CN106892090B

CN106892090B - Aircraft foot rest locking device and aircraft

Info

Publication number: CN106892090B
Application number: CN201610526161.3A
Authority: CN
Inventors: 郑卫锋; 其他发明人请求不公开姓名
Original assignee: PowerVision Robot Inc
Current assignee: PowerVision Robot Inc
Priority date: 2015-12-18
Filing date: 2016-07-05
Publication date: 2020-06-30
Anticipated expiration: 2036-07-05
Also published as: CN106892090A

Abstract

The invention provides an aircraft foot stool locking device and an aircraft, wherein the aircraft foot stool locking device comprises a framework (51), and the framework (51) is used for being connected with a foot stool (3); the framework (51) is provided with a sliding assembly (54), the first end of the sliding assembly (54) is arranged opposite to the foot rest (3), the second end of the sliding assembly (54) is connected with a driving assembly, and the driving assembly is used for driving the sliding assembly (54) to move towards the foot rest (3) so that the first end of the sliding assembly (54) is outwards pressed against the foot rest (3). When aircraft starts or the foot rest is opened, drive assembly work, and drive sliding assembly moves towards the foot rest, slides when first end of sliding assembly supports when pressing with the foot rest contact, and outwards thrust is applyed to the foot rest to sliding assembly, locks the foot rest, prevents that the foot rest from producing vibrations at the in-process of flight, guarantees the quality of the image of flight safety and aircraft shooting.

Description

Aircraft foot rest locking device and aircraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aircraft foot rest locking device and an aircraft.

Background

The multi-rotor aircraft has the advantages of flexibility, quick response, strong environmental adaptability, low operation requirement and the like, so that the multi-rotor aircraft is widely applied to three fields of military affairs, scientific research and civil use to perform tasks such as transportation, monitoring, investigation, exploration, shooting and the like. Multi-rotor aircraft typically include a fuselage, arms, a foot rest (also referred to as landing gear), and an aircraft control system. The horn is connected in fuselage upper portion, has the driving system who is used for driving this many rotor crafts on every horn, and the foot rest is installed to the fuselage lower part, and fuselage inside is provided with aircraft control system. Typically, a multi-rotor aircraft includes a plurality of arms, which may be four, six, eight, or more.

When the aircraft performs field tasks, such as detection tasks, shooting tasks and the like, the aircraft is required to fly stably. Therefore, the stability greatly affects the quality of the detection data or the captured image. Minute vibrations in flight during flight may have a great influence on the detection data or the captured image.

Then, in the aircraft in the prior art, a structure for locking the foot stand is not adopted, and the foot stand is not firmly fixed, so that the foot stand is easily affected by various factors in flight after being unfolded to generate vibration, and the safety of the aircraft and the quality of images shot by the aircraft are affected.

Disclosure of Invention

The invention aims to provide an aircraft foot rest locking device to solve the technical problem that a foot rest is easy to vibrate when an aircraft flies in the prior art.

The invention provides an aircraft foot stool locking device, which comprises a framework 51, wherein the framework 51 is used for being connected with a foot stool 3; the framework 51 is provided with a sliding assembly 54, a first end of the sliding assembly 54 is opposite to the foot rest 3, a second end of the sliding assembly 54 is connected with a driving assembly, and the driving assembly is used for driving the sliding assembly 54 to move towards the foot rest 3, so that the first end of the sliding assembly 54 is outwards pressed against the foot rest 3.

