vehicle when the unmanned aerial vehicle catapulting and takes off, and the unmanned aerial vehicle body is not easy to damage.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and relates to an unmanned aerial vehicle ejection point structure.
Background
In recent years, the development speed of the fixed wing unmanned aerial vehicle is faster, various unmanned aerial vehicles appear, and the fixed wing unmanned aerial vehicle plays an increasingly important role in aerial photography, agricultural plant protection, logistics transportation, disaster rescue, measurement and control, infectious disease monitoring and electric power inspection. The unmanned aerial vehicle has a plurality of take-off modes, and one special type of the unmanned aerial vehicle for catapulting take-off has the characteristics of convenient transmission, no landing gear, light structure weight and wide application.
In the manufacturing process of the catapulting unmanned aerial vehicle system, due to manufacturing tolerance and assembly errors, the weight of parts and the design value are deviated, and the gravity center of the unmanned aerial vehicle can be changed within a certain range. This will cause when launching unmanned aerial vehicle, the thrust line when rocket launches has the problem of misalignment with unmanned aerial vehicle's focus, and unmanned aerial vehicle launches the back and has actions such as roll, low head and new line, can't ensure unmanned aerial vehicle initial flight's stability, leads to unmanned aerial vehicle ejection to launch the problem that has the failure.
Meanwhile, for the catapulting unmanned aerial vehicle, as the catapulting and taking-off of the unmanned aerial vehicle adopts a rocket catapulting mode, the initial flight of the unmanned aerial vehicle is accelerated by the catapulting force of the rocket, the whole weight which is several times of the weight of the unmanned aerial vehicle is completely applied to a catapulting point structure, the initial overload is large, the rocket is in contact with the unmanned aerial vehicle to be in local point contact, the local stress is large, and the damage to the unmanned aerial vehicle body is easily caused.
Disclosure of Invention
The invention aims at solving the problems in the prior art, and provides an unmanned aerial vehicle catapulting point structure, which aims at the gravity center of an unmanned aerial vehicle when the unmanned aerial vehicle catapulting and takes off, and the body is not easy to damage.
The aim of the invention can be achieved by the following technical scheme: the utility model provides an unmanned aerial vehicle catapult point structure, unmanned aerial vehicle includes the organism, catapult point structure includes the regulating part and is arranged in the catapult body of organism, the catapult body sets up along the fore-and-aft direction of organism, the rear end of catapulting body articulates with the organism mutually, the rear end of catapulting body has linked firmly and has hit the platform of beating just hit the platform and be located outside the organism, the inner of regulating part passes the organism and links to each other with the front end of catapulting body, adjusts the regulating part can drive the catapulting body and rotate the central axis that makes the catapulting body around the pin joint and pass through unmanned aerial vehicle's focus.
After the unmanned aerial vehicle is built, even though the gravity center points are inconsistent due to manufacturing and assembly tolerance, the unmanned aerial vehicle has high precision requirement on production, the distance of gravity center deviation is generally smaller, the unmanned aerial vehicle is of a bilateral symmetry structure, and the gravity center deviation is mostly deviation in the vertical direction. This launch some structures is direct setting in unmanned aerial vehicle, hit the part that the platform extended to outside the organism for the rear end of launching the body, hit the platform and launch the body coaxial line setting, can drive the body of launching through the regulating part and rotate around the pin joint, the upper and lower position and the angle of body of launching can finely tune promptly, make the central axis of body of launching pass through unmanned aerial vehicle's focus, rocket thrust line aims at unmanned aerial vehicle's focus when making unmanned aerial vehicle launch take off, can not have actions such as roll after making unmanned aerial vehicle launch, low head and new line, guarantee unmanned aerial vehicle launch stability, ensure unmanned aerial vehicle launch safety, make unmanned aerial vehicle be difficult for damaging.
