WO2018040765A1

WO2018040765A1 - Aircraft with replaceable protective cover

Info

Publication number: WO2018040765A1
Application number: PCT/CN2017/093215
Authority: WO
Inventors: 恽为民; 叶鹏; 庞作伟
Original assignee: 上海未来伙伴机器人有限公司
Priority date: 2016-08-30
Filing date: 2017-07-17
Publication date: 2018-03-08
Also published as: CN106335635A

Abstract

Disclosed is an aircraft with a replaceable protective cover, comprising an aircraft body (1), wherein the aircraft body (1) has a duct (2), the duct (2) is internally provided with a propeller (4), a plurality of clamping grooves (21) are provided between an end face and an inner wall of the duct (2), and a plurality of clamping keys (51) are provided at an outer edge of a circular cover body (5) in a matching manner; and each clamping key (51) matches and is embedded into the corresponding clamping groove (21), and the circular cover body is fixed, via the clamping grooves, between the duct and the surface of the aircraft body, such that the assembly and disassembly of the circular cover body can be realized only by the rotation of the circular cover body while the propeller in the duct is protected.

Description

Aircraft with replaceable shield

Technical field

The invention discloses an aircraft, in particular to an aircraft with a replaceable shield.

Background technique

The protective net of the aircraft is mainly used to protect the spiral propeller. During the operation, the high-speed rotation is prevented from harming the personnel. Therefore, the protective net has a very important meaning.

Some of the UAVs in the prior art, the flying propellers have no protection measures, and cannot provide effective protection for flight safety.

The invention application of the application No. 201010220017.X discloses a small electric ducted propeller type intelligent unmanned aerial vehicle. The aircraft consists of a ducted enclosure, a bracket, a coaxial reverse propeller, a fairing, a battery, a motor, a drive control circuit, and a microcontroller. The appearance of the body is dish-shaped, and the ducted enclosure is added outside the rotor, which eliminates the flight safety threat caused by the exposure of the traditional structure rotor and increases the working efficiency of the propeller; the aircraft uses a coaxial reversing double-rotor design, which does not need The tail rotor is set to offset the inertia rotation of the fuselage, saving material and expanding the running space; the propeller is driven by the motor, and the motor is servo-controlled by the drive control circuit; the horizontal movement of the aircraft in the air is made by the deflectable deflector below the propeller. Cooperate with. In addition, there are multi-directional convenient slots in the duct enclosure of the aircraft for installation and replacement of various sensors at any time. The microcontroller comprehensively processes the feedback information of each sensor and performs autonomous flight control according to the task. The specific disclosed structure does not include protective measures, resulting in special conditions in the flight may cause damage to the propeller.

In part, even if there is a UAV with a protective net, by adding a lower guard net with a fan-shaped incompleteness, it is also integrated with the arm, which is not convenient to replace.

The other part of the aircraft protection net is mostly integrated with the fuselage or fixed, and it will be difficult to repair once damaged in flight. Moreover, the flight protection net has a great influence on the airflow, and the bonded protective net can not be conveniently replaced according to the use situation or the modeling requirements.

Therefore, there is a lack of a shield in the prior art that can effectively protect the blades in the duct of the aircraft and facilitate replacement.

Summary of the invention

In view of the above-mentioned deficiencies of the prior art, the technical problem to be solved by the present invention is to provide an aircraft with a replaceable shield, comprising: a fuselage having a duct, wherein the duct is provided with a propeller, Wherein, a plurality of card slots are arranged between the end surface of the duct and the inner wall, and the outer edges of a circular shell match There are a plurality of card keys; each of the card keys is fitted to one of the card slots.

Preferably, the card slot comprises: an access slot extending in an inner wall of the duct to communicate with the end surface of the duct; and a locking groove formed in an inner wall of the duct and communicating perpendicularly with the inlet slot.

Preferably, the width of the access slot is greater than the width of the card key, and the card key is embedded in the locking slot.

Preferably, the inner wall of the locking groove and the outer side wall of the card have corrugated protrusions.

Preferably, an annular recess is defined between the end surface of the duct and the inner wall, and the plurality of the slots are equally spaced between the outer sidewall of the annular recess and the end surface of the duct.