Further, the drive assembly is including setting up rotate 55 in the skeleton 51, be equipped with the guide way 55a on the rotation piece 55, the first end of guide way 55a is close to the axis of rotation piece 55, the second end of guide way 55a is kept away from the axis of rotation piece 55, the second end embedding of slip assembly 54 in the guide way 55a and can be in follow under the drive of rotation piece 55 the extending direction slip of guide way 55 a. In this embodiment, the direction of the sliding assembly 54 can be controlled by controlling the rotation direction of the rotating member, so that the foot stand 3 can be switched between the locked state and the unlocked state at any time. In addition, among the drive assembly that this embodiment provided, rotate the piece only need rotate alright drive sliding assembly along its slip direction towards the foot rest or keep away from the foot rest motion, the volume that rotates the piece can be less with from the weight average to save drive assembly's occupation space, conveniently arrange on the aircraft, and can alleviate the dead weight of aircraft. Further, the guide groove 55a is arc-shaped. Wherein, the first end of curved guide way 55a is close to the axis of rotation of rotating member 55, the second end of guide way 55a is kept away from the axis of rotation of rotating member 55, because the distance between curved guide way and the axis of rotation of rotating member is gradual change and curved guide way is very smooth, make the second end of slip subassembly slide gradually in curved guide way 55a, avoid blocking in the guide way.

Further, the rotating member 55 is a gear, and the guide groove 55a is provided on an end surface of the gear. This embodiment only need one or a plurality of guide way 55a to realize the gliding effect of drive slip subassembly on the basis of ordinary gear, the guide way is seted up on the terminal surface of gear (between the teeth of a cogwheel of the center pin of gear and gear), and it is convenient to make, with low costs to do not influence the rotation of gear, can also alleviate the dead weight of gear simultaneously, can adopt less power supply to come drive gear rotation.

Further, the driving assembly further includes a motor 57 and a driving gear 56, the motor 57 drives the driving gear 56, and the driving gear 56 drives the rotating member 55 to rotate around the rotation axis. When the rotating part is a gear, the rotating axis of the rotating part is the central line of the gear. The motor is used as a power source, and compared with other power sources, the motor has the advantage of convenient control (namely the running state of the motor can be controlled by controlling the power supply information of the motor), and automatic control is utilized; in addition, the driving gear 56 is adopted to drive the rotating part 55, and the rotating part 55 is of a gear structure, and at this time, the rotating part is equivalent to a driven gear, and the gear transmission mechanism formed by the driving gear 56 and the rotating part 55 is accurate and stable in gear transmission mode, so that the rotating angle of the rotating part 55 can be conveniently controlled, and the moving distance of the sliding component 54 can be accurately controlled, wherein the more the sliding component 54 moves towards the foot rest 3, the greater the outward pushing force applied by the sliding component 54 to the foot rest 3 is, and the better the locking effect of the foot rest 3 is.

Further, the sliding assembly 54 includes a first sliding member 54a and a second sliding member 54b connected in an L-shape, the first sliding member 54a is disposed toward the foot rest 3, and the second sliding member 54b is inserted into the guide groove 55 a. The first sliding part 54a and the second sliding part 54b in this embodiment are connected in an L-shape, wherein the first sliding part 54a is perpendicular to the rotation axis of the rotating part 55, and the second sliding part 54b is parallel to the rotation axis of the rotating part, that is, the acting force applied by the rotating part to the second sliding part 54b during rotation is exactly parallel to the sliding direction of the first sliding part 54a, and the acting force is used for deriving the movement of the sliding components.

Further, the first slider 54a is formed integrally with the second slider 54 b. The integrated structure is very firm, the service life of the sliding assembly 54 can be prolonged, and when the first sliding part 54a and the second sliding part 54b are integrated, an intermediate connecting structure is omitted, and the manufacturing and the use are convenient.

Further, aircraft foot rest locking device still includes fixed setting the guide assembly 53 on skeleton 51, guide assembly 53 has the direction chamber, first slider 54a wears to establish in the direction chamber, first slider 54a can extend the extending direction removal in the direction chamber and follow stretch out in the direction chamber, second slider 54b stretches out outside the direction chamber. In the embodiment, the guide assembly is additionally arranged, so that the guide and constraint effects on the movement of the first sliding part 54a are achieved, the first sliding part 54a is prevented from deviating in the moving process, and the first sliding part 54a is ensured to move towards/away from the foot rest 3 along the constraint direction of the guide cavity all the time.