In the unmanned aerial vehicle ejection point structure, the machine body is further provided with a reinforcing frame, the rear end of the ejection body is hinged with the reinforcing frame, and the circumferential edge of the reinforcing frame is fixedly connected with the machine body. When the hitting platform is stressed, all forces are transmitted to the reinforcing frame, the force is transmitted to the machine body through the circumferential edge of the reinforcing frame, the conversion from rocket thrust to unmanned aerial vehicle ejection force is completed, the force transmission mode is large in machine body stressed area, the machine body is stressed more uniformly, the problems that when an ejection unmanned aerial vehicle is launched by means of a rocket, the loading is large and the stress point is small are solved, the unmanned aerial vehicle body is prevented from being damaged by rocket thrust, and local reinforcing structures can be arranged at the joint of the reinforcing frame and the machine body if necessary.
In the unmanned aerial vehicle catapulting point structure, the hinge hole that supplies the catapulting body rear end to wear to establish has in the reinforcing frame, the left and right sides of catapulting body rear end is the plane form and supports the face of leaning on, support the face of leaning on closely and lean on the pore wall in hinge hole, all have the clearance between catapulting body and hinge hole top pore wall and the bottom pore wall. The structure ensures that the ejection body cannot deflect left and right, the ejection body can only be adjusted in a vertical rotation way, the central axis of the ejection body can pass through the gravity center of the unmanned aerial vehicle, and the continuous transmission of rocket thrust is also ensured; meanwhile, as the abutting surface is closely abutted against the hole wall of the hinge hole, the ejection body can only rotate around the hinge point under the condition of applying set external force, and the gravity of the ejection body alone cannot rotate.
In the unmanned aerial vehicle ejection point structure, the thickness of the bottom of the reinforcing frame provided with the hinge holes along the front-back direction of the machine body is larger than the thickness of the rest parts of the reinforcing frame, the bottom of the reinforcing frame is of a solid structure, and the rest parts of the reinforcing frame are of hollow structures. This kind of structure, the weight is lighter when making the reinforcing frame have enough intensity, reduces unmanned aerial vehicle's weight under the circumstances of assurance unmanned aerial vehicle security.
In the unmanned aerial vehicle catapulting point structure, the regulating part comprises a regulating bolt and a plurality of regulating gaskets, the rod part of the regulating bolt penetrates through the machine body and is fixedly connected with the front end threads of the catapulting body, and the regulating gaskets are sleeved outside the rod part of the regulating bolt and are positioned between the head part of the regulating bolt and the machine body. During adjustment, the unmanned aerial vehicle with the ejection point structure is placed on an unmanned aerial vehicle gravity center adjusting tool, the adjusting bolt is fixedly connected with the front end screw thread of the ejection body, namely, the adjusting bolt is detachable, and the central axis of the ejection body passes through the gravity center of the unmanned aerial vehicle in a mode of repeatedly disassembling and assembling the adjusting bolt and increasing and decreasing the adjusting gasket, so that the adjustment is convenient, and the cost is low; meanwhile, as the adjusting bolt directly passes through the machine body, the adjusting bolt is not in threaded connection with the machine body, when the striking table is stressed, the adjusting bolt can be clamped with the machine body to generate weak connection, and as the inner end of the adjusting bolt is connected with the front end of the ejection body, the force arm is larger, the weak connection can also provide a certain force to ensure that the ejection body cannot deflect, and the central axis of the ejection body cannot change. In actual production, the adjustable bolt can also be adjusted by changing adjusting bolts with different weights, sizes and lengths.
In the unmanned aerial vehicle catapulting point structure, the through hole is formed in the machine body, the through hole is used for penetrating the joint of the striking platform and the catapulting body, a gap is formed between the joint of the striking platform and the catapulting body and the hole wall of the through hole, and a gap is formed between the striking platform and the machine body. The structure ensures that the ejection body cannot touch the machine body during adjustment, ensures that the central axis of the ejection body can pass through the gravity center of the unmanned aerial vehicle, and prevents the machine body from being damaged when the striking table receives rocket thrust.
