CN106915431B - Framework mechanism of aircraft and aircraft - Google Patents

Abstract

The invention discloses a framework mechanism of an aircraft and the aircraft, comprising: the first framework body is provided with a hollow cavity and a side wall surrounding the hollow cavity, and the side wall is provided with a horn installation seat close to the top surface of the first framework body; the second framework body is connected to the bottom surface of the first framework body and covers the opening of the hollow cavity on the bottom surface of the first framework body; a third frame connected to a bottom surface of the second frame, and having a leg mounting seat formed at a side edge thereof; and a fourth frame connected to a bottom surface of the third frame, and a housing mounting seat formed on a side edge of the fourth frame. The invention realizes the integration of the horn, the foot rest, the control device and the aircraft shell, and when the aircraft is not used, the horn and the foot rest can be recovered to the inside of the shell and close to the framework mechanism, thereby avoiding the breakage of the horn and the foot rest caused by accidents.

Description

Framework mechanism of aircraft and aircraft

Technical Field

The invention relates to an aircraft manufacturing technology, in particular to a framework mechanism of an aircraft and the aircraft adopting the framework mechanism of the aircraft.

Background

At present, an aircraft or an unmanned aerial vehicle is widely applied to social life, close-range observation is carried out on places where people are difficult to reach, or overhead shooting is carried out, and convenience is provided for observation and shooting.

The existing aircraft is often composed of an aircraft body and a horn extending outwards from the aircraft body, wherein the outer end part of the horn is provided with a motor and a propeller so as to drive the aircraft to fly, and the lower part of the aircraft is also provided with a foot rest so as to facilitate landing of the aircraft.

However, in the existing aircraft, the extended arms and the foot rests are fixedly connected with the fuselage, and after the aircraft is used, the arms are expanded greatly, so that the aircraft has high requirements on storage space.

Therefore, it has become an important research direction to design an aircraft that is easy to store when not in use. Meanwhile, in order to realize such an aircraft, for example, a framework mechanism of the aircraft, an arm locking driving mechanism of the aircraft, which enables the arm of the aircraft to be unfolded and retracted, an arm of the aircraft, and a foot stool driving mechanism of the aircraft, which enables the foot stool of the aircraft to be unfolded and retracted, need to be newly developed.

Disclosure of Invention

In view of the above, the present invention provides a framework mechanism of an aircraft and an aircraft using the framework mechanism, so as to integrate a horn, a foot rest, a control device, and a housing.

The technical scheme of the invention is realized as follows:

a backbone mechanism for an aircraft, the backbone mechanism comprising:

the first framework body is provided with a hollow cavity and a side wall surrounding the hollow cavity, and the side wall is provided with a horn installation seat close to the top surface of the first framework body;

the second framework body is connected to the bottom surface of the first framework body and covers an opening of the hollow cavity on the bottom surface of the first framework body;

a third frame connected to a bottom surface of the second frame, and having a leg mounting seat formed at a side edge thereof;

and a fourth frame connected to a bottom surface of the third frame, and having a housing mounting seat formed on a side edge thereof.

Further, a pan/tilt head mount is further formed on the bottom surface of the third skeleton body, and an opening region exposing the pan/tilt head mount is further formed on the fourth skeleton body.

Further, the horn installation base includes a first projection formed on the side wall of the first skeleton body, and the first projection is formed with a first installation hole for fixing a horn base.

Further, a second bump flush with the bottom surface of the first framework is formed on the side wall of the first framework, a second mounting hole is formed in the surface of the second bump flush with the bottom surface of the first framework, a third mounting hole corresponding to the second mounting hole is formed in the top surface of the second framework, and the second framework is connected to the bottom surface of the first framework through a first connecting piece penetrating through the second mounting hole and the third mounting hole.

Further, a convex column is arranged on the bottom surface of the second framework body, a sleeve capable of accommodating the convex column is arranged on the top surface of the third framework body, and a second connecting piece for fixing the convex column in the sleeve by the third framework body is connected to the bottom surface of the second framework body.

Further, the foot stool mount includes a recess formed at a side edge of the third skeleton body, and a mounting post formed at the recess for fixing the foot stool and the foot stool driving mechanism.