Further, the guide cavities and the first sliding parts 54a are all multiple, and the guide cavities and the first sliding parts 54a are arranged in a one-to-one correspondence manner. The number of the guide cavities and the first sliding parts 54a is set according to the number of the foot rests 3, when the number of the foot rests 3 is N, the number of the guide cavities and the number of the first sliding parts 54a can be N respectively, the first sliding parts 54a are arranged in one guide cavity, and one foot rest 3 is locked by the first sliding parts 54 a. In addition, the number of the guide cavities and the first sliding parts 54a can be respectively 2N, one guide cavity is internally provided with the first sliding part 54a, and the two sliding parts 54a lock one foot rest 3. The plurality of guide cavities and the plurality of first sliding parts 54a can lock the plurality of foot rests 3, thereby improving the locking force.

Further, the aircraft foot stand locking device further comprises a foot stand support 52, a first end of the foot stand support 52 is fixedly connected with the framework 51, and a second end of the foot stand support 52 is used for being connected with the foot stand 3. The foot rest support 52 facilitates the connection of the foot rest 3 with the framework 51 and also has a bearing effect on the foot rest 3, improving the strength of the locking device.

Furthermore, a clamping groove 52a is formed in the foot stand support 52, and the guide component 53 is clamped in the clamping groove 52 a. The clamping groove 52a is convenient and quick for fixing the guide component 53 on the foot rest support 52, and after the guide component is clamped in the clamping groove 52a, the guide component 53 does not protrude out of the foot rest support 52 too much, so that the arrangement space is saved.

The invention also provides an aircraft comprising a foot rest 3 and an aircraft foot rest locking device according to the invention. Due to the fact that the aircraft foot stand locking device provided by the invention is installed on the aircraft, after the foot stand 3 is unfolded, the aircraft foot stand locking device can lock the foot stand 3, the foot stand 3 is prevented from shaking in the flying process, the driving safety is improved, and the quality of shot images is guaranteed.

Further, a groove is formed in the foot rest 3 opposite to the sliding component 54, and a first end of the sliding component 54 is clamped in the groove. The embodiment not only fixes the sliding component 54 and prevents the sliding component from sliding accidentally, but also enlarges the contact area of the sliding component and the foot rest 3 into the area of the inner wall of the groove after the first end of the sliding component is clamped into the groove, thereby improving the locking force between the sliding component 54 and the foot rest 3 and preventing the foot rest 3 from shaking.

The aircraft foot stand locking device provided by the invention comprises a framework and a sliding assembly, wherein a first end of the sliding assembly is arranged opposite to a foot stand, a second end of the sliding assembly is connected with a driving assembly, when an aircraft is started or the foot stand is opened, the driving assembly works to drive the sliding assembly to move towards the foot stand, when the first end of the sliding assembly slides to be in contact with and pressed against the foot stand, the sliding assembly applies outward thrust to the foot stand to lock the foot stand, the foot stand is prevented from vibrating in the flying process, and the flying safety and the quality of images shot by the aircraft are ensured.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

Fig. 1 is a schematic view of an aircraft foot stand locking device and an installation of a foot stand according to an embodiment of the present invention;

fig. 2 is an exploded view of an aircraft foot stool locking device provided by an embodiment of the invention;

FIG. 3 is an end view of the rotary member of FIG. 2;

fig. 4 is a perspective view of the slide assembly of fig. 2.

Reference numerals:

3-a foot rest;

51-a backbone; 52-a tripod support;

53-a guide assembly; 54-a slide assembly;

55-a rotating member; 56-a drive gear;

57-an electric motor; 52 a-card slot;

54 a-a first slide; 54 b-a second slide;

55 a-guide groove.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Wherein the terms "first position" and "second position" are two different positions.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Fig. 1 is a schematic view of an aircraft foot stool locking device and a foot stool 3 according to an embodiment of the present invention; fig. 2 is an exploded view of an aircraft foot stool locking device provided by the embodiment of the invention.

The invention provides an aircraft foot stool locking device, as shown in fig. 1 and 2, the aircraft foot stool locking device comprises a framework 51, wherein the framework 51 is used for being connected with a foot stool 3; the framework 51 is provided with a sliding assembly 54, a first end of the sliding assembly 54 is arranged opposite to the foot rest 3, a second end of the sliding assembly 54 is connected with a driving assembly, and the driving assembly is used for driving the sliding assembly 54 to move towards the foot rest 3, so that the first end of the sliding assembly 54 is outwards pressed against the foot rest 3.