Preferably, the circular cover comprises: a protective net fixed in the fixing ring, and the plurality of the keys are equidistantly disposed on an outer edge of the fixing ring.

Preferably, the protective net is a strip spherical net, and the concave surface of the strip spherical net faces the duct.

Preferably, the airframe is in the shape of a disk, and the plurality of ducts are provided, and each of the ducts runs through the fuselage, and both openings of the duct are covered with the circular shell.

Preferably, the card slot has six, six of the card slots are equidistantly disposed; and the matching card keys have six.

Preferably, the strip spherical net comprises: a plurality of purlins, and the horizontal projection of each of the purlins is on a concentric circle centered on the axis of the fuselage.

Compared with the prior art, the aircraft of the replaceable shield of the present invention effectively solves the problem of lacking a structurally strong and easily replaceable protective cover in the prior art, and through the card slot pair between the ducted surface and the surface of the fuselage The circular cover is fixed. While protecting the propeller in the duct, the circular cover can be disassembled and assembled only by rotating the circular cover, and the operation is very convenient.

The concept, the specific structure and the technical effects of the present invention will be further described in conjunction with the accompanying drawings in order to fully understand the objects, features and effects of the invention.

DRAWINGS

Figure 1 is a schematic view of the structure of the present invention;

Figure 2 is a schematic view showing the structure of the unmounted circular cover of the present invention;

Figure 3 is a cross-sectional view showing the structure of the duct of the present invention;

Figure 4 is a plan view showing the structure of the duct of the present invention;

Figure 5 is a partial enlarged view of the contact portion of the card key and the duct in the present invention;

Figure 6 is a schematic view showing the structure of the circular cover of the present invention installed on the duct;

Figure 7 is a schematic structural view of a circular cover of the present invention;

Figure 8 is a perspective view of the duct of the present invention;

Figure 9 is a schematic structural view of a first embodiment of the circular cover of the present invention;

Figure 10 is a cross-sectional view showing the structure of the first embodiment of the circular cover of the present invention;

Figure 11 is a perspective view showing the first embodiment of the circular cover of the present invention;

Figure 12 is a schematic structural view of a second embodiment of the circular cover of the present invention;

Figure 13 is a cross-sectional view showing the structure of a second embodiment of the circular cover of the present invention;

Figure 14 is a perspective view showing the structure of the second embodiment of the circular cover of the present invention;

Figure 15 is a schematic structural view of a third embodiment of the circular cover of the present invention;

Figure 16 is a cross-sectional view showing the structure of a third embodiment of the circular cover of the present invention;

Figure 17 is a perspective view showing a three-dimensional structure of a third embodiment of the circular cover of the present invention;

Figure 18 is a schematic structural view of a fourth embodiment of the circular cover of the present invention;

Figure 19 is a cross-sectional view showing the structure of a fourth embodiment of the circular cover of the present invention;

Figure 20 is a perspective view showing the structure of the fourth embodiment of the circular cover of the present invention;

Figure 21 is a schematic structural view of a fifth embodiment of the circular cover of the present invention;

Figure 22 is a cross-sectional view showing the structure of a fifth embodiment of the circular cover of the present invention;

Figure 23 is a perspective view showing the structure of a fifth embodiment of the circular cover of the present invention.

detailed description

As shown in the figure, FIG. 1 is a schematic structural view of the present invention, and FIG. 2 is a schematic structural view of the unmounted circular cover of the present invention. The aircraft of the replaceable protective cover includes: a body 1 having a body 1 The duct 2 is provided with a propeller 4 in the duct 2, and the duct 2 is a tubular structure, wherein a plurality of card slots 21 are provided between the end surface of the duct 2 and the inner wall, and the outer edge of a circular shell 5 is matched. a plurality of card keys 51; each of the card keys 51 is fitted into a card slot 21, and the circular cover body 5 is mounted in the card slot 21 by the card key 51. The structure of the card is securely carried out under the premise of ensuring stability. Disassembly and replacement operations.

Further, a pillar is vertically installed in each side wall of the duct 2, and the pillar may adopt a polygonal prism pillar to improve the firmness. The pillar is mounted with the motor 3, and the propeller 4 is mounted on the rotating shaft of the motor 3, and the power of the motor 3 is The wire can pass through the pillar into the fuselage 1. The struts are directed perpendicular to the axis of the fuselage 1, and the propeller 4 is a three-blade propeller 4.