Furthermore, a boss is arranged on the bottom surface of the third framework body, a fourth mounting hole corresponding to the boss is arranged on the top surface of the fourth framework body, and the fourth framework body is connected to the bottom surface of the third framework body through a third connecting piece which penetrates through the fourth mounting hole and is fixed on the boss.

An aircraft, characterized in that the aircraft employs a skeleton mechanism as described in any one of the above.

According to the framework mechanism of the aircraft, the horn, the foot rest, the controller device in the aircraft and the aircraft shell are integrated to form a unified whole, the framework mechanism of the aircraft also realizes the protection of the controller device in the aircraft, and when the horn and the foot rest are recovered into the shell, the framework mechanism can be close to the framework mechanism, so that the space occupied by the aircraft is reduced, and the aircraft with the reduced occupied space can avoid the damage of the horn and the foot rest caused by accidents under the condition that the aircraft is not used.

Drawings

FIG. 1 is a schematic illustration of an aircraft according to an embodiment of the present invention after receiving a horn and a foot rest;

FIG. 2 is a schematic illustration of the configuration of an embodiment of the aircraft of the present invention after deployment of the horn and foot rest;

FIG. 3 is a schematic view of the structure of FIG. 2 with the peripheral wall and bottom cover removed;

FIG. 4 is a schematic structural diagram of a skeleton mechanism according to an embodiment of the present invention;

fig. 5 is a schematic structural diagram of a first skeleton body in an embodiment of the present invention.

Fig. 6A is a three-dimensional structure of a second skeleton body in an embodiment of the present invention;

fig. 6B is a top view of a second skeleton body in the embodiment of the present invention;

fig. 6C is a bottom view of the second skeleton body in the embodiment of the present invention;

fig. 7A is a three-dimensional structure of a third skeleton body in an embodiment of the present invention;

fig. 7B is a top view of a third skeleton body in the embodiment of the present invention;

fig. 7C is a bottom view of the third skeleton body in the embodiment of the present invention;

fig. 8 is a schematic structural view of the framework mechanism provided with the foot stool driving mechanism in the embodiment of the invention;

fig. 9A is a three-dimensional structure of a fourth skeleton body in an embodiment of the present invention;

fig. 9B is a top view of a fourth skeleton body in the embodiment of the present invention;

fig. 9C is a bottom view of a fourth skeleton body according to an embodiment of the present invention;

fig. 10A is a structural sectional view of a horn unlock drive mechanism in the embodiment of the invention;

FIG. 10B is an enlarged view of the structure of the area A in FIG. 10A;

FIG. 11 is a perspective view of a turntable structure of the arm release drive mechanism in an embodiment of the present invention;

FIG. 12 is a bottom view of the turntable structure of the arm release drive mechanism in an embodiment of the present invention;

FIG. 13 is a perspective view of an adapter ring in an embodiment of the invention;

FIG. 14 is a top view of an embodiment of the engagement ring of the present invention;

FIG. 15 is a schematic perspective view of a horn according to an embodiment of the present invention;

FIG. 16 is a cross-sectional view of a horn in an embodiment of the present invention;

FIG. 17 is an enlarged view of the structure of area B in FIG. 16;

fig. 18 is a schematic structural view of a foot stool driving mechanism of an aircraft in an embodiment of the invention.

Fig. 19 is a schematic structural view of a foot rest of an aircraft according to an embodiment of the invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and examples.

The embodiment of the invention provides an aircraft capable of accommodating a horn and a foot stool. The aircraft has the advantages that the aircraft arms and the foot rests are unfolded to carry out flying operation and landing support when the aircraft is used, the aircraft arms and the foot rests are stored in the shell of the aircraft arms when the aircraft is not used, the whole shell, the arm covering plate and the foot rest covering plate exposed outside after the aircraft arms and the foot rests are stored form an ellipsoid shape together, internal equipment of the aircraft, the aircraft arms and the foot rests are protected when the aircraft is not used, the aircraft stored with the aircraft arms and the foot rests is convenient to place, and the space for placing the aircraft is saved.

