Storage mechanism and low-altitude aircraft

Abstract

The utility model relates to the technical field of low-altitude aircrafts, in particular to a storage mechanism and a low-altitude aircraft. The supporting assembly comprises a transverse frame arranged at the bottom of the bearing shell, a sleeve arranged at the bottom of the transverse frame and supporting legs arranged on the inner wall of the sleeve, and when the low-altitude aircraft lands, the supporting legs make contact with the ground and can bear counter-acting force of the ground; the battery bin assembly comprises a containing bin arranged on the side face of the bearing shell, a friction plate arranged on the inner wall of the containing bin, a supporting plate arranged at the bottom of the containing bin and a balancing weight arranged on the top of the supporting plate, a battery is stored in the containing bin, and the battery bin assembly protects the battery when the low-altitude aircraft flies, so that the safety of the low-altitude aircraft is improved. When the low-altitude aircraft lands, the supporting assembly can transmit counter-acting force transmitted from the ground to the balancing weight, the battery bin assembly is opened through the balancing weight, an operator can quickly detach a battery, and time is saved.

Description

Technical Field

[0001] The utility model relates to the technical field of low-altitude aircraft, in particular to a storage mechanism and a low-altitude aircraft. Background Art

[0002] Unmanned aerial vehicles (UAVs), also known as "drones" ("UAVs"), are unmanned aerial vehicles that are controlled by radio remote control equipment and self-contained program control devices. UAVs are actually a general term for unmanned aerial vehicles. From a technical point of view, they can be divided into: unmanned fixed-wing aircraft, unmanned vertical take-off and landing aircraft, unmanned airships, unmanned helicopters, unmanned multi-rotor aircraft, unmanned paragliders, etc. Among them, unmanned multi-rotor aircraft are the most common, and some unmanned multi-rotor aircraft are used for competitive flying, which is quite beneficial to the development of unmanned multi-rotor aircraft.

[0003] In drone racing, speed and efficiency are key factors in achieving victory. Racing aircraft need to land to replace batteries after long-distance flights, and the time required to replace batteries on landing should be minimized. Therefore, it is particularly important to design a drone that can achieve fast battery replacement.

[0004] The purpose of this section is to summarize some aspects of the embodiments of the present invention and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and in the abstract and title of the utility model to avoid obscuring the purpose of this section, the abstract and the title of the utility model, and such simplifications or omissions shall not be used to limit the scope of the present invention.

[0005] In view of the fact that there is a need in the prior art for a low-altitude aircraft capable of quickly disassembling batteries, the present utility model is proposed.

[0006] In order to solve the above technical problems, the present invention provides the following technical solutions: a storage mechanism, which includes a load-bearing shell; and a support assembly, including a cross frame arranged at the bottom of the load-bearing shell, a sleeve arranged at the bottom of the cross frame, and a support leg arranged on the inner wall of the sleeve; and a battery compartment assembly, including a accommodating compartment arranged on the side of the load-bearing shell, a friction plate arranged on the inner wall of the accommodating compartment, a support plate arranged at the bottom of the accommodating compartment, and a counterweight block arranged on the top of the support plate.

[0007] As a preferred solution of the storage mechanism of the present invention, the outer wall of the support leg is provided with a slide cylinder, the outer wall of the sleeve is provided with a slide groove, the inner wall of the slide groove is provided with a connecting rod, one end of the connecting rod is connected to the slide cylinder, the end of the connecting rod away from the slide cylinder is provided with a centralizing disk, and the top of the centralizing disk is provided with a top column.

[0008] As a preferred solution of the storage mechanism of the present invention, a gasket is provided on the top of the supporting leg, and the top of the gasket is connected to the horizontal frame.

[0009] As a preferred solution of the storage mechanism of the present invention, the axis of the top column and the center of mass of the support plate are located on the same plumb line, and the top of the top column is connected to the bottom of the support plate.

[0010] As a preferred solution of the storage mechanism of the present invention, the top of the counterweight block is provided with an arc surface, the side of the arc surface is provided with a twisted rope, the side of the twisted rope is provided with a first guide wheel, and the side of the first guide wheel is provided with a first rotating frame.

[0011] As a preferred solution of the storage mechanism of the present invention, a second rotating frame is provided on the top of the first rotating frame, a second guide wheel is provided on the side of the second rotating frame, a clamping column is provided at one end of the twisted rope above the second guide wheel, and the top busbar of the second guide wheel is on the same horizontal line as the axis of the clamping column.

[0012] As a preferred solution of the storage mechanism of the present invention, a sliding plate is provided on the side of the clamping column, a second elastic member is provided on the side of the sliding plate, and a sliding rod is provided inside the second elastic member.

[0013] As a preferred solution of the storage mechanism of the present invention, a bin cover component is provided on the side of the slide.