Further, a battery and a control circuit component are installed in the body 1, the battery supplies power to the control circuit component and the motor 3, and the control circuit component controls the motor 3, thereby realizing control of the flight state of the fuselage 1.

Further, the control circuit component comprises: a signal transceiving circuit component, a switch circuit component, a motor control circuit, a main control chip, and the signal transceiving circuit component has a receiving device, and the receiving device is mounted on the casing of the fuselage 1 and can be equipped with a remote controller. The remote controller communicates with the signal transceiving circuit component to realize communication between the remote controller and the aircraft, thereby controlling the aircraft by the remote controller.

Further, the body 1 includes a first casing and a second casing, and a supporting mechanism is disposed between the first casing and the second casing to maintain the rigidity of the body 1.

Further, FIG. 3 is a cross-sectional view showing the structure of the duct of the present invention, and FIG. 4 is a knot of the duct of the present invention. The card slot 21 includes: an access slot that opens on the inner wall of the duct 2 to communicate with the end face of the duct 2; and a locking slot that opens in the inner wall of the duct 2 and communicates with the access slot. In fact, the function of the slot is to connect the culvert. The entry between the end face of the track 2 and the locking groove, the snap key 51 enters the locking groove through the entry groove, and the operation of locking the circular cover 5 in the locking groove is realized.

Further, the width of the entry slot is greater than the width of the card key 51, so that the card key 51 can enter through the slot, the card key 51 enters the process of entering the slot, the card key 51 can be matched with the side wall of the access slot, and the card key 51 is embedded. Locking groove, the width of the locking groove is matched with the thickness of the key 51, and when the key 51 enters through the entry slot and is placed at the bottom of the entry slot, the circular cover 5 is rotated, so that the key 51 is embedded in the locking groove, and the key is inserted The upper and lower side walls of the 51 are statically rubbed against the inner wall of the locking groove, thereby realizing the fixing of the key 51 in the locking groove, and the circular cover 5 is not detached from the locking groove during the operation of the aircraft.

Further, FIG. 5 is a partial enlarged view of the contact portion of the card key 51 and the duct 2 of the present invention, the inner wall of the locking groove and the outer side wall of the card key 51 each have a corrugated protrusion, and the wavy protrusion and the card key of the inner wall of the locking groove The undulating protrusions of the outer side wall of 51 are matched, and the direction of the wavy protrusion is perpendicular to the direction in which the card key 51 enters and exits. Further, the wavy protrusion is added to further increase the firmness of the fixing of the card key 51 in the locking groove. The wavy raised surface can also be made of a matte material to further increase the friction.

Further, FIG. 6 is a schematic structural view of the circular cover body of the present invention installed on the duct. FIG. 8 is a schematic perspective view of the duct of the present invention, and an annular recess 22 is formed between the end surface of the duct 2 and the inner wall. The card slots 21 are equally spaced between the outer side wall of the annular recess 22 and the end surface of the duct 2, and in one embodiment of the present invention, the annular recess 22 is added, and the annular recess 22 is opened in the culvert. Between the end surface of the channel 2 and the inner wall, a recess having a right angle is formed between the end surface of the duct 2 and the inner wall, and the annular recess 22 has a tubular vertical surface perpendicular to the end surface of the duct 2 and is perpendicular to the inner wall of the duct 2 The disc-shaped horizontal surface forms a structure similar to two steps between the end surface of the duct 2 and the inner wall, and the plurality of card slots 21 are disposed on the outer side wall of the annular recess 22, that is, the first quarter step from top to bottom. The vertical portion of the structure is also the portion of the tubular vertical surface; specifically, the card slot 21 includes: an entry slot and a locking slot, a side wall of the locking slot and a surface of the annular recess 22 disposed in the duct 2, that is, a disk shape The horizontal plane is on the same plane, and the other side surface of the locking groove Closer to the end face of the duct 2, so that after the snap key 51 enters the portion where the entry slot communicates with the lock groove, the circular cover 5 abuts against the disc-shaped horizontal plane, and the disc-shaped horizontal plane serves as a limit platform to provide a certain support, and Since the diameter of the circular shape of the card slot 21 is increased, the side edges of the circular cover 5 are placed in the annular recess 22, and the side of the circular cover 5 is disposed on the horizontal surface of the disk instead of the culvert. The air flow of the track 2 exerts any influence, and the effect on the operation of the aircraft is reduced while the stability of the key 51 of the circular cover 5 is increased into the card slot 21.