In the present invention, an embodiment of an aircraft specifically housing a horn and a foot rest is shown in fig. 1, fig. 2 shows an embodiment of the aircraft with the horn and the foot rest deployed, and fig. 3 shows an embodiment of the aircraft with a peripheral wall and a bottom cover of a housing removed from fig. 2. It should be noted that fig. 2 and 3 only show a structure in which one horn and one foot rest are deployed, and in practice, all the horns and foot rests are deployed for use.

Referring also to fig. 1 to 3, the aircraft of the embodiment of the present invention includes a framework 1, a casing 2, a horn 3, a foot rest 4, a horn cover plate 31, and a foot rest cover plate 41.

The shell 2 is fixedly installed on the framework 1, the shell 2 is provided with an outer envelope surface in a closed curved surface shape, and the shell 2 is provided with a first opening groove 21 and a second opening groove 22. The horn 13 is rotatably mounted to the frame 1 at the first opening slot 21, and the horn 13 has a first degree of freedom extending from the first opening slot 21 to the outside of the housing 2 or retracting to the inside of the housing 2. The foot rest 4 is rotatably mounted to the framework 1 at the second opening slot 22, and the foot rest 4 has a second degree of freedom extending from the second opening slot 22 to the outside of the housing 2 or retracting to the inside of the housing 2.

The horn cover plate 31 is fixedly mounted on a side of the horn 3 facing away from the inside of the housing 2, and the horn cover plate 31 has a shape that closes the first open groove 21 along the outer envelope surface when the horn 3 is retracted into the housing 2. The foot rest cover plate 41 is fixedly installed on a side of the foot rest 4 facing away from the inside of the housing 2, and the foot rest cover plate 41 has a shape that can close the second open groove 22 along the outer envelope surface when the foot rest 4 is retracted inside the housing 2.

When the arm and the foot rest 4 of the machine 3 are retracted into the shell 2, the outer curved surface of the arm covering plate 31 and the outer curved surface of the foot rest covering plate 41 are spliced with the outer curved surface of the shell 2 to form a closed curved shell. Wherein, closed curved surface shape is the ellipsoid form, and this kind of shape can obtain the effect to the protection of aircraft internal plant and horn, foot rest when not using the aircraft, also is convenient for to accomodating placing of the aircraft behind horn and the foot rest, saves the space of placing of aircraft, and in addition, this kind of shape can also reduce the air current impact that the aircraft received on the lateral direction to reduce the emergence probability of turning on one's side.

In the embodiment of the present invention, the horn 3 and the foot rest 4 both extend and retract at an angle varying with respect to the major axis of the ellipsoid (as indicated by the imaginary axis Z in fig. 1, 2 and 3).

With continuing reference to fig. 1, 2, and 3, in the embodiment of the present invention, the installation position of the horn 3 on the framework 1 and the installation position of the foot rest 4 on the framework 1 are disposed on opposite sides of the long axis direction of the ellipsoid. As shown in fig. 2, 3, the horn 3 is disposed in an upper portion of the imaginary line axis Z in the mounting position of the frame 1, and the foot stand 4 is disposed in a lower portion of the imaginary line axis Z in the mounting position of the frame 1. That is, the horn 3 is arranged in the upper part of the ellipsoidal vehicle in the mounted position of the skeleton 1, and the foot rest 4 is arranged in the lower part of the ellipsoidal vehicle in the mounted position of the skeleton 1. In addition, the position of the center of gravity of the aircraft in the long axis direction of the ellipsoid is closer to the mounting position of the foot rest 4 on the framework 1, that is, the position of the center of gravity of the aircraft in the long axis direction of the ellipsoid is relatively far away from the mounting position of the horn 3 on the framework 1, so as to reduce the probability of the aircraft rolling over.

In the present invention, the ellipsoidal shape has a first minor axis length at a mounting position of the frame 1 near the horn 3, the ellipsoidal shape has a second minor axis length at a mounting position of the frame 1 near the foot rest 4, and the first minor axis length is greater than the second minor axis length. That is, in the present invention, the ellipsoidal flying device has a large top and a small bottom, and the radian of the top is smaller than that of the bottom, and the top is shaped like an egg with a downward tip, and the area of the cross section of the installation position of the horn 3 is larger than that of the cross section of the installation position of the foot rest 4.