[0014] As a preferred solution of the storage mechanism of the present invention, the compartment cover member includes a flip cover provided on the top of the accommodating compartment, a locking block is provided at the bottom of the flip cover, and a groove for the sliding of the clamping column is provided on the side of the locking block;

[0015] Wherein, an arc-shaped plate is provided on the top of the flip cover, and a torsion spring is provided at the connection between the flip cover and the accommodating compartment.

[0016] Provided is a low-altitude aircraft, comprising a storage mechanism, a flight control system, a motor, and a propeller.

[0017] The beneficial effects of the storage mechanism of the present invention are: the compartment cover component is automatically opened when the aircraft lands, making it convenient to remove the battery for replacement, and at the same time, the impact force of the ground on the low-altitude aircraft is used to move the counterweight block, which can reduce the impact on the battery of the low-altitude aircraft during landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0019] Figure 1 It is a schematic diagram of the overall structure of the present utility model.

[0020] Figure 2 It is a structural schematic diagram of the support assembly in the present invention and a partially enlarged schematic diagram thereof.

[0021] Figure 3 This is a structural diagram of the battery compartment assembly in the present invention.

[0022] Figure 4 It is an enlarged schematic diagram of point A in the present invention.

[0023] Figure 5 It is a structural schematic diagram of the flip cover in the present utility model. DETAILED DESCRIPTION

[0024] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below with reference to the accompanying drawings.

[0025] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0026] Secondly, the term "one embodiment" or "embodiment" herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in various places throughout this specification does not necessarily refer to the same embodiment, nor does it refer to a separate or selective embodiment that is mutually exclusive with other embodiments.

[0027] Example 1, with reference to Figures 1 to 3, is the first embodiment of the present invention, which provides a storage mechanism, including a carrying shell 100; and a support assembly 200, including a cross frame 201 arranged at the bottom of the carrying shell 100, a sleeve 202 arranged at the bottom of the cross frame 201, and a support leg 203 arranged on the inner wall of the sleeve 202. When the low-altitude aircraft lands, the support leg 203 contacts the ground and is subjected to the reaction force of the ground; and a battery compartment assembly 300, including a storage compartment 301 arranged on the side of the carrying shell 100, a sleeve 202 arranged at the bottom of the cross frame 201, and a support leg 203 arranged on the inner wall of the sleeve 202. The friction plate 304 is placed on the inner wall of the storage compartment 301, the support plate 302 is arranged at the bottom of the storage compartment 301, and the counterweight block 303 is arranged on the top of the support plate 302. The battery is stored in the storage compartment 301. The battery compartment assembly 300 protects the battery when the low-altitude aircraft is flying. When the low-altitude aircraft lands, the support assembly 200 will transfer the reaction force from the ground to the counterweight block 303. The counterweight block 303 is used to open the battery compartment assembly 300, allowing the operator to quickly remove the battery and save time.

[0028] Usage process: The battery compartment assembly 300 protects the battery when the low-altitude aircraft is flying. When the low-altitude aircraft lands, the support leg 203 contacts the ground and will be subjected to the reaction force of the ground. The support assembly 200 will transfer the reaction force from the ground to the counterweight block 303, and use the counterweight block 303 to open the battery compartment assembly 300, so that the operator can quickly remove the battery and save time. At the same time, part of the impulse applied by the ground to the aircraft is converted into the energy required to open the battery compartment assembly 300, thereby enhancing the buffering effect and better protecting the aircraft.

[0029] Example 2, reference Figures 1 to 5 , which is the second embodiment of the present invention. Different from the previous embodiment, the outer wall of the support leg 203 is provided with a slide 205, the outer wall of the sleeve 202 is provided with a slide groove 206, and the inner wall of the slide groove 206 is provided with a connecting rod 207. The connecting rod 207 can slide in the slide groove 206. One end of the connecting rod 207 is connected to the slide 205. The slide 205 plays a sealing and blocking role between the sleeve 202 and the outside world to prevent the parts in the sleeve 202 from being contaminated. The end of the connecting rod 207 away from the slide 205 is provided with a central disk 208, and the top of the central disk 208 is provided with a top column 2 09. A gasket 204 is provided on the top of the support leg 203. The top of the gasket 204 is connected to the cross frame 201. The axis of the top column 209 and the center of mass of the support plate 302 are located on the same plumb line. The top of the top column 209 is connected to the bottom of the support plate 302. When the low-altitude aircraft lands, the speed of the low-altitude aircraft becomes zero when the support leg 203 touches the ground. At this time, the low-altitude aircraft receives the impact force of the ground, and the support leg 203 will move upward, driving the slide 205 and the connecting rod 207 to move upward, and then driving the central disk 208 to move upward, and finally driving the support plate 302 to move upward.