Wherein, fig. 1 shows four guide assemblies 53, only two of the guide assemblies 53 are labeled in fig. 1, wherein, the sliding assembly 54 in the left guide assembly 53 is in an extending state, and the sliding assembly 54 presses the foot rest 3 outwards to lock the foot rest 3; while the slide assembly 54 in the guide assembly 53 on the right is in a retracted state, the slide assembly 54 does not abut against the foot rest 3 and the foot rest 3 is not locked. That is, when the sliding assembly 54 is slid toward the foot rest 3 and the foot rest 3 is depressed, the foot rest 3 is locked; conversely, when the sliding assembly 54 is slid away from the foot rest 3 and separated from the foot rest 3, the foot rest 3 is unlocked.

The aircraft foot stool locking device provided by the invention comprises a framework 51 and a sliding component 54, wherein the sliding component is arranged on the sliding component 54, the first end of the sliding component is opposite to the foot stool, the second end of the sliding component is connected with a driving component, when the aircraft is started or the foot stool is opened, the driving component works to drive the sliding component to move towards the foot stool, when the first end of the sliding component slides to be in contact with and pressed against the foot stool, the sliding component applies outward thrust to the foot stool to lock the foot stool, so that the foot stool is prevented from vibrating in the flight process, and the flight safety and the quality of images shot by the aircraft are ensured.

The driving assembly of the present invention may be any suitable structure capable of driving the sliding assembly 54 to slide toward the foot rest 3.

In a first embodiment, the drive assembly is a linear drive assembly, such as a pneumatic cylinder, a hydraulic cylinder. Wherein, cylinder and pneumatic cylinder all include the cylinder body and set up the piston rod in the cylinder body, and one of them is connected with the second end of sliding component 54 in cylinder body and the piston rod, and another one in cylinder body and the piston rod is connected with the first end of sliding component 54, and when cylinder body and piston rod took place relative motion, one of the cylinder body and the piston rod that is connected with sliding component 54 drove sliding component 54 and moves towards foot rest 3 or keep away from foot rest 3.

More specifically, the cylinder in the above embodiment may be fixedly disposed on the frame 51, and one end of the piston rod extending out of the cylinder is fixedly connected to the sliding assembly 54, and when the piston rod retracts toward the inside of the cylinder, the piston rod drives the sliding assembly 54 to slide away from the foot rest 3; when the piston rod extends out of the cylinder, the piston rod drives the sliding component 54 to slide towards the foot rest 3, and when the sliding component contacts with the foot rest 3 and outwards presses the foot rest 3, the foot rest 3 is locked.

In this embodiment, the moving direction of the piston rod can be flexibly controlled by controlling the air intake direction of the cylinder or the oil intake direction of the hydraulic cylinder, so as to control the moving direction of the sliding assembly 54, and the foot rest 3 can be switched between the locked state and the unlocked state at any time.

In a second embodiment, the drive assembly is a rotary drive assembly. Specifically, referring to fig. 2, the driving assembly includes a rotating member 55 disposed in the frame 51, the rotating member 55 is provided with a guide groove 55a, a first end of the guide groove 55a is close to the rotation axis of the rotating member 55, a second end of the guide groove 55a is far away from the rotation axis of the rotating member 55, and a second end of the sliding assembly 54 is embedded in the guide groove 55a and can slide along the extending direction of the guide groove 55a under the driving of the rotating member 55.