In the present invention, the number of the horn 3 and the first opening groove 21, and the number of the foot rest 4 and the second opening groove 22 are plural. The plurality of horn 2 and the plurality of foot rest 3 are alternately arranged in a direction around the major axis of the ellipsoid, and the plurality of first open grooves 21 and the plurality of second notches 22 are alternately arranged in a direction around the major axis of the ellipsoid. Further, the plurality of horn 3, the plurality of foot rests 4, the plurality of first open grooves 21, and the plurality of second notches 22 are all distributed equiangularly in a direction around the major axis of the ellipsoid. Further, the number of the horn 3 is the same as that of the foot rest 4, and the number of the first opening grooves 21 is the same as that of the first opening grooves 21. Further, in the embodiment of the present invention, the number of the horn 3, the foot rest 4, the first opening groove 21, and the second opening groove 22 is four.

With continued reference to fig. 1, 2 and 3, the housing 2 includes a top cover 23, an engagement ring 24, a peripheral wall 25 and a bottom cover 26. Wherein the peripheral wall 25 has an upper opening and a lower opening, the top cover 23 is spliced with the peripheral wall 25 at the upper opening by the adapter ring 24, the bottom cover 26 is spliced with the peripheral wall 25 at the lower opening, and the first opening groove 21 and the second opening groove 22 are opened in the peripheral wall 25.

In an embodiment of the present invention, the bottom cover 26 includes an openable and closable cover plate (not shown). The cover plate is used to expose a head mounted in the aircraft inside the casing 2.

In the embodiment of the invention, the aircraft further comprises a control assembly and a battery. The framework 1 is of a hollow structure and is provided with an accommodating space for accommodating the control assembly and the battery, and the battery and the control assembly are both arranged in the accommodating space of the framework. In addition, the other end of the horn 3, remote from the end where the frame is mounted, is mounted with a motor 5 with a propeller (not shown in the figure). The control assembly is electrically connected to the motor to control rotation of the propeller. The battery is used for supplying power to the control assembly and the motor. When the horn 3 is in the deployed state, the motor 5 faces downward, and then drives the rotation of the propeller thereon, generating downward thrust, and further propelling the ascent and flight of the aircraft.

When the aircraft is not used, the whole shell and the arm covering plate and the foot rest covering plate exposed after the arm and the foot rest are received form an ellipsoid together, so that internal equipment of the aircraft, the arm and the foot rest are protected when the aircraft is not used, the aircraft with the arm and the foot rest received is convenient to place, and the space for placing the aircraft is saved.

Fig. 4 shows the structure of the framework mechanism used in the aircraft of the invention. The skeleton mechanism comprises a first skeleton 11, a second skeleton 12, a third skeleton 13 and a fourth skeleton 14, and the skeleton 1 is formed by the first skeleton 11, the second skeleton 12, the third skeleton 13 and the fourth skeleton 14.

Fig. 5 shows a schematic structural view of the first skeleton body 11 in the skeleton mechanism of the present invention. As shown in fig. 5, the first frame 11 has a hollow cavity 111 and a sidewall 112 surrounding the hollow cavity 111, and the sidewall 112 is formed with a horn installation seat 113 near a top surface of the first frame 11. The horn installation base 113 includes a plurality of first protrusions 1131 formed on the side wall 112 of the first framework 11, the first protrusions 1131 are formed with first installation holes 1132 for fixing the horn base 32, the horn base 32 is fixed to the horn installation base 113 through fixing members penetrating through the first installation holes 1132, and the horn base 32 is further installed on a framework mechanism of an aircraft through the horn installation base 113. The horn base 32 is provided with a horn mounting hole, and the horn 3 is mounted on the horn base 32 through the horn mounting hole and is extended and retracted with the axis of the horn mounting hole as an axis. Note that, in fig. 5, only the horn mounting seat 113, the first protrusion 1131 and the first mounting hole 1132 of one of the side walls 112 are marked with symbols, and the other side walls 112 have the same structure. In an embodiment of the present invention, the fixing member is, for example, a bolt or a rivet.

