阅读说明：本技术 一种多旋翼飞行器 (Multi-rotor aircraft ) 是由 缪顺文 于 2020-12-31 设计创作，主要内容包括：本发明涉及一种多旋翼飞行器,属于飞行设备技术领域。该多旋翼飞行器包括机身,机身的形状为长条形,并且机身包括机头和机尾；第一臂组、第二臂组和第三臂组,第一臂组、第二臂组以及第三臂组均由两根对称设置在机身两侧的机臂组成,第一臂组位于机身的顶端,第二臂组位于机身的底部靠近机头的位置,第三臂组位于机身的底部靠近机尾的位置；旋翼系统,每根机臂上均安装有旋翼系统,第一臂组上的旋翼系统位于第二臂组的旋翼系统以及第三臂组的旋翼系统的上方。通过上述结构,本实施例提供的多旋翼飞行器中能够安装旋翼的空间则更大,因此可安装更多的旋翼,因此其总升力以及旋翼效率均更高,旋翼布置也更加灵活。(The invention relates to a multi-rotor aircraft, and belongs to the technical field of flight equipment. The multi-rotor aircraft comprises an airframe, wherein the airframe is in a strip shape and comprises a nose and a tail; the robot comprises a first arm group, a second arm group and a third arm group, wherein the first arm group, the second arm group and the third arm group are respectively composed of two symmetrical machine arms arranged on two sides of a machine body; and the rotor system is arranged on each horn, and the rotor system on the first arm group is positioned above the rotor system of the second arm group and the rotor system of the third arm group. Through above-mentioned structure, the space that can install the rotor among the many rotor crafts that this embodiment provided is then bigger, consequently can install more rotors, and consequently its total lift and rotor efficiency are all higher, and the rotor is arranged also more in a flexible way.)

1. A multi-rotor aircraft, comprising:

the machine body is in a strip shape and comprises a machine head and a machine tail;

the robot comprises a first arm group, a second arm group and a third arm group, wherein the first arm group, the second arm group and the third arm group are respectively composed of two machine arms symmetrically arranged on two sides of a machine body, the first arm group is positioned at the top end of the machine body, the second arm group is positioned at the position, close to the machine head, of the bottom of the machine body, and the third arm group is positioned at the position, close to the machine tail, of the bottom of the machine body;

a rotor system, each said horn having said rotor system mounted thereon, and said rotor system on said first armset being positioned above said rotor system of said second armset and said rotor system of said third armset.

2. A multi-rotor aerial vehicle as recited in claim 1, further comprising:

the cargo hold is arranged at the bottom end of the machine body.

3. A multi-rotor aerial vehicle according to claim 1 wherein:

each of the machine arms is rotatably mounted on the machine body through a hinge structure, the rotation direction of the machine arm of the first arm group is in a vertical plane, and the rotation directions of the machine arm of the second arm group and the machine arm of the third arm group are in a horizontal plane;

and each machine arm is detachably fixed on the machine body through one locking structure.

4. The multi-rotor aircraft according to claim 3, wherein the hinge structure comprises a hinge base and a hinge shaft, the hinge base is fixedly arranged on the fuselage, the hinge shaft passes through one end of the horn and is inserted into the hinge base in a rotating manner, and the rotor system is arranged at the other end of the horn;

the locking structure comprises a lock rod and a lock block, one end of the lock rod is rotatably connected to the middle part of the machine arm, the other end of the lock rod is provided with a lock hole, and the lock block is fixedly arranged on the machine body;

when the locking structure locks the machine arm on the machine body, the locking block is buckled in the locking hole.

5. A multi-rotor aerial vehicle according to claim 1 wherein: still include the rotor and vert the mechanism, at least on the first armset the rotor system passes through the rotor verts the mechanism and rotates and install on the horn of first armset.

6. A multi-rotor aerial vehicle according to claim 1 wherein: and the lifting support below the horn is arranged on the horn of the second arm group and the horn of the third arm group.

7. A multi-rotor aerial vehicle according to any one of claims 1-6, wherein: first armset second armset with the quantity of third armset all is a set of, the top surface of fuselage is for certainly the aircraft nose extends to the tail just arches up first linear curved surface, first armset is located the top of first linear curved surface.