Specifically, when the rotation member 55 is rotated in the first direction (e.g., clockwise direction) about the rotation axis by the driving source, the guide groove 55a of the rotation member 55 is also rotated in the first direction about the rotation axis, so that the sliding member 54 inserted into the guide groove 55a passively slides in the extending direction of the guide groove 55a, wherein when the second end of the sliding member 54 slides from the first end of the guide groove 55a to the second end of the guide groove 55a (i.e., when the second end of the sliding member is away from the rotation axis of the rotation member 55), the sliding member 54 is pushed away by the rotation member 55, and the first end of the sliding member moves toward the foot stand 3, thereby locking the foot stand. Conversely, when the rotating member 55 is rotated in a second direction (e.g., counterclockwise direction) opposite to the first direction about the rotating axis by the driving source, the guide groove 55a of the rotating member 55 is also rotated in the second direction about the rotating axis, so that the sliding member 54 inserted into the guide groove 55a passively slides in the extending direction of the guide groove 55a, and when the second end of the sliding member 54 slides from the second end of the guide groove 55a toward the first end of the guide groove 55a (i.e., when the second end of the sliding member approaches the rotating axis of the rotating member 55), the sliding member 54 is retracted inward by the driving of the rotating member 5, the first end of the sliding member is separated from the foot rest 3, thereby releasing the foot rest 3, and the foot rest 3 can be folded and retracted.

In this embodiment, the direction of the sliding assembly 54 can be controlled by controlling the rotation direction of the rotating member, so that the foot stand 3 can be switched between the locked state and the unlocked state at any time. In addition, among the drive assembly that this embodiment provided, rotate the piece only need rotate alright drive sliding assembly along its slip direction towards the foot rest or keep away from the foot rest motion, the volume that rotates the piece can be less with from the weight average to save drive assembly's occupation space, conveniently arrange on the aircraft, and can alleviate the dead weight of aircraft.

Specifically, the guide groove 55a may have various suitable shapes, such as a U shape, a straight line shape, and a broken line shape.

Preferably, as shown in fig. 2, the guide groove 55a is arc-shaped. Wherein, the first end of curved guide way 55a is close to the axis of rotation of rotating piece 55, and the second end of guide way 55a is kept away from the axis of rotation of rotating piece 55, because the distance between curved guide way and the axis of rotation of rotating piece is gradual change and curved guide way is very smooth for the second end of slip subassembly can slide gradually in curved guide way 55a, avoids blocking in the guide way.

Specifically, the shape of the guide groove 55a may be an arc groove or a non-arc groove; the number of the arc-shaped grooves can be one or more. Preferably, the arcuate slots are arranged in a one-to-one correspondence with the slide assemblies 54. As shown in fig. 2, there are four arcuate slots and slide assemblies 54, respectively. More preferably, the plurality of arc-shaped grooves are uniformly distributed along the circumferential direction of the rotating member 55 to apply an equal pushing force to the plurality of foot rests 3.

Specifically, the rotating member 55 may be a rotating block, a roller, a pulley, a gear, or other various rotatable structures.

FIG. 3 is an end view of the rotary member of FIG. 2;

preferably, as shown in fig. 2 and 3, the rotating member 55 is a gear, and the guide groove 55a is provided on an end surface of the gear. This embodiment only need one or a plurality of guide way 55a to realize the gliding effect of drive slip subassembly on the basis of ordinary gear, the guide way is seted up on the terminal surface of gear (between the teeth of a cogwheel of the center pin of gear and gear), and it is convenient to make, with low costs to do not influence the rotation of gear, can also alleviate the dead weight of gear simultaneously, can adopt less power supply to come drive gear rotation.

Further, as shown in fig. 1, the driving assembly further includes a motor 57 and a driving gear 56, the motor 57 drives the gear 56, and the driving gear 56 rotates the rotation member 55 around the rotation axis. When the rotating part is a gear, the rotating axis of the rotating part is the central line of the gear. The motor is used as a power source, and compared with other power sources, the motor has the advantage of convenient control (namely the running state of the motor can be controlled by controlling the power supply information of the motor), and automatic control is utilized; in addition, the driving gear 56 is adopted to drive the rotating part 55, and the rotating part 55 is of a gear structure, at the moment, the rotating part is equivalent to a driven gear, a gear transmission mechanism formed by the driving gear 56 and the rotating part 55 is accurate and stable in gear transmission mode, the rotating angle of the rotating part 55 is convenient to control, and the moving distance of the sliding component 54 is accurately controlled, wherein the more the sliding component 54 moves towards the foot rest 3, the larger the outward thrust exerted by the sliding component 54 on the foot rest 3 is, and the better the locking effect of the foot rest 3 is.