As shown in fig. 5, the main body of the first frame body 11 is a hollow long cylinder shape surrounded by a plurality of side walls 112, and the plurality of side walls 112 have the same width so that the cross section of the main body of the first frame body 1 is a regular polygon. The top surface of the first frame 11 may also serve as another housing mounting point (which may be used to mount the engaging ring 24 of the housing 2 and the upper portion of the peripheral wall 25) in addition to the housing mounting seat 141 of the fourth frame 14 (which is used to mount the bottom cover 26 of the housing 2 and the lower portion of the peripheral wall 25). The side wall 112 of the first frame 11 is a hollow structure, so that the weight of the first frame 11 can be reduced.

Referring to fig. 4, the second frame 12 is connected to the bottom surface of the first frame 11 and covers the opening of the hollow cavity 111 at the bottom surface of the first frame 11.

Fig. 6A shows a three-dimensional structure of the second skeleton body 12, fig. 6B shows a top-view structure of the second skeleton body 12, and fig. 6C shows a bottom-view structure of the second skeleton body 12. As shown in fig. 6A, 6B, 6C, and also fig. 5, the second skeleton body 12 has a top surface facing the first skeleton body 11 and a bottom surface facing away from the first skeleton body 11. Wherein the top surface of the second frame 12 is fixed to the bottom surface of the first frame 11. The plurality of side walls 112 of the first framework body 11 and the second framework body 12 jointly surround a containing cavity forming an aircraft electric control device. The bottom surface of the second skeleton body 12 has a plurality of protruding columns 122.

As shown in fig. 5, 6A and 6B, a plurality of second protrusions 114 flush with the bottom surface of the first skeleton body 11 are formed on the side wall 112 of the first skeleton body 11, second mounting holes 115 are formed on the surface of the second protrusions 114 flush with the bottom surface of the first skeleton body 11, third mounting holes 121 corresponding to the second mounting holes 115 are formed on the top surface of the second skeleton body 12, and the second skeleton body 12 is connected to the bottom surface of the first skeleton body 11 through first connecting members inserted through the second mounting holes 115 and the third mounting holes 121.

As shown in fig. 4, the third frame 13 is connected to the bottom surface of the second frame 12, and a leg mounting seat 131 is formed on a side edge of the third frame 13. Fig. 7A shows a three-dimensional structure of the third skeleton body 13, fig. 7B shows a top-view structure of the third skeleton body 13, and fig. 7C shows a bottom-view structure of the third skeleton body 13. A sleeve 133 capable of accommodating the boss 122 is disposed on the top surface of the third frame 13, and a second connecting member for fixing the boss 122 in the sleeve 133 by the third frame 13 is connected to the bottom surface of the second frame 112, that is, the boss 122 is fixed in the sleeve 133 by the second connecting member, so that the third frame 13 is connected to the bottom surface of the second frame 112.

As shown in fig. 7A and 7B, the foot stool mount 131 includes a recess 1311 formed at a side edge of the third frame body 13, and a mounting post 1312 formed at the recess 1311 for fixing the foot stool 4 and the foot stool driving mechanism 42. Fig. 8 shows the framework mechanism structure after the foot frame driving mechanism 42 is installed.

In the embodiment of the present invention, the protruding column 122 and the sleeve 133 have a relatively high height, so that after the third skeleton body 13 is connected to the second skeleton body 112, a relatively large space is left between the third skeleton body 13 and the second skeleton body 112 to satisfy the installation of the tripod driving mechanism 42.

As shown in fig. 4, the fourth skeleton body 14 is connected to the bottom surface of the third skeleton body 13, and the side edge of the fourth skeleton body 14 is formed with a housing mounting seat 141, the housing mounting seat 141 is used for mounting the bottom cover 26 of the housing 2 and the lower part of the peripheral wall 25, the number of the housing mounting seats 141 is, for example, four, and the distribution is, for example, equiangular distribution in the direction around the long axis of the ellipsoid of the aircraft. Fig. 9A shows a three-dimensional structure of the fourth skeleton body 14, fig. 9B shows a top-view structure of the fourth skeleton body 14, and fig. 9C shows a bottom-view structure of the fourth skeleton body 14.