8. A multi-rotor aerial vehicle according to any one of claims 1-6, wherein: the quantity of first armset is two sets of, the second armset with the quantity of third armset all is a set of, the top surface of fuselage is for certainly the aircraft nose extends to tail and the second linear curved surface of arching up, four of fuselage unilateral the horn is located same trapezoidal four summits respectively.

9. A multi-rotor aerial vehicle according to any one of claims 1-6, wherein: the number of the first arm groups is three, the number of the second arm groups and the number of the third arm groups are both one, the top surface of the machine body is a third linear curved surface which extends from the machine head to the machine tail and is arched upwards, one group of the first arm groups are positioned at the top of the third linear curved surface, and the other two groups of the first arm groups are respectively positioned at two sides of the top of the third linear curved surface.

10. A multi-rotor aerial vehicle according to any one of claims 1-6, wherein: the quantity of first armset is two sets of, the second armset with the quantity of third armset all is a set of, the top surface of fuselage is for certainly the aircraft nose extends to the aircraft tail and the face of buckling of hunch up, four of fuselage unilateral the horn is located four summits of same quadrangle respectively.

Technical Field

The invention belongs to the technical field of flight equipment, and particularly relates to a multi-rotor aircraft.

Background

Many rotor unmanned aerial vehicle is because simple structure, and the operation is reliable, and cost economy has become low latitude freight transportation at present, especially the main power model of short distance low latitude freight transportation, to the unmanned aerial vehicle that has six above rotors, the rotor is on the fuselage structural configuration the good or bad general lift and the rotor efficiency that have directly decided whole aircraft.

At present, a plurality of rotors all adopt the overall arrangement on the fuselage along equidistant range all around in a plane usually, also all rotors are installed on the same aspect of fuselage, because the volume of space of the same aspect of fuselage is limited, consequently there is the inverse relation between the quantity of rotor installation axle and the rotor size, when needing to install more rotors, the rotor size just needs corresponding reduction, otherwise just need increase the whole size of aircraft, so the installation quantity and the flexibility of arrangement of rotor system then receive the restriction, so that the performance of aircraft can not promote.

Disclosure of Invention

The invention provides a multi-rotor aircraft, which is used for solving the technical problem that the installation quantity and the arrangement flexibility of rotor systems of the multi-rotor aircraft with six or more than six arms are limited in the prior art.

The invention is realized by the following technical scheme: a multi-rotor aircraft comprising:

the machine body is in a strip shape and comprises a machine head and a machine tail;

the robot comprises a first arm group, a second arm group and a third arm group, wherein the first arm group, the second arm group and the third arm group are respectively composed of two machine arms symmetrically arranged on two sides of a machine body, the first arm group is positioned at the top end of the machine body, the second arm group is positioned at the position, close to the machine head, of the bottom of the machine body, and the third arm group is positioned at the position, close to the machine tail, of the bottom of the machine body;

a rotor system, each of the rotor systems mounted on the horn, and the rotor system on the first armset being located above the rotor system of the second armset and the rotor system of the third armset.

Further, in order to better implement the present invention, a cargo compartment is provided at the bottom end of the fuselage.

Further, in order to better implement the present invention, each of the booms is rotatably mounted on the body through a hinge structure, the rotation direction of the booms of the first arm group is in a vertical plane, and the rotation directions of the booms of the second arm group and the booms of the third arm group are in a horizontal plane;

and each machine arm is detachably fixed on the machine body through one locking structure.

Further, in order to better implement the invention, the hinge structure comprises a hinge seat and a hinge shaft, the hinge seat is fixedly arranged on the machine body, the hinge shaft penetrates through one end of the machine arm and then is inserted into the hinge seat in a rotating mode, and the rotor system is arranged at the other end of the machine arm;

the locking structure comprises a lock rod and a lock block, one end of the lock rod is rotatably connected to the middle part of the machine arm, the other end of the lock rod is provided with a lock hole, and the lock block is fixedly arranged on the machine body;

when the locking structure locks the machine arm on the machine body, the locking block is buckled in the locking hole.

Further, in order to better implement the invention, the invention further comprises a rotor tilting mechanism, and the rotor system on at least the first arm group is rotatably installed on the machine arm of the first arm group through the rotor tilting mechanism.

Further, in order to better implement the present invention, a lift bracket located below the horn is mounted on each of the horn of the second arm group and the horn of the third arm group.