[0030] Furthermore, the top of the counterweight 303 is provided with an arc surface 305, the side of the arc surface 305 is provided with a rope 306, the side of the rope 306 is provided with a first guide wheel 307, the side of the first guide wheel 307 is provided with a first rotating frame 308, the first guide wheel 307 guides the rope 306 to extend upward, the top of the first rotating frame 308 is provided with a second rotating frame 309, the side of the second rotating frame 309 is provided with a second guide wheel 310, the rope 306 is provided with a first guide wheel 310, and the rope 306 is provided with a first guide wheel 310. A clamping column 311 is provided at one end above the second guide wheel 310. The top busbar of the second guide wheel 310 and the axis of the clamping column 311 are on the same horizontal line. When the low-altitude aircraft lands, the impact force of the ground drives the support plate 302 to move upward, and the support plate 302 will drive the counterweight block 303 to move upward. The counterweight block 303 will move upward with the bottom end of the winch rope 306, and then the end of the winch rope 306 connected to the clamping column 311 will move toward the second turntable 309.

[0031] Furthermore, a slide 312 is provided on the side of the clamping column 311, a second elastic member 314 is provided on the side of the slide 312, a slide rod 313 is provided inside the second elastic member 314, and a groove with the same outer diameter as the slide rod 313 is provided on the slide 312. The slide 312 can slide along the direction of the slide rod 313 together with the clamping column 311. When the end of the rope 306 connected to the clamping column 311 moves toward the direction of the second rotating frame 309, it will drive the clamping column 311 to slide together.

[0032] Furthermore, a compartment cover component 315 is provided on the side of the slide 312, and the compartment cover component 315 includes a flip cover 315a provided on the top of the accommodating compartment 301, and a locking block 315b is provided at the bottom of the flip cover 315a. A groove for the sliding of the card column 311 is provided on the side of the locking block 315b. When the card column 311 is in the groove on the side of the locking block 315b, the flip cover 315a is locked, which protects the battery in the accommodating compartment 301.

[0033] Usage process: During the normal flight of the low-altitude aircraft, the flip cover 315a is covered above the accommodating chamber 301, and the locking block 315b is locked by the clamping column 311 and cannot be opened, which protects the battery. When the low-altitude aircraft lands, the speed of the low-altitude aircraft becomes zero when the support leg 203 touches the ground. At this time, the low-altitude aircraft receives the impact force of the ground, and the support leg 203 will move upward, driving the slide 205 and the connecting rod 207 to move upward, and then driving the central disk 208 to move upward, and finally driving the support plate 302 to move upward, and the support plate 302 will drive As the counterweight 303 moves upward, the counterweight 303 will move upward with the winch 306 at the bottom, so that the end of the winch 306 connected to the clamping column 311 will move toward the second rotating frame 309, driving the clamping column 311 to slide together and disengage from the groove on the side of the locking block 315b. At this time, the flip cover 315a is unlocked, and the operator can easily open the flip cover 315a, take out the battery, and replace the battery, saving time. In addition, the impact force of the ground on the low-altitude aircraft to move the counterweight 303 can reduce the impact on the battery during landing and better protect the battery.

[0034] Example 3, reference Figures 1 to 5 This is the third embodiment of the present utility model. Different from the previous embodiment, an arc-shaped plate 315c is provided on the top of the flip cover 315a, and a torsion spring 315d is provided at the connection between the flip cover 315a and the accommodating chamber 301. When the low-altitude aircraft lands and the flip cover is unlocked, the arc-shaped plate 315c can facilitate the staff to open the flip cover 315a. When the battery replacement is completed, the flip cover 315a is lowered, and the torsion spring 315d will automatically return the flip cover 315a to its original position.

[0035] Usage process: When the battery replacement is completed, the flip cover 315a returns to the top of the accommodating chamber 301 under the action of the torsion spring 315d. Since the friction plate 304 is provided on the inner wall of the accommodating chamber 301, the counterweight block 303 will slowly move downward relative to the low-altitude aircraft. At this time, the rope 306 is loosened, so the second elastic member 314 will slide the slide 312 and the clamping column 311 toward the locking block 315b until the clamping column 311 extends into the locking block 315b, locking the flip cover 315a and continuing to protect the battery during the flight of the low-altitude aircraft.

[0036] Example 4, with reference to Figures 1 to 5 , which is the fourth embodiment of the present utility model. This embodiment is based on the previous embodiment, but differs in that it provides a low-altitude aircraft, including a storage mechanism, a flight control system 400, a motor 500 and a propeller 600.

[0037] The flight control system 400 receives ground remote control signals and controls the flight, and the motor 500 provides power to the propeller 600 to drive the low-altitude aircraft to fly.