The diameter of the driving gear 56 may be smaller than that of the rotating member 55, that is, the driving gear 56 may transmit the power of the motor to the rotating member 55, and the smaller the volume of the driving gear is, the more convenient the arrangement is.

Fig. 4 is a perspective view of the slider in fig. 2.

Further, as shown in fig. 4, the sliding assembly 54 includes a first sliding member 54a and a second sliding member 54b connected in an L-shape, the first sliding member 54a is disposed toward the foot rest 3, and the second sliding member 54b is inserted into the guide groove 55 a. The first sliding part 54a and the second sliding part 54b in this embodiment are connected in an L-shape, wherein the first sliding part 54a is perpendicular to the rotation axis of the rotating part 55, and the second sliding part 54b is parallel to the rotation axis of the rotating part, that is, the acting force applied by the rotating part to the second sliding part 54b during rotation is exactly parallel to the sliding direction of the first sliding part 54a, and the acting force is used for deriving the movement of the sliding components.

The first sliding member 54a and the second sliding member 54b may be a split structure, for example, the second sliding member 54b is inserted into the first sliding member. The first slide 54a is threadably connected to the second slide 54 b.

Preferably, the first slider 54a is formed integrally with the second slider 54 b. The integrated structure is very firm, the service life of the sliding assembly 54 can be prolonged, and after the first sliding part 54a and the second sliding part 54b adopt the integrated structure, an intermediate connecting structure is omitted, and the manufacturing and the use are convenient. Specifically, the first sliding part 54a and the second sliding part 54b may be integrally welded, integrally bent, and integrally injection-molded.

Specifically, the first slider 54a may have a bar shape, a plate shape, or a column shape. When the first sliding member 54a is plate-shaped, the entire width of the first sliding member can contact and press the foot rest 3, so as to increase the contact area and enhance the locking effect.

Specifically, the second slide member 54b may have a cylindrical shape, and as shown in fig. 4, the contact surface between the cylindrical second slide member 54b and the arc-shaped guide groove 55a is small, so that the resistance to sliding of the second slide member 54b in the guide groove 55a is reduced, and jamming of the second slide member 54b is avoided.

Further, as shown in fig. 1 and 2, the aircraft foot stool locking device further includes a guide assembly 53 fixedly disposed on the framework 51, the guide assembly 53 has a guide cavity, the first sliding member 54a is inserted into the guide cavity, the first sliding member 54a can move along the extending direction of the guide cavity and extend out of the guide cavity (see fig. 1), and the second sliding member 54b extends out of the guide cavity. In the embodiment, the guide assembly is additionally arranged, so that the guide and constraint effects on the movement of the first sliding part 54a are achieved, the first sliding part 54a is prevented from deviating in the moving process, and the first sliding part 54a is ensured to move towards/away from the foot rest 3 along the constraint direction of the guide cavity all the time.

Preferably, the guide cavities and the first sliding parts 54a are multiple, and the multiple guide cavities and the first sliding parts 54a are arranged in a one-to-one correspondence. The number of the guide cavities and the first sliding parts 54a is set according to the number of the foot rests 3, when the number of the foot rests 3 is N, the number of the guide cavities and the number of the first sliding parts 54a can be N respectively, the first sliding parts 54a are arranged in one guide cavity, and one foot rest 3 is locked by the first sliding parts 54 a. In addition, the number of the guide cavities and the number of the first sliding parts 54a can be respectively 2N, the first sliding part 54a is arranged in one guide cavity, and one foot rest 3 is locked by the two sliding parts 54 a. The plurality of guide cavities and the plurality of first sliding parts 54a can lock the plurality of foot rests 3, thereby improving the locking force.

In fig. 1 and 2, the number of the guide cavities is four, and the four guide cavities are connected into a cross shape.

Wherein, when the guide member 53 is plural, it is preferable that the plural guide members 53 are integrally formed. The integrated guide members 53 are structurally sound and enable the simultaneous movement of the slide members 54 within the different guide members 53.