As shown in fig. 7C, 9A, 9B, and 9C, the third skeleton body 13 is further formed with a pan/tilt mount 132 on a bottom surface thereof, and the fourth skeleton body 14 is further formed with an opening region 142 exposing the pan/tilt mount 132. As shown in fig. 7C and 9B, a boss 134 is disposed on a bottom surface of the third frame 13, a fourth mounting hole 143 corresponding to the boss 134 is disposed on a top surface of the fourth frame 14, and the fourth frame 14 is connected to the bottom surface of the third frame 13 through a third connecting member that is inserted into the fourth mounting hole 143 and fixed to the boss 134.

In the embodiment of the present invention, the number of the side walls 112, the number of the horn mounts 113, the number of the foot stool mounts 131, and the number of the housing mounts 141 are equal, and further, the number of the side walls 112 is four, the number of the horn mounts 113 is four, the number of the foot stool mounts 131 is four, and the number of the housing mounts 141 is four.

The framework mechanism used in the aircraft realizes the integration of the horn, the foot rest, the controller in the aircraft and the aircraft shell to form a unified whole, and the framework mechanism also realizes the protection of the controller in the aircraft, and can be close to the framework mechanism when the horn and the foot rest are recovered into the shell, so that the space occupied by the aircraft is reduced, and the aircraft occupying the reduced space can avoid the breakage of the horn and the foot rest caused by accidents under the condition that the aircraft is not used.

Fig. 10A shows a structural sectional view of the horn unlock drive mechanism in the present invention, and fig. 10B shows a structure which is a region a in fig. 10A, the sectional view showing a deployed state of the horn 13. As shown in fig. 10A and 10B, the aircraft 1 includes a horn 3, and a horn lock mechanism 33, and the horn lock mechanism 33 has a telescopic degree of freedom that can lock and unlock the horn 3 when the horn 3 is extended. In fig. 10A and 10B, the solid-line horn lock mechanism 33 shows a state in which the horn lock mechanism 33 is extended to lock the horn 3, and the broken-line horn lock mechanism 33 shows a state in which the horn lock mechanism 33 is retracted to unlock the horn 3.

As shown in fig. 10A and 10B, the arm unlocking drive mechanism 34 includes a dial 341 and a dial 342. Fig. 11 shows a perspective view of the turntable 342, and fig. 12 shows a bottom view of the turntable 342. In the arm lock release driving mechanism 34, the dial 341 protrudes from the arm lock mechanism 33. The dial 342 is located on the side of the horn lock mechanism 33 where the dial 341 is formed, and the surface of the dial 342 facing the horn lock mechanism 33 has a flange 3421 that contacts the dial 341. Wherein the arm lock mechanism 33 extends and retracts in a radial direction of the turntable 342 (as shown by an arrow in fig. 10B), and the flange 3421 extends with a curvature radius that changes monotonically in a rotational direction of the turntable 34 (as shown in fig. 11 and 12), so that the arm lock mechanism 33 is driven to unlock the arm 3 by adjusting a position of the toggle button 341 in the radial direction.

Referring to fig. 4, 5, 10A and 10B, the horn lock mechanism 33 is mounted to the horn base 32.

In the embodiment of the present invention, the arm lock mechanism 33 receives a return elastic force in the radial direction, the return elastic force drives the arm lock mechanism 33 to move to a position where the arm 3 is locked, and the flange 3421 contacts the toggle 341 on a side resisting the return elastic force, as shown in fig. 10A and 10B. Further, the direction of the return elastic force is toward the outside of the outer shell 2 of the aircraft, the flange 3421 contacts the toggle latch 341 on the side of the toggle latch 341 near the outside of the outer shell 2, and the return elastic force may be applied to the horn lock mechanism 33 by a spring provided in the radial direction. As described above with respect to the aircraft, and as shown in fig. 1 and 2, the aircraft further includes a housing 2, and the housing 2 has a first opening slot 21 for the horn 3 to extend out of the housing 2 or to retract into the housing 2 by swinging. The housing 2 includes a peripheral wall 25 and a top cover 23 rotatable with respect to the peripheral wall 25, the first opening groove 21 is opened in the peripheral wall 25, the arm locking mechanism 33 is fixed at a position corresponding to the first opening groove 21, and the turntable 342 is fixed in the top cover 23. In one embodiment, the turntable 342 may be secured to the top cover 23, and rotation of the turntable 342 may be accomplished by rotating the top cover 23.