In the unmanned aerial vehicle catapulting point structure, one end of the striking platform, which is close to the catapulting body, is provided with a convex edge which is arranged in an outward protruding mode, and the convex edge is provided with a plurality of guide holes for the guide pins to penetrate through. One end of the guide pin is inserted into the guide hole, and the other end of the guide pin is connected with the rocket, so that the rocket thrust line and the ejection body are always coaxial, and the stability of unmanned aerial vehicle launching is improved through the gravity center of the unmanned aerial vehicle; after the rocket is launched, the pin and the rocket automatically fall off under the action of gravity and inertia, so that the flight of the unmanned aerial vehicle is not affected.
In the unmanned aerial vehicle catapulting point structure, a hinge shaft is arranged in the machine body in a penetrating mode, and the hinge shaft penetrates through the rear ends of the reinforcing frame and the catapulting body to enable the reinforcing frame to be hinged with the catapulting body. The hinge shaft firstly plays a role in connecting the reinforcing frame and the ejection body, and secondly, when the ejection body is stressed, force is transmitted to the reinforcing frame through the hinge shaft, and then the force is transmitted to the machine body through the reinforcing frame.
In the unmanned aerial vehicle catapulting point structure, the front end of catapulting body is provided with the bar passageway that is rectangular form along the organism fore-and-aft direction, axial positioning circumference rotatable in the bar passageway is provided with the locking axle, have the locking hole in the locking axle, catapulting point structure still includes the locking bolt, the bottom of organism is provided with the bar hole that is rectangular form along the organism fore-and-aft direction, the pole portion of locking bolt stretches into the organism through the bar hole and wears to establish in the locking hole and make locking bolt and locking axle screw thread link firmly. After the angle of the ejection body is finely adjusted, the position can be changed slightly, the locking shaft can rotate circumferentially to buffer the change, the locking bolt directly penetrates through the machine body, the locking bolt is not in threaded connection with the machine body, the locking bolt is matched with the adjusting piece, a weak connection is generated between the locking bolt and the machine body, a certain force can be provided for guaranteeing that the ejection body cannot deflect, and further the central axis of the ejection body cannot change.
In the unmanned aerial vehicle catapulting point structure, the catapulting point structure still includes the regulation frame of fixing in the organism, have in the regulation frame and supply to catapulting body front end to wear to establish and be rectangular form regulation hole, the front end of catapulting body can reciprocate along the regulation hole, it has the clearance to catapulting between body and the regulation frame. The adjusting frame plays a role in supporting the machine body, the strength of the machine body is improved, and meanwhile, whether the ejection body is installed in place or not can be judged through the arrangement of the adjusting frame and the adjusting holes.
In the unmanned aerial vehicle catapulting point structure, the adjusting piece and the locking bolt are respectively located on the front side and the rear side of the adjusting frame, and gaps are reserved between the adjusting piece and the adjusting frame and between the locking bolt and the adjusting frame. The space is reasonably utilized, and the adjusting piece, the locking bolt and the adjusting frame can not interfere with each other.
In the unmanned aerial vehicle catapulting point structure, the catapulting body is rectangular, a plurality of lightening holes have been seted up in the catapulting body. The weight of the ejection body is reduced by the arrangement of the weight reducing holes, and the weight of the unmanned aerial vehicle is reduced.
Compared with the prior art, the unmanned aerial vehicle ejection point structure provided by the invention has the following advantages:
1. the vertical position and the angle of this launch point structure launch body can finely tune, make the central axis of launch body pass through unmanned aerial vehicle's focus, and the rocket thrust line aims at unmanned aerial vehicle's focus when making unmanned aerial vehicle launch take off, can not exist actions such as rolling, low head and new line after making unmanned aerial vehicle launch, guarantee unmanned aerial vehicle launch stability, ensure unmanned aerial vehicle launch safety, make unmanned aerial vehicle be difficult for impaired.