Further, as shown in fig. 1 and 2, the aircraft foot stand locking device further comprises a foot stand support 52, wherein a first end of the foot stand support 52 is fixedly connected with the framework 51, and a second end of the foot stand support 52 is used for being connected with the foot stand 3. The foot rest support 52 facilitates the connection of the foot rest 3 with the framework 51 and also has a bearing effect on the foot rest 3, improving the strength of the locking device.

Specifically, the first end of the foot stand bracket 52 may be connected to the framework 51 by a fastener such as a bolt. The second end of the foot stand support 52 may be hinged to the foot stand by a pin, hinge, or the like.

Preferably, the foot stand support 52 is detachably provided on the framework 51. Specifically, the foot stool support 52 and the framework 51 may be detachably connected by a screw connection manner such as a screw thread, a screw, or a snap connection manner, or may be detachably connected by an interference fit manner. When the foot stool bracket 52 is detachably arranged on the framework 51, the disassembly and the maintenance are convenient.

The number of the foot stool supports 52 can be set according to the number of the foot stools 3, and can be one or more. Preferably, the foot rest supports 52 are arranged in one-to-one correspondence with the foot rests 3, and as shown in fig. 1, the foot rest supports 52 and the foot rests 3 are four in number.

Preferably, as shown in fig. 1 and 2, a locking groove 52a is formed on the stand support 52, and the guide member 53 is locked in the locking groove 52 a. The clamping groove 52a is convenient and quick for fixing the guide component 53 on the foot rest support 52, and after the guide component is clamped in the clamping groove 52a, the guide component 53 does not protrude out of the foot rest support 52 too much, so that the arrangement space is saved.

The engaging groove 52a may be a groove with various shapes, as long as the guiding component 53 can be fixed by matching with the end of the guiding component 53. As shown in fig. 2, the first end of the guide member 53 is rectangular, and the engaging groove 52a is U-shaped.

Wherein, the framework 51 can be a hollow structure, and the foot rest support 52 is fixedly connected on the outer wall of the framework 51. The framework 51 has the function of convenient installation, that is, the aircraft foot stand locking device is installed on the framework 51, the framework 51 is fixedly installed with the fuselage of the aircraft, and meanwhile, the foot stand 3 of the aircraft is installed on the foot stand bracket 52 in the aircraft foot stand locking device.

The shape of the skeleton 51 may be triangular, rectangular, circular, polygonal (the number of sides is more than four, such as pentagonal, hexagonal, etc.). In the embodiment shown in fig. 2, the framework 51 is rectangular, and four foot stand supports 52 are fixed to four corners of the framework 51.

The invention also provides an aircraft comprising a foot prop 3 and an aircraft foot prop locking device according to the invention, as shown in fig. 1.

Due to the fact that the aircraft foot stand locking device provided by the invention is installed on the aircraft, after the foot stand 3 is unfolded, the aircraft foot stand locking device can lock the foot stand 3, the foot stand 3 is prevented from shaking in the flying process, the driving safety is improved, and the quality of shot images is guaranteed.

In addition, the aircraft can also comprise a fuselage, a horn, a foot rest 3, an aircraft control system and an aircraft foot rest locking device according to the invention, wherein the horn is arranged at the upper part of the fuselage, the foot rest 3 is arranged at the lower part of the fuselage, a framework 51 is fixed on the fuselage, and the foot rest 3 is rotatably connected with the fuselage through a foot rest bracket 52. The rotor 55 or motor 57 may be connected to an aircraft control system.

When the motor 57 is connected to an aircraft control system, when the control system detects that the aircraft is started or the foot rest 3 is opened, the driving motor 57 is driven to drive, the motor 57 drives the rotating member 55 to rotate through the driving gear 56, the guide groove 55a on the rotating member 55 rotates along with the rotating member 55, because the first end of the sliding member 54 is embedded in the guide groove 55a, and the sliding member 54 is constrained by the guide member 53, the sliding member 54 can only pop out outwards along the extending direction of the guide member 53, namely the radial direction of the rotating member 55, so as to abut against the foot rest 3, and exert an outward thrust on the foot rest 3, so that the foot rest 3 (see the foot rest 3 on the left side of fig. 1) is locked, the foot rest 3 is prevented from vibrating in the flying process, and the.