[0038] It is important to note that the construction and arrangement of the present application shown in a number of different exemplary embodiments are merely illustrative. Although only a few embodiments are described in detail in this disclosure, it should be readily understood by those who refer to this disclosure that many modifications are possible (e.g., the size, scale, structure, shape and proportion of various elements, and parameter values (e.g., temperature, pressure, etc.), mounting arrangements, use of materials, colors, directional changes, etc.) without departing substantially from the novel teachings and advantages of the subject matter described in this application. For example, an element shown as integrally formed may be composed of multiple parts or elements, the position of the element may be inverted or otherwise changed, and the nature or number or position of the discrete elements may be altered or changed. Therefore, all such modifications are intended to be included within the scope of the present invention. The order or sequence of any process or method steps may be changed or reordered according to alternative embodiments. In the claims, any "means plus function" clause is intended to cover the structure of performing the function described herein, and is not only structurally equivalent but also an equivalent structure. Without departing from the scope of the present invention, other substitutions, modifications, changes and omissions may be made in the design, operating conditions and arrangement of the exemplary embodiments. Therefore, the present invention is not limited to the specific embodiments, but extends to various modifications that still fall within the scope of the appended claims.

[0039] Additionally, in order to provide a concise description of example embodiments, all features of an actual embodiment (ie, those features that are not relevant to the best mode presently contemplated for carrying out the invention or those that are not relevant to implementing the invention) may not be described.

[0040] It will be appreciated that in the development of any actual embodiment, as in any engineering or design project, numerous implementation-specific decisions may be made. Such a development effort may be complex and time-consuming, but will, for those of ordinary skill having the benefit of this disclosure, be a routine undertaking of design, fabrication, and production without undue experimentation.

[0041] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, and all of these should be included in the scope of the claims of the present invention.

Claims

1. A storage mechanism, characterized in that: include, a carrying shell (100); and A support assembly (200) comprises a cross frame (201) disposed at the bottom of the bearing shell (100), a sleeve (202) disposed at the bottom of the cross frame (201), and a support leg (203) disposed on the inner wall of the sleeve (202); and The battery compartment assembly (300) comprises a accommodating compartment (301) arranged on the side of the carrying shell (100), a friction plate (304) arranged on the inner wall of the accommodating compartment (301), a support plate (302) arranged at the bottom of the accommodating compartment (301), and a counterweight (303) arranged on the top of the support plate (302).

2. The storage mechanism according to claim 1, wherein: The outer wall of the support leg (203) is provided with a slide (205), the outer wall of the sleeve (202) is provided with a slide groove (206), the inner wall of the slide groove (206) is provided with a connecting rod (207), one end of the connecting rod (207) is connected to the slide (205), and the end of the connecting rod (207) away from the slide (205) is provided with a centralizing disk (208), and the top of the centralizing disk (208) is provided with a top column (209).

3. The storage mechanism according to claim 2, wherein: A gasket (204) is provided on the top of the support leg (203), and the top of the gasket (204) is connected to the cross frame (201).

4. The storage mechanism according to claim 3, wherein: The axis of the top column (209) and the center of mass of the support plate (302) are located on the same plumb line.

5. The storage mechanism according to claim 4, wherein: The top of the counterweight block (303) is provided with an arc surface (305), the side of the arc surface (305) is provided with a twisted rope (306), the side of the twisted rope (306) is provided with a first guide wheel (307), and the side of the first guide wheel (307) is provided with a first rotating frame (308).

6. The storage mechanism according to claim 5, wherein: A second rotating frame (309) is provided on the top of the first rotating frame (308), a second guide wheel (310) is provided on the side of the second rotating frame (309), a clamping column (311) is provided at one end of the twisted rope (306) above the second guide wheel (310), and the top busbar of the second guide wheel (310) and the axis of the clamping column (311) are on the same horizontal line.

7. The storage mechanism according to claim 6, wherein: A sliding plate (312) is provided on the side of the clamping column (311), a second elastic member (314) is provided on the side of the sliding plate (312), and a sliding rod (313) is provided inside the second elastic member (314).

8. The storage mechanism according to claim 7, wherein: A bin cover component (315) is provided on the side of the slide (312).

9. The storage mechanism according to claim 8, wherein: The bin cover component (315) comprises a flip cover (315a) arranged on the top of the accommodating bin (301), a locking block (315b) is arranged at the bottom of the flip cover (315a), and a groove for the sliding of the clamping column (311) is provided on the side of the locking block (315b); Wherein, an arc-shaped plate (315c) is provided on the top of the flip cover (315a), and a torsion spring (315d) is provided at the connection between the flip cover (315a) and the accommodating chamber (301).

10. A low-altitude aircraft, characterized by: The invention comprises the storage mechanism according to any one of claims 1 to 9, and further comprises a flight control system (400), a motor (500) and a propeller (600).

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