Fig. 13 shows a perspective structure of the adapter ring 24, and fig. 14 shows a top view structure of the adapter ring 24. Referring to fig. 1 and 2, since the top cover 23 is engaged with the peripheral wall 25 at the upper opening via the engaging ring 24, the flange 3421 of the rotary disc 342 fixed to the top cover 23 will pass through the engaging ring 24 to contact the toggle 341. In the embodiment of the present invention, a limiting opening 241 is disposed in the connecting ring 24, and the flange 3421 passes through the limiting opening 241, so as to limit the over-rotation of the rotating disc 342 and ensure that the toggle 341 does not disengage from the flange 3421.

In the horn unlocking drive mechanism of the embodiment of the invention, the flange with the monotonically changing curvature radius extending is arranged in the rotation direction of the turntable, the flange contacts the toggle button, and further when the turntable is rotated, the flange pushes the toggle button due to the monotonically changing curvature radius of the flange in the rotation direction of the turntable, so that the toggle button drives the arm locking mechanism to move, and the horn is unlocked. The horn unlocking driving mechanism provided by the embodiment of the invention is simple in structure, realizes the integration with the whole ellipsoidal aircraft integral structure, and can realize the horn unlocking only by rotating the top cover.

Fig. 15 shows the structure of the horn 3 of the aircraft 1, and as shown in fig. 15, in the embodiment of the present invention, the width of the root 36 of the horn 3 mounted on the aircraft frame 1 is smaller than the width of the free end 35 of the horn 3, which can reduce the width of the open slot of the shell 2 on one hand, and also has the effect of line beauty on the other hand. In the embodiment of the present invention, the reason why the free end 35 is wider is that the motor 5 is installed at the free end 35, and the installation space of the motor 5 needs to be reserved. Due to the weight of the motor 5, the unfolded horn 3 will put a large stress on its root 36 after the motor 5 is mounted. Therefore, referring to the schematic cross-sectional view of the horn shown in fig. 16, in the embodiment of the present invention, a reinforcing piece 37 is installed at the root 36 of the horn 3.

Fig. 17 is an enlarged view of a region B in fig. 16, and as shown in fig. 17, the reinforcing sheet 37 includes a first reinforcing wall 371 and a second reinforcing wall 372 that are perpendicular to each other and are integrally formed. Wherein, the first reinforcing wall 371 is disposed on a side of the second reinforcing wall 372 away from the free end 35 of the horn 3, and the first reinforcing wall 371 and the second reinforcing wall 371 are perpendicular to each other. In addition, the second reinforcing wall 372 is notched. The arm covering plate 31 is clipped in the notch by a hook 311 to be fixed on the arm 3.

Referring also to fig. 2, 3, 4, 15, 16 and 17, the root 36 of the horn 3 is mounted to the frame structure of the aircraft by the horn base 32. The horn base 32 is provided with a horn mounting hole, and the horn 3 is mounted on the horn base 32 through the horn mounting hole and is extended and retracted with the axis of the horn mounting hole as an axis.

According to the aircraft horn of the embodiment of the invention, the reinforcing sheet is arranged at the root part of the aircraft horn, so that the bending resistance of the root part of the aircraft horn is increased, the root part of the aircraft horn cannot be damaged when the aircraft horn bears larger stress, the first reinforcing wall and the second reinforcing wall are mutually vertical, the reinforcing effect on the root part of the aircraft horn is maximized, and convenience is provided for the installation of the aircraft horn cover plate 31 at the root part of the aircraft horn due to the opening of the notch.

Fig. 18 shows a foot stool driving mechanism of an aircraft in the present invention. The foot stool driving mechanism 42 includes a steering engine 421 and a gear train 422. Wherein, steering wheel 421 is fixed in the skeleton 1 of aircraft through foot rest mount pad 131. The gear set 422 is installed between the crankshaft of the steering engine 421 and the rotating shaft 43 of the foot rest of the aircraft, so as to control the extension and the recovery of the foot rest 4 under the action of the steering engine 421.