2. This catapulting point structure is through setting up the strengthening frame, makes to hit the platform atress and passes through the strengthening frame and transmit the organism again, improves the atress area, and the organism atress is more even, prevents rocket thrust damage unmanned aerial vehicle organism.
3. The adjusting piece and the locking bolt of the ejection point structure are both partially positioned outside the machine body, a weak connection is generated between the adjusting piece and the machine body and between the locking bolt and the machine body, the weak connection can provide a certain force to ensure that the ejection body cannot deflect, the central axis of the ejection body is further ensured not to change, and the emission success rate of the unmanned aerial vehicle is ensured.
Drawings
Fig. 1 is a schematic view of the whole structure of the ejection point structure installed in a machine body.
Fig. 2 is a perspective view of the overall structure of the present ejector point structure installed into the body.
Fig. 3 is an exploded view of the present shoot point structure and body.
Fig. 4 is a schematic overall structure of the ejection point structure.
Fig. 5 is an exploded view of a partial structure of the present shoot dot structure.
Fig. 6 is a schematic structural view of the hinge joint of the ejection body and the reinforcing frame of the ejection point structure.
Fig. 7 is a schematic diagram of the structure of the strip-shaped hole and the via hole of the ejection point structure.
In the figure, 1, a machine body; 11. a via hole; 12. a bar-shaped hole; 2. an adjusting member; 21. an adjusting bolt; 22. adjusting the gasket; 3. a reinforcing frame; 31. a hinge hole; 4. an ejection body; 41. an abutment surface; 42. a strip-shaped channel; 43. a lightening hole; 5. a striking table; 51. a convex edge; 52. a guide hole; 6. a hinge shaft; 7. a locking shaft; 71. a locking hole; 8. a locking bolt; 9. an adjusting frame; 91. and adjusting the hole.
Detailed Description
The following are specific embodiments of the present invention and the technical solutions of the present invention will be further described with reference to the accompanying drawings, but the present invention is not limited to these embodiments.
As shown in fig. 1, 2 and 3, the unmanned aerial vehicle comprises a machine body 1, the ejection point structure comprises an adjusting piece 2, a reinforcing frame 3, an ejection body 4, a striking table 5, a hinge shaft 6, a locking shaft 7, a locking bolt 8 and an adjusting frame 9, and the reinforcing frame 3, the ejection body 4, the locking shaft 7 and the adjusting frame 9 are all positioned in the machine body 1.
The circumferential edge of the reinforcing frame 3 is fixedly connected with the machine body 1 through an adhesive, the ejection body 4 is arranged along the front-back direction of the machine body 1, the ejection body 4 is in a strip shape, in the embodiment, three lightening holes 43 are formed in the ejection body 4, and in actual production, the number of the lightening holes 43 can be four or five.
As shown in fig. 4, the bottom of the reinforcing frame 3 is provided with a hinge hole 31, the rear end of the ejection body 4 is inserted into the hinge hole 31, the machine body 1 is inserted with a hinge shaft 6, and the hinge shaft 6 penetrates through the rear ends of the reinforcing frame 3 and the ejection body 4 to enable the reinforcing frame 3 and the ejection body 4 to be hinged. As shown in fig. 6, the left and right sides of the rear end of the ejection body 4 are planar abutment surfaces 41, the abutment surfaces 41 are closely abutted against the wall of the hinge hole 31, and gaps are formed between the ejection body 4 and the top and bottom walls of the hinge hole 31. The thickness of the bottom of the reinforcing frame 3 provided with the hinge hole 31 along the front-back direction of the machine body 1 is larger than the thickness of the rest parts of the reinforcing frame 3, the bottom of the reinforcing frame 3 is of a solid structure, and the rest parts of the reinforcing frame 3 are of hollow structures.