Further, in order to better implement the present invention, the first arm set, the second arm set and the third arm set are all in one set, the top surface of the fuselage is a first linear curved surface extending from the nose to the tail and arching upwards, and the first arm set is located at the top of the first linear curved surface.

Furthermore, in order to better realize the invention, the number of the first arm groups is two, the number of the second arm groups and the number of the third arm groups are both one, the top surface of the machine body is a second linear curved surface which extends from the machine head to the machine tail and is arched upwards, and the four machine arms on one side of the machine body are respectively positioned on four vertexes of the same trapezoid.

Further, in order to better implement the present invention, the number of the first arm groups is three, the number of the second arm groups and the number of the third arm groups are both one, and the top surface of the body is a third linear curved surface extending from the nose to the tail and arched upward, wherein one of the first arm groups is located on the top of the third linear curved surface, and the other two first arm groups are respectively located on two sides of the top of the third linear curved surface.

Furthermore, in order to better implement the present invention, the number of the first arm groups is two, the number of the second arm groups and the number of the third arm groups are both one, the top surface of the machine body is a bending surface extending from the machine head to the machine tail and upwardly arched, and the four machine arms on one side of the machine body are respectively located on four vertexes of the same quadrangle.

Compared with the prior art, the invention has the following beneficial effects:

the invention provides a multi-rotor aircraft which comprises an aircraft body, a first arm group, a second arm group, a third arm group and a rotor system, wherein the aircraft body is in a long strip shape, the aircraft body comprises an aircraft nose and an aircraft tail, the first arm group, the second arm group and the third arm group are respectively composed of two aircraft arms symmetrically arranged on two sides of the aircraft body, the first arm group is positioned at the top end of the aircraft body, the second arm group is positioned at the bottom of the aircraft body and close to the aircraft nose, the third arm group is positioned at the bottom of the aircraft body and close to the aircraft tail, and the rotor system is arranged on each aircraft arm. Through the structure, the multi-rotor aircraft provided by the invention has larger space for installing the rotors, compared with the prior art, under the condition of the same fuselage size and the same rotor size, the multi-rotor aircraft provided by the embodiment can be provided with more rotors, the number of the rotors is increased, the total lift force and the rotor efficiency of the multi-rotor aircraft can be enhanced, the arrangement of the rotors is more flexible, in other words, when the number and the size of the installed rotors are the same, the fuselage of the multi-rotor aircraft provided by the embodiment can be made smaller, so that the structure is more compact, in addition, after the distance between the rotors on one side of the fuselage is increased, the arrangement of the cabin door can be facilitated, the rotors on the first arm group are positioned above the gravity center of the whole multi-rotor aircraft, so that the self-stabilizing effect of the multi-rotor aircraft during flying is better, and, rotor size on the first armset can be made bigger than the rotor of second armset and third armset, like this, can further promote flight stability, reinforcing rotor efficiency and total lift to because the rotor of first armset is liftoff higher, thereby effectively reduces the ground effect when taking off or descending.

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, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic structural view of a multi-rotor aircraft of the present application;

FIG. 2 is a partially enlarged view of region A in FIG. 1;

FIG. 3 is an exploded view of a multi-rotor aircraft of the present application;

fig. 4 is a partially enlarged view of the region B in fig. 3;

fig. 5 is a schematic structural diagram of the present application when the number of the first arm set, the second arm set and the third arm set mounted on the fuselage is one;

fig. 6 is a schematic structural diagram of the present application when two first arm sets, two second arm sets and one third arm set are mounted on the fuselage (the top surface of the fuselage is a second linear curved surface);

fig. 7 is a schematic structural diagram of the present application when two sets of first arms, two sets of second arms, and one set of third arms are mounted on the fuselage (the top surface of the fuselage is a bending surface);

fig. 8 is a schematic structural diagram of the present application when three sets of first arm sets, two sets of second arm sets, and three sets of third arm sets are mounted on the fuselage.

In the figure:

1-a fuselage; 11-a machine head; 12-machine tail;

2-a first armset;

3-a second armset;

4-a third armset;

5-a rotor system;

6-cargo hold;

7-a hinge structure; 71-a hinged seat; 72-an articulated shaft;

8-a locking structure; 81-locking bar; 82-a locking block;

9-rotor tilt mechanism; 91-a tooth holder; 92-round bar; 93-a turning block; 94-a rotating electrical machine;

10-lifting support.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the examples given herein without any inventive step, are within the scope of the present invention.