Further, FIG. 7 is a schematic structural view of the circular cover body of the present invention. The circular cover body 5 includes: a mesh body 52. The mesh body 52 includes: a protective net fixed in the fixing ring, and a plurality of card keys 51 are equidistant Provided on the outer edge of the fixing ring, in the specific production process, the plurality of card keys 51 and the circular cover body 5 can be produced into an integrated structure, thereby increasing the firmness thereof; further, the fixing ring and the protective net Can be taken With integrated structure, the whole mold opening process is carried out to avoid the cracking of parts caused by external force during use.

Further, the protective net is a strip-shaped spherical net, and the concave surface of the strip-shaped spherical net faces the duct 2, and the structure of the strip-shaped spherical net can effectively reduce the air resistance generated by increasing the protective net to provide good protection. effect.

Further, the protection net may have two depressions, the two depressions matching the shape of the human finger, the spacing between the two depressions may be 3-5 cm, and the midpoint of the connection between the two depressions is on the axis of the circular cover 5, thereby It is convenient for the user to rotate the circular cover 5 to remove it.

Further, a removal device may be further included, the removal device includes a concave body matching the shape of the protective mesh, the concave surface of the concave body has a plurality of strip-shaped protrusions of different lengths, and the torsion bar passes through the concave body During use, the concave surface of the concave body faces the circular cover 5, so that the strip-shaped convex portion in the concave surface is embedded in the protective net, and the torsion bar is rotated, and the circular cover 5 can be easily removed.

Further, the fuselage 1 has a disk shape, and there are a plurality of ducts 2, each of which is penetrated through the fuselage 1, and both openings of the duct 2 are covered with a circular cover 5. In general, with the structure of four ducts 2, four ducts 2 are symmetrically distributed on the disk-shaped fuselage 1, and the propellers 4 in the four ducts 2 provide a stable thrust so that the fuselage 1 can fly up, and By adjusting the rotational speed of the four propellers 4, other action operations in the air are realized.

Further, there are six card slots 21, and the six card slots 21 are equidistantly disposed; matching, the card keys 51 have six, and the structure of the six card slots 21 and the card keys 51 ensures that the annular cover body is in the duct 2 Fixed stability on the top.

Further, in the specific implementation process of the present invention, the protective mesh of different mesh structures may be covered in the two openings of the duct 2, and since the two openings of the duct 2 are respectively responsible for the intake and the outflow, the aerodynamic characteristics thereof are Differently, the air inlet is relatively less affected, and the air outlet and the airflow are concentrated to generate thrust. Therefore, different structures have different effects on the thrust of the aircraft. The following embodiments use different mesh structures for different situations:

9 is a schematic structural view of a first embodiment of a circular cover of the present invention, FIG. 10 is a schematic cross-sectional view showing a first embodiment of the circular cover of the present invention, and FIG. 11 is an implementation of the circular cover of the present invention. In the first embodiment of the present invention, in the first embodiment of the present invention, the strip-shaped spherical network of the mesh body 52 includes: a plurality of purlins, and the horizontal projection of each of the purlins is at the axis of the fuselage 1 The line is a concentric circle of the center of the circle. The structure has a great influence on the aerodynamic force. If the number of the rafters is large, the turbulence may be caused, especially at the air outlet. Therefore, the mesh cover at the air outlet uses a radial rafter. The purlins adopt a square cross section. Referring to the design of similar baffles, the number of roots is reasonably distributed to minimize the influence of airflow.

Figure 12 is a schematic structural view of a second embodiment of the circular cover of the present invention, Figure 13 is a schematic cross-sectional view showing a second embodiment of the circular cover of the present invention, and Figure 14 is a perspective view of the circular cover of the present invention. A schematic diagram of the three-dimensional structure of the second embodiment. In the second embodiment of the present invention, the mesh body 52 is made of a radial strip. With a square cross section, there is a strength reinforcement ring in the middle.