The rear end of the ejection body 4 is fixedly connected with the striking table 5, the striking table 5 is positioned outside the machine body 1, a through hole 11 is formed in the machine body 1, the through hole 11 is used for penetrating the joint of the striking table 5 and the ejection body 4, a gap is formed between the joint of the striking table 5 and the ejection body 4 and the hole wall of the through hole 11, and a gap is formed between the striking table 5 and the machine body 1. The striking platform 5 has a protruding edge 51 protruding outwards near the ejection body 4, in this embodiment, the protruding edge 51 has four guiding holes 52 for guiding pins to pass through, and in actual production, the number of the guiding holes 52 may be three or six.
The adjusting piece 2 comprises an adjusting bolt 21 and an adjusting gasket 22, wherein the rod part of the adjusting bolt 21 penetrates through the machine body 1 and is fixedly connected with the front end of the ejection body 4 through threads, and the adjusting gasket 22 is sleeved outside the rod part of the adjusting bolt 21 and is positioned between the head part of the adjusting bolt 21 and the machine body 1. As shown in fig. 5, the front end of the ejection body 4 is provided with a strip-shaped channel 42 along the front-back direction of the body 1, the strip-shaped channel 42 is axially positioned and circumferentially rotatably provided with a locking shaft 7, and the locking shaft 7 is provided with a locking hole 71. As shown in fig. 7, a strip-shaped hole 12 is provided at the bottom of the machine body 1 in the front-rear direction of the machine body 1, and the rod portion of the locking bolt 8 extends into the machine body 1 through the strip-shaped hole 12 and is inserted into the locking hole 71 to fix the locking bolt 8 and the locking shaft 7 by screw threads.
The adjusting frame 9 is provided with an adjusting hole 91 which is provided with a strip shape and penetrates through the front end of the ejection body 4, the front end of the ejection body 4 can move up and down along the adjusting hole 91, and a gap is reserved between the ejection body 4 and the adjusting frame 9. The adjusting piece 2 and the locking bolt 8 are respectively positioned at the front side and the rear side of the adjusting frame 9, and gaps are reserved between the adjusting piece 2 and the locking bolt 8 and between the adjusting frame 9.
During adjustment, the center of gravity of the unmanned aerial vehicle is detected through equipment, then the machine body 1 with the ejection point structure is placed on an unmanned aerial vehicle center of gravity adjustment tool, the ejection body 4 rotates around the hinge shaft 6 in a mode of assembling and disassembling the adjusting bolt 21 and increasing and decreasing the adjusting gasket 22 for multiple times, the central axis of the ejection body 4 passes through the center of gravity of the unmanned aerial vehicle, the adjusting bolt 21 is locked, and finally the locking bolt 8 is locked, so that the ejection body 4 is fixed.
The specific embodiments described herein are offered by way of example only to illustrate the spirit of the invention. Those skilled in the art may make various modifications or additions to the described embodiments or substitutions thereof without departing from the spirit of the invention or exceeding the scope of the invention as defined in the accompanying claims.
Although the terms of the body 1, the via hole 11, the bar hole 12, the adjusting member 2, the adjusting bolt 21, the adjusting washer 22, the reinforcing frame 3, the hinge hole 31, the ejector body 4, the abutment surface 41, the bar passage 42, the lightening hole 43, the striking table 5, the flange 51, the guide hole 52, the hinge shaft 6, the locking shaft 7, the locking hole 71, the locking bolt 8, the adjusting frame 9, the adjusting hole 91 are used more herein, the possibility of using other terms is not excluded. These terms are used merely for convenience in describing and explaining the nature of the invention; they are to be interpreted as any additional limitation that is not inconsistent with the spirit of the present invention.