Example 1:

the embodiment provides a multi-rotor aircraft, which is used for solving the technical problem that the installation quantity and the arrangement flexibility of rotor systems of the multi-rotor aircraft with six or more than six rotors are limited in the prior art. Specifically, in the prior art, there are three rotor installation methods for a multi-rotor aircraft having six or more rotors, the first is that all rotors are installed on the top of the fuselage, the second is that all rotors are installed in the middle of the fuselage, and the third is that all rotors are installed on the bottom of the fuselage, and regardless of which installation method, all rotors are installed on the same plane of the fuselage, because the volume of the space around the same plane of the fuselage is limited, i.e. the installation space size of the rotor system is limited, so that the number of rotor systems and the size of the rotors are in an inverse relationship, if the number of rotors is more, the size of the rotors needs to be smaller, if the size of the rotors is larger, the number of rotors that can be installed is correspondingly reduced, otherwise, interference between adjacent rotors cannot normally operate, and the other method is to increase the size of the fuselage, but this causes a problem of an increase in the weight of the body.

The multi-rotor aircraft provided by the embodiment comprises a fuselage 1, a first arm group 2, a second arm group 3, a third arm group 4 and a rotor system 5, wherein the overall shape of the fuselage 1 is long strip-shaped, the fuselage 1 comprises a nose 11 and a tail 12, specifically, the overall shape of the fuselage 1 is long strip-shaped and flat, more specifically, the nose 11 and the tail 12 are arranged at two ends of the length direction of the fuselage 1, the length of a connecting line between the nose 11 and the tail 12 is greater than the length of a perpendicular line between a top point on the fuselage 1 and the nose 11 and the tail 12, and in addition, the connecting line between the top point on the fuselage 1 and the nose 11 and the tail 12 is at least greater than 60% of the width of the fuselage 1.

The first arm set 2, the second arm set 3, and the third arm set 4 are each composed of two symmetric arms disposed on two sides of the fuselage 1, and each arm is provided with a rotor system 5, it is noted that in this embodiment, each arm can be provided with one rotor system 5, so that the number of rotor systems 5 of the multi-rotor aircraft provided in this embodiment is six, and certainly, each arm can also be provided with two rotor systems 5 one above the other, at this time, the number of rotor systems 5 of the multi-rotor aircraft provided in this embodiment is twelve, so as to obtain better lift force and improve load-carrying capacity, and therefore the multi-rotor aircraft provided in this embodiment is actually an aircraft having at least six rotor systems 5. In addition, the rotor system on first armset 2 is located above the rotor system of second armset 3 and the rotor system of third armset 3

In this embodiment, the first arm set 2 is located at the top end of the body 1, and most preferably, the first arm set 2 is located at the top end of the body 1 at a position not close to the nose 11 or the tail 12, the second arm set 3 is located at the bottom of the body 1 at a position close to the nose 11, and the third arm set 4 is located at the bottom of the body 1 at a position close to the tail 12. With this arrangement, among the plurality of arms located on one side of the fuselage 1, the wings of the second arm group 3 and the third arm group 4 are located on the same layer (bottom) of the fuselage 1, but the arms of the second arm group 3 are located near the nose 11, the arms of the third arm group 4 are located near the tail 12, the distance between the arms of the second arm group 3 and the arms of the third arm group 4 is large, and the arms of the first arm group 2 are located at the top end of the fuselage 1, at this time, the arms of the first arm group 2 and the arms of the second arm group 3/the third arm group 4 are not on the same layer, so that the distance between the arms of the first arm group 2 and the arms of the second arm group 3 is large. Furthermore, the rotors of rotor system 5 in second armset 3 and third armset 4 are positioned at a lower altitude than the rotors of rotor system 5 in first armset 2.