Preferably, a groove (not shown) is formed at a position of the foot rest 3 opposite to the sliding member 54, and a first end of the sliding member 54 is engaged in the groove. The embodiment not only fixes the sliding component 54 and prevents the sliding component from sliding accidentally, but also enlarges the contact area of the sliding component and the foot rest 3 into the area of the inner wall of the groove after the first end of the sliding component is clamped into the groove, thereby improving the locking force between the sliding component 54 and the foot rest 3 and preventing the foot rest 3 from shaking.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aircraft foot stool locking device is characterized by comprising a framework (51), wherein the framework (51) is used for being connected with a foot stool (3); a sliding assembly (54) is arranged on the framework (51), a first end of the sliding assembly (54) is arranged opposite to the foot rest (3), a second end of the sliding assembly (54) is connected with a driving assembly, and the driving assembly is used for driving the sliding assembly (54) to move towards the foot rest (3) so that the first end of the sliding assembly (54) is outwards pressed against the foot rest (3);

the drive assembly is including setting up rotate piece (55) in skeleton (51), be equipped with guide way (55a) on rotating piece (55), the first end of guide way (55a) is close to the axis of rotation of rotating piece (55), the second end of guide way (55a) is kept away from the axis of rotation of rotating piece (55), the second end embedding of slip subassembly (54) in guide way (55a) and can follow under the drive of rotating piece (55) the extending direction of guide way (55a) slides.

2. Aircraft foot prop locking device according to claim 1, characterized in that the guide slot (55a) is arc-shaped.

3. Aircraft foot prop locking device according to claim 1, characterized in that the turning piece (55) is a gear wheel, the guide groove (55a) being provided on an end face of the gear wheel.

4. An aircraft foot prop locking device according to claim 3, characterized in that the drive assembly further comprises an electric motor (57) and a drive gear (56), the electric motor (57) driving the drive gear (56), the drive gear (56) causing the rotation member (55) to rotate about the axis of rotation.

5. Aircraft foot prop locking device according to any one of claims 1 to 4, characterized in that the sliding assembly (54) comprises a first (54a) and a second (54b) slide connected in an L-shape, the first slide (54a) being arranged towards the foot prop (3) and the second slide (54b) being embedded in the guide slot (55 a).

6. Aircraft foot prop locking device according to claim 5, characterized in that the first slider (54a) is formed in one piece with the second slider (54 b).

7. An aircraft foot stool locking device according to claim 5, characterized by further comprising a guide assembly (53) fixedly arranged on the framework (51), wherein the guide assembly (53) is provided with a guide cavity, the first sliding piece (54a) is arranged in the guide cavity in a penetrating mode, the first sliding piece (54a) can move along the extension direction of the guide cavity and extends out of the guide cavity, and the second sliding piece (54b) extends out of the guide cavity.

8. Aircraft foot prop locking device according to claim 7, characterized in that the guiding cavities and the first sliding member (54a) are each provided in plurality, the plurality of guiding cavities and the first sliding member (54a) being arranged in a one-to-one correspondence.

9. An aircraft foot prop locking device according to claim 7, characterized in that it further comprises a foot prop bracket (52), a first end of the foot prop bracket (52) being fixedly connected to the framework (51), a second end of the foot prop bracket (52) being adapted to be connected to a foot prop (3).

10. Aircraft foot prop locking device according to claim 9, characterized in that the foot prop support (52) is provided with a catch (52a), the guide member (53) being snapped into the catch (52 a).

11. An aircraft, characterized in that it comprises a foot prop (3) and an aircraft foot prop locking device according to any one of claims 1-10.

12. The aircraft according to claim 11, characterized in that the foot rest (3) is provided, opposite the sliding assembly (54), with a groove in which a first end of the sliding assembly (54) is snapped in.