Figure 15 is a schematic structural view of a third embodiment of the circular cover of the present invention, Figure 16 is a schematic cross-sectional view showing a third embodiment of the circular cover of the present invention, and Figure 17 is a perspective view of the circular cover of the present invention. A three-dimensional structural diagram of the third embodiment. In the third embodiment of the present invention, the mesh body 52 is made of a radial beam, the stringer has a circular cross section, and the middle portion has a strength reinforcing ring.

Figure 18 is a schematic structural view of a fourth embodiment of the circular cover of the present invention, Figure 19 is a schematic cross-sectional view showing a fourth embodiment of the circular cover of the present invention, and Figure 20 is an embodiment of the circular cover of the present invention. In a fourth embodiment of the present invention, the mesh body 52 is a radial beam, the stringer has a circular cross section, and the middle portion has a strength reinforcing ring, and the shape matches the shape of the outer surface of the body 1. .

Figure 21 is a schematic structural view of a fifth embodiment of the circular cover of the present invention, Figure 22 is a schematic cross-sectional view showing a fifth embodiment of the circular cover of the present invention, and Figure 23 is a perspective view of the circular cover of the present invention. In the fifth embodiment of the present invention, in the fifth embodiment of the present invention, the mesh body 52 adopts a radial beam, and the stringer adopts a circular cross section. Compared with the fourth embodiment, the middle reinforcing ring is removed to increase the number of the stringers. .

Further, the cross-sectional shape of the beam has a large influence on the aerodynamic force. It has been verified that the cross section of the same feature size has a square section resistance of about 1/3 of that of the circular section, and therefore, in all embodiments of the present invention, A cross section of a cross section can be used.

Further, the cross-sectional dimension of the purlin also has a certain influence on the purlin. The excessive size has an excessive influence on the airflow, reduces the efficiency of the aircraft, and the size is too small and the strength is weak. Therefore, in all the embodiments of the present invention, the purlin The cross-sectional feature size can be selected between 1.2 and 1.5 mm.

Further, the protective net can also adopt a plurality of different mesh structures, and different protective nets can be adopted according to different environmental requirements. If the environment is relatively bad, a protective net with a dense mesh structure can be adopted.

The above has described in detail the preferred embodiments of the invention. It will be appreciated that many modifications and variations can be made in the present invention without departing from the scope of the invention. Therefore, any technical solution that can be obtained by a person skilled in the art based on the prior art based on the prior art by logic analysis, reasoning or limited experimentation should be within the scope of protection determined by the claims.

Claims

An aircraft with a replaceable shield includes: a fuselage having a duct, wherein the duct is provided with a propeller, wherein a plurality of end faces and an inner wall of the duct are provided The card slot, the outer edge of a circular cover is matched with a plurality of card keys; each of the card keys is matched to be embedded in the card slot.
The aircraft according to claim 1, wherein the card slot comprises: an access slot formed in an inner wall of the duct to communicate with the end surface of the duct; and an inner wall of the duct and the access slot Vertically connected locking slots.
The aircraft of claim 2 wherein said inlet slot has a width greater than a width of said snap key and said snap key is embedded in said locking slot.
The aircraft according to claim 3, wherein said locking groove inner wall and said snap outer wall have corrugated projections.
The aircraft according to claim 1, wherein an annular recess is formed between the end surface of the duct and the inner wall, and the plurality of the slots are equidistantly formed on the outer side wall of the annular recess and the culvert Between the end faces of the road.
The aircraft according to claim 1, wherein said circular cover comprises: a protective net fixed in the fixing ring, and said plurality of said keys are equidistantly disposed on an outer edge of said fixed ring.
The aircraft of claim 6 wherein said protective mesh is a strip of spherical mesh, said concave surface of said strip of spherical mesh facing said duct.
The aircraft according to claim 1, wherein the fuselage has a disk shape, and the plurality of ducts are plural, each of the ducts penetrating the fuselage, and both openings of the duct are Covered with the circular cover.
The aircraft according to claim 1, wherein said card slot has six, six said card slots are equidistantly disposed; and wherein said card keys are six.
The aircraft according to claim 6, wherein said strip-shaped spherical net comprises: a plurality of purlins, each of said purlins having a horizontal projection of a concentric circle centered on said body axis on.