Through above-mentioned structure, on the many rotor crafts that this embodiment provided, the space that can install the rotor is then bigger, compares with prior art, under the condition of 1 size in the same fuselage and the same rotor size, the many rotor crafts that this embodiment provided then can install more rotors, and the rotor quantity increases, then can so that its total lift and rotor efficiency all can strengthen. In other words, the fuselage 1 of the multi-rotor aircraft provided by the present embodiment can be made smaller, making the structure more compact, when the number and size of the rotors installed are the same. In addition, the arrangement of the doors can be facilitated after the distance between the respective rotors on the one side of the body 1 is increased. The rotor on first armset 2 is located on the focus of whole many rotor crafts to make the self-stabilization effect when the many rotor crafts that this embodiment provided fly better. In the present embodiment, the size of the rotor on the first arm set 2 is larger than that of the second arm set 3 and the third arm set 4, so that the flight stability, the rotor efficiency and the total lift can be further improved, and the ground effect during taking off or landing can be effectively reduced because the rotor of the first arm set 2 is higher off the ground. In addition, in this embodiment, the length of the connection line between the arm of the second arm group 3 and the arm of the third arm group 4 is greater than the length of the perpendicular line between the arm of the first arm group 2 and the connection line, and the length of the perpendicular line between the arm of the first arm group 2 and the connection line is greater than sixty percent of the width of the fuselage 1.

As an embodiment of this embodiment, the multi-rotor aircraft in this embodiment further includes rotor controllers, wherein the rotor system 5 on the first arm group 2 is electrically connected to one rotor controller, the rotor system 5 on the second arm group 3 and the rotor system 5 on the third arm group 4 are electrically connected to the other rotor controller, so that the rotor at the top end of the fuselage 1 and the rotor at the bottom of the fuselage 1 are separately controlled by the two rotor controllers, which can improve flight safety. As another embodiment of the present embodiment, the rotor system 5 on the first arm set 2, the rotor system 5 on the second arm set 3, and the rotor system 5 on the third arm set 4 in the present embodiment are electrically connected to a rotor controller. It should be noted that the rotor controller in this embodiment is the same as the rotor craft in the prior art, which is taken as the prior art, and therefore, detailed description thereof is omitted here.

As a more preferable embodiment of the present embodiment, in the present embodiment, the cargo hold 6 is provided at the bottom end of the body 1, and specifically, the cargo hold 6 is mounted on the bottom end of the body 1, or the cargo hold 6 is welded to the bottom end of the body 1, so as to facilitate the transportation of cargo. Hatches may be provided on the side walls of the cargo compartment 6. As another embodiment of the present embodiment, the cargo compartment 6 in the present embodiment may also be disposed inside the fuselage 1 and located at the middle rear portion of the fuselage 1.

As a more preferable embodiment of the present embodiment, in the present embodiment, each horn is rotatably installed on the fuselage 1 through a hinge structure 7, and the rotation direction of the horn of the first arm group 2 is in a vertical plane, the rotation directions of the horn of the second arm group 3 and the horn of the third arm group 4 are in a horizontal plane, and a locking structure 8 is further provided between each horn and the fuselage 1, when a flight is required, each horn is unfolded and locked on the fuselage 1 by using the locking structure 8, when the multi-rotor aircraft needs to be transported by using a truck or other transportation tools, the locking structure 8 is unlocked, and the horn of the first arm group 2 is folded downward, so that the horns of the first arm group 2 and the second arm group 3 are folded toward the middle, thereby facilitating transportation. In addition, in the present embodiment, the positional relationship among the first arm group 2, the second arm group 3, and the third arm group 4 is such that the three arm groups have a sufficient space therebetween for the folding of the horn. It is worth noting that when the locking structure 8 is locked, the arms of the first arm set 2 are inclined upwards, the arms of the second arm set 3 are inclined towards the front of the multi-rotor aircraft, and the arms of the third arm set 4 are inclined towards the rear of the multi-rotor aircraft, so as to leave a wider space between each other.

As a specific embodiment of this embodiment, the hinge structure 7 in this embodiment includes a hinge seat 71 and a hinge shaft 72, wherein the hinge seat 71 is welded or screwed to the fuselage 1, the hinge shaft 72 passes through one end of the fuselage and is inserted into the hinge seat 71 in a rotating manner, so that the fuselage is rotatably connected to the fuselage 1, the rotor system 5 includes a motor and a rotor driven by the motor, and the motor of the rotor system 5 is installed at the other end of the fuselage and the rotor is located above the fuselage. The locking structure 8 in this embodiment includes a locking rod 81 and a locking block 82, one end of the locking rod 81 is rotatably connected to the middle of the horn, the other end of the locking rod 81 is provided with a locking hole, the locking block 82 is welded or integrally formed on the machine body 1, the locking block 82 is buckled in the locking hole during locking, and at this time, the relative position between the horn and the machine body 1 can be locked by utilizing the connection effect of the locking rod 81. The hinge structure 7 and the locking structure 8 have the advantages of simple structure and light weight.