Claims (9)
1. The utility model provides an unmanned aerial vehicle catapult point structure, unmanned aerial vehicle includes organism (1), its characterized in that, catapult point structure includes regulating part (2), is located catapult body (4) and fixes regulating frame (9) in organism (1), the fore-and-aft direction setting of organism (1) is followed to catapult body (4), the rear end of catapulting body (4) is articulated mutually with organism (1), the rear end of catapulting body (4) has linked firmly and has hit platform (5) just hit platform (5) and is located outside organism (1), the inner of regulating part (2) passes organism (1) and links to each other with the front end of catapulting body (4), have in regulating frame (9) and supply to set up in the front end of catapulting body (4) and be rectangular form regulation hole (91), the front end of catapulting body (4) can reciprocate along regulation hole (91), have the clearance between catapulting body (4) and regulating frame (9), adjust regulating part (2) can drive the body (4) and make the center of gravity of the body (4) pass through the articulated point of the unmanned aerial vehicle who catapulting of the centre of gravity of catapulting of messenger's body (4).
2. The unmanned aerial vehicle ejection point structure according to claim 1, wherein a reinforcing frame (3) is further arranged in the machine body (1), the rear end of the ejection body (4) is hinged with the reinforcing frame (3), and the circumferential edge of the reinforcing frame (3) is fixedly connected with the machine body (1).
3. The unmanned aerial vehicle ejection point structure according to claim 2, wherein the reinforcing frame (3) is provided with a hinge hole (31) penetrated by the rear end of the ejection body (4), the left side and the right side of the rear end of the ejection body (4) are plane-shaped abutting surfaces (41), the abutting surfaces (41) are tightly abutted against the hole wall of the hinge hole (31), and gaps are reserved between the ejection body (4) and the top hole wall and the bottom hole wall of the hinge hole (31).
4. A launch point structure of an unmanned aerial vehicle according to claim 1, 2 or 3, wherein the adjusting member (2) comprises an adjusting bolt (21) and a plurality of adjusting gaskets (22), a rod portion of the adjusting bolt (21) penetrates through the machine body (1) and is fixedly connected with a front end thread of the launch body (4), and the adjusting gaskets (22) are sleeved outside the rod portion of the adjusting bolt (21) and are located between a head portion of the adjusting bolt (21) and the machine body (1).
5. An unmanned aerial vehicle ejection point structure according to claim 1, 2 or 3, wherein the body (1) is provided with a via hole (11), the via hole (11) is used for the joint of the striking table (5) and the ejection body (4) to penetrate, a gap is formed between the joint of the striking table (5) and the ejection body (4) and the wall of the via hole (11), and a gap is formed between the striking table (5) and the body (1).
6. A launch point structure of an unmanned aerial vehicle according to claim 1, 2 or 3, wherein one end of the striking table (5) close to the launch body (4) is provided with a convex edge (51) which is arranged to be outwards convex, and the convex edge (51) is provided with a plurality of guide holes (52) for the guide pins to pass through.
7. A launch point structure of an unmanned aerial vehicle according to claim 2 or 3, wherein a hinge shaft (6) is provided in the body (1), and the hinge shaft (6) passes through the rear ends of the reinforcing frame (3) and the launch body (4) to hinge the reinforcing frame (3) and the launch body (4).
8. An unmanned aerial vehicle ejection point structure according to claim 1, 2 or 3, wherein the front end of the ejection body (4) is provided with a strip-shaped channel (42) along the front-back direction of the machine body (1), the strip-shaped channel (42) is axially positioned and circumferentially rotatably provided with a locking shaft (7), the locking shaft (7) is internally provided with a locking hole (71), the ejection point structure further comprises a locking bolt (8), the bottom of the machine body (1) is provided with a strip-shaped hole (12) along the front-back direction of the machine body (1), and the rod part of the locking bolt (8) extends into the machine body (1) through the strip-shaped hole (12) and is penetrated into the locking hole (71) to enable the locking bolt (8) to be fixedly connected with the locking shaft (7) through threads.
9. A launch point structure of an unmanned aerial vehicle according to claim 1, 2 or 3, wherein the launch body (4) is elongated, and a plurality of lightening holes (43) are formed in the launch body (4).
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| CN202110474700.4A CN113148213B (en) | 2021-04-29 | 2021-04-29 | Unmanned aerial vehicle catapult point structure |
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