Wherein the gear set 422 includes a first drive gear 4221 and a second drive gear 4222. The first transmission gear 4221 is mounted on a crankshaft of the steering gear 421 to rotate along with the rotation of the crankshaft of the steering gear 421. The second transmission gear 4222 is mounted on the aircraft foot stool rotating shaft 43, and the second transmission gear 4222 is meshed with the first transmission gear 4221, so that the first transmission gear 4221 rotates to drive the second transmission gear 4222 to rotate, and further the foot stool 4 is controlled to extend and retract.

Fig. 19 is a schematic structural view of the foot rest 42 of the present invention, as shown in fig. 19 and fig. 18, the aircraft foot rest rotating shaft 43 is provided with a limiting surface 431, and the second transmission gear 4222 limits the relative rotation between the second transmission gear 4222 and the aircraft foot rest rotating shaft 43 through the limiting surface 431, so that the foot rest 4 can be extended and retracted along with the rotation of the second transmission gear 4222.

As shown in fig. 7A and 7B, the foot stool mounting base 131 includes a mounting post 1312 for fixing the foot stool 4 and the foot stool driving mechanism 42. The steering engine 421 is fixed to the mounting post 1312. The aircraft foot prop 43 is mounted to the mounting post 1312 by a foot prop mount.

In the foot rest driving mechanism of the aircraft, the position of the rotating shaft is kept unchanged when the steering engine stops rotating, so that the unfolding and recycling angles of the foot rest are determined.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.

Claims (8)

1. A backbone mechanism for an aircraft, the backbone mechanism comprising:

a first frame body having a hollow cavity and a sidewall surrounding the hollow cavity, and the sidewall being formed with a horn mounting seat near a top surface of the first frame body, wherein a horn with a horn cover plate is mounted to the horn mounting seat;

the second framework body is connected to the bottom surface of the first framework body and covers an opening of the hollow cavity on the bottom surface of the first framework body;

a third frame connected to a bottom surface of the second frame, and having a foot mount formed at a side edge thereof, wherein a foot with a foot cover plate is mounted to the foot mount;

a fourth skeleton body connected to a bottom surface of the third skeleton body, and a shell mounting seat formed at a side edge of the fourth skeleton body, wherein a shell of the aircraft is fixedly mounted on the shell mounting seat; wherein the content of the first and second substances,

when the horn and the foot rest are retracted into the shell, the horn cover plate and the foot rest cover plate form an outer envelope surface in a closed curved shape.

2. The gimbal mechanism according to claim 1, wherein a pan/tilt mount is further formed on a bottom surface of the third gimbal body, and wherein an opening region exposing the pan/tilt mount is further formed on the fourth gimbal body.

3. The framework mechanism according to claim 1, wherein the horn mount includes a first projection formed at the side wall of the first framework, the first projection being formed with a first mounting hole for fixing a horn base.

4. The framework mechanism according to claim 1, wherein the side wall of the first framework is formed with a second protrusion flush with the bottom surface of the first framework, the second protrusion is formed with a second mounting hole on a surface flush with the bottom surface of the first framework, the top surface of the second framework has a third mounting hole corresponding to the second mounting hole, and the second framework is connected to the bottom surface of the first framework by a first connecting member passing through the second mounting hole and the third mounting hole.

5. The armature mechanism according to claim 1, wherein a bottom surface of the second armature has a boss, a top surface of the third armature has a sleeve in which the boss is received, and a second connecting member of the third armature fixing the boss in the sleeve is connected to a bottom surface of the second armature.

6. The framework mechanism according to claim 1, wherein the foot stool mount includes a recess formed at a side edge of the third framework body, and a mounting post formed at the recess for fixing the foot stool and the foot stool driving mechanism.

7. The framework mechanism of claim 1, wherein a bottom surface of the third framework body is provided with a boss, a top surface of the fourth framework body is provided with a fourth mounting hole corresponding to the boss, and the fourth framework body is connected to the bottom surface of the third framework body through a third connecting piece which is arranged in the fourth mounting hole in a penetrating manner and fixed on the boss.

8. An aircraft, characterized in that the aircraft employs a skeleton mechanism according to any one of claims 1 to 7.

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