As a more specific implementation manner of this embodiment, the hinge seat 71 in this embodiment is a channel steel, the hinge shaft 72 is a pin, the notch of the channel steel corresponding to the first arm set 2 faces downward, the horn of the first arm set 2 is inserted into the notch of the channel steel of the first arm set 2 and can rotate therein, the notch of the channel steel corresponding to the second arm set 3 faces the rear of the body 1, the horn of the second arm set 3 is inserted into the notch of the channel steel of the second arm set 3 and can rotate therein, the notch of the channel steel corresponding to the third arm set 4 faces the front of the body 1, and the horn of the third arm set 4 is inserted into the notch of the channel steel of the third arm set 4 and can rotate therein. The pin then passes the lateral wall of channel-section steel and the one end of horn to realize that the horn articulates on fuselage 1.

As a more preferred embodiment of the present embodiment, in the present embodiment, at least the rotor system 5 on the first armset 2 is rotatably mounted on the horn of the first armset 2 by the rotor tilt mechanism 9. Preferably, rotor system 5 on first arm set 2 is pivotally mounted to the horn of first arm set 2 by rotor tilt mechanism 9, rotor system 5 on second arm set 3 is pivotally mounted to the horn of second arm set 3 by another rotor tilt mechanism 9, and rotor system 5 on third arm set 4 is pivotally mounted to the horn of third arm set 4 by another rotor tilt mechanism 9. At this time, the rotor on the second arm group 3 and the rotor on the third arm group 4 can be tilted by a certain angle, so that the aircraft provided by the present embodiment can implement motions/flights such as pitching and pitching, but it should be noted that when the rotor on the second arm group 3 and the rotor on the third arm group 4 are driven by the corresponding rotor tilting mechanisms 9 to be located in the horizontal plane and above the corresponding arms, the rotor on the second arm group 3 and the rotor on the third arm group 4 can provide lift force by rotation. Of course, it is also possible to provide only a rotor tilt structure between the rotor of the first armset 2 and the horn of the first armset 2. Adopt above-mentioned structure, then can be so that the many rotor crafts that this embodiment provided can be applicable to multiple different scenes, for example when descending on the surface of water, then can incline and realize going on the surface of water through rotor tilting mechanism 9 drive rotor. In addition, in the present embodiment, the positional relationship between the first arm group 2, the second arm group 3, and the third arm group 4 is such that the three arm groups have sufficient space between each other to facilitate rotor tilting.

In a preferred embodiment of the present invention, a buoyant ball is mounted in the lower portion of the fuselage 1 or in the cargo hold 6 and the second arm group 3 and the third arm group 4, so that the multi-rotor aircraft provided in the present embodiment can float on the water surface. It should be noted that in the present embodiment, the rotor of the first armset 2 can be rotated to be horizontal (i.e. the rotor of the first armset 2 rotates in a horizontal plane) or to be vertical (i.e. rotates in a vertical plane) under the driving of the rotor tilting mechanism 9, and when the rotor of the first armset 2 is rotated to rotate in a vertical plane, the outer edge of the rotor of the first armset 2 is higher than the bottom end of the fuselage 1 or the cargo hold 6.

Due to the effect of the buoyancy ball, when the aircraft provided by the embodiment lands on the water surface, the rotor on the first arm group 2 is driven by the corresponding rotor tilting mechanism 9 to rotate downwards to be vertical, so that the rotor on the first arm group 2 can rotate in a vertical plane, and the aircraft provided by the embodiment can run on the water surface. And, the many rotor crafts that this embodiment provided have two kinds of states at least, first state, rotor on the first armset 2 is in rotor tilting mechanism 9's effect and is changeed to the level and be located the top of first armset 2, and at this moment, the rotor on the first armset 2 is rotatory then can provide lift, and the second state, rotor on the first armset 2 is changeed to vertical under rotor tilting mechanism 9's effect, and at this moment, the rotor on the first armset 2 is rotatory then can provide the power that traveles on the surface of water for the aircraft that this embodiment provided. Compare with the aircraft that can stop in the surface of water among the prior art, the aircraft that this embodiment provided not only can stop at the surface of water, can also travel on the surface of water, and its practicality is stronger to solve many rotor unmanned aerial vehicle among the prior art and can not go the technical problem on the surface of water.

As a specific embodiment of this embodiment, the rotor tilting mechanism 9 in this embodiment includes a tooth holder 91, a round bar 92, a rotating block 93, and a rotating motor 94, the tooth holder 91 is fixed on the upper surface of the other end of the horn, and the tooth slot of the tooth holder 91 faces upward, the rotating block 93 is inserted into the tooth slot, the rotating motor 94 is installed on the horn, the round bar 92 is keyed on the rotating block 93, and the round bar 92 is rotatably inserted into the slot wall of the tooth slot, the power output end of the rotating motor 94 is connected to the round bar 92 through a coupling, and the motor of the rotor system 5 is installed on the rotating block 93, so that when the motor is operated, the rotating block 93 and the rotor system 5 thereon can be driven to rotate/tilt relative to the horn.

In this embodiment, as a more preferable embodiment, the lift bracket 10 located below the arm is mounted to the arm of the second arm group 3 and the arm of the third arm group 4 by screws, and it should be noted that the lift bracket 10 in this embodiment is actually a single rod, and the bottom end of the lift bracket 10 is lower than the bottom end of the fuselage 1/the bottom end of the cargo hold 6. When the multi-rotor aircraft provided in this embodiment lands on the ground, landing gear 10 overlaps the ground to facilitate smooth takeoff and landing of the multi-rotor aircraft. The drop-off stand 10 of this embodiment has the advantages of simpler structure and lighter weight compared to the prior art. Further, since the horn of the second arm group 3 and the horn of the third arm group 4 are located at a relatively large distance from each other, the respective landing gear brackets 10 are located at a relatively large distance from each other, and therefore, the plurality of landing gear brackets 10 in the present embodiment can support the fuselage 1 more stably. Compared with the prior art aircraft with the rotor arranged on the top of the fuselage 1, the multi-rotor aircraft provided by the embodiment does not need to be provided with a special undercarriage, so that the structure of the multi-rotor aircraft is more simplified. Preferably, the landing gear support 10 of this embodiment may also be provided with a buoyancy ball, so as to increase the buoyancy of the multi-rotor aircraft provided in this embodiment in water.

As an embodiment of the present embodiment, the first arm set 2, the second arm set 3 and the third arm set 4 in the present embodiment are all one set, and the top surface of the body 1 is a first linear curved surface extending from the nose 11 to the tail 12 and arched upward, that is, the top surface of the body 1 is an arched surface, and the first arm set 2 is located on the top of the first linear curved surface. In this configuration, the three arms on one side of the fuselage 1 are located at the three vertices of the same triangle. In the multi-rotor aircraft with the structure, the distance between three wings on one side of the aircraft body 1 is large, the space around the arms of the first arm group 2 is large, and rotors with larger sizes can be installed.

As another embodiment of this embodiment, the number of the first arm sets 2 in this embodiment is two, the number of the second arm sets 3 and the number of the third arm sets 4 are both one, the top surface of the body 1 is a second linear curved surface extending from the nose 11 to the tail 12 and arching upward, at this time, the four arms on one side of the body 1 are respectively located on four vertexes of the same trapezoid, and the trapezoid is a trapezoid with the upper base located above the lower base, and most preferably, the trapezoid is an isosceles trapezoid with a small top and a large bottom. In this embodiment, the rotor mounted on the top surface of the fuselage 1 (the rotor of the first armset 2) may be the same size as the rotors mounted on the second armset 3 and the third armset 4.

As another embodiment of this embodiment, the number of the first arm groups 2 in this embodiment is three, the number of the second arm groups 3 and the number of the third arm groups 4 are both one, the top surface of the body 1 is a third linear curved surface extending from the head 11 to the tail 12 and arching upward, one of the first arm groups 2 is located at the top of the third linear curved surface, the other two first arm groups 2 are located at two sides of the top of the third linear curved surface, and at this time, five arms on one side of the body 1 are located at five vertexes of the same pentagon.

As another embodiment of this embodiment, the number of the first arm sets 2 in this embodiment is two, the number of the second arm sets 3 and the number of the third arm sets 4 are both one, the top surface of the body 1 is a bending surface extending from the nose 11 to the tail 12 and arching upward, the two first arm sets 2 are respectively located at bending nodes of the bending surface, and in this structure, four arms on one side of the body 1 are respectively located at four vertices of the same quadrangle.

The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.