阅读说明：本技术 可折叠变构无人机 (Collapsible allosteric unmanned aerial vehicle ) 是由 曾揚洋 桂熙汶 李佳忆 向怀祥 黄卿釤 唐震宇 程彦凯 王相龙 戴家俊 赵君珂 于 2021-10-08 设计创作，主要内容包括：本发明公开了一种可折叠变构无人机,包括机身、可转动安装于机身上的两对机翼、安装于机身头部的前推桨、安装于机身尾部的尾翼以及设置于机翼上的涵道风扇,所述机翼可被驱动转动与机身近似平行形成折叠状态或与机身近似垂直形成展开状态或与机身斜交形成半展开状态；本发明的无人机可依据地势自适应的切换起落模式以及飞行模式,利于适应复杂的地形,能够实现各种应用场景下的稳定飞行,使得操空更加的灵活；而且该结构的机翼折叠时水平收纳至机身两侧,可大大减小整个飞行器的降落占地面积；该结构的无人机其结构较为简单,利于实现轻量化设计,减小能耗,并且利于减小无人机的机身体积,实现高空间利用率。(The invention discloses a foldable reconfigurable unmanned aerial vehicle, which comprises a fuselage, two pairs of wings, a forward propeller, an empennage and a ducted fan, wherein the two pairs of wings are rotatably arranged on the fuselage, the forward propeller is arranged at the head of the fuselage, the empennage is arranged at the tail of the fuselage, and the ducted fan is arranged on the wings; the unmanned aerial vehicle can adaptively switch the landing and landing modes and the flight mode according to the terrain, is favorable for adapting to complex terrain, and can realize stable flight in various application scenes, so that the operation is more flexible; the wings of the structure are horizontally stored to two sides of the aircraft body when being folded, so that the landing floor area of the whole aircraft can be greatly reduced; its structure of the unmanned aerial vehicle of this structure is comparatively simple, does benefit to and realizes lightweight design, reduces the energy consumption to do benefit to and reduce unmanned aerial vehicle's fuselage volume, realize high space utilization.)

1. The utility model provides a collapsible allosteric unmanned aerial vehicle which characterized in that: the aircraft comprises an aircraft body, two pairs of wings which are rotatably arranged on the aircraft body, a forward propeller arranged at the head of the aircraft body, an empennage arranged at the tail of the aircraft body and a ducted fan arranged on the wings, wherein the wings can be driven to rotate to form a folding state approximately parallel to the aircraft body or an unfolding state approximately vertical to the aircraft body or a semi-unfolding state obliquely crossed with the aircraft body.

2. The foldable reconfigurable unmanned aerial vehicle of claim 1, wherein: the aircraft wing comprises thin beams, a main beam, positioning beams, a plurality of supporting plates and a rod head, wherein the thin beams, the main beam and the positioning beams are arranged in parallel, the supporting plates simultaneously penetrate through the beams and are arranged in the length direction of the beams, the rod head is connected to the tail end of each beam, the ducted fan is arranged on the rod head, and when the aircraft wing is in an open state, the thin beams, the main beam and the positioning beams are sequentially arranged from back to front.

3. The foldable reconfigurable unmanned aerial vehicle of claim 1, wherein: the fuselage includes the mainboard body that the level set up and is located the lower plate body of mainboard body below and connects the lower tie-beam between mainboard body and the lower plate body, No. one installation position has been formed between mainboard body and the lower plate body.

4. The foldable reconfigurable unmanned aerial vehicle of claim 1, wherein: the wings are connected with the fuselage through a steering driving piece, and the rotating driving piece can directly drive the wings to horizontally rotate so as to form a folding state or an unfolding state or a semi-unfolding state.

5. The foldable reconfigurable unmanned aerial vehicle of claim 3, wherein: the fuselage still includes the last plate body that the level set up and connects the last tie-beam between mainboard body and last plate body, it is located mainboard body afterbody position top to go up the plate body, it has formed No. two installation positions to go up between plate body and the mainboard body.

6. The foldable reconfigurable unmanned aerial vehicle of claim 5, wherein: the pair of wings positioned on the front side are installed in the first installation position, and the pair of wings positioned on the rear side are installed in the second installation position.

7. The foldable reconfigurable unmanned aerial vehicle of claim 5, wherein: the tail wing comprises a tail wing mounting seat and a tail wing body, the tail wing mounting seat is mounted in the second mounting position, and the tail wing mounting seat extends backwards out of the second mounting position and then is connected with the tail wing body.

8. The foldable reconfigurable unmanned aerial vehicle of claim 2, wherein: the supporting plate is approximately drop-shaped with a wide head and a sharp tail.

Technical Field

The invention relates to the technical field of aircrafts, in particular to a foldable reconfigurable unmanned aerial vehicle.

Background

The unmanned plane is an unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. Unmanned aerial vehicles are widely used in a variety of settings, such as aerial photography, crop monitoring, vegetation protection, self-timer photography, express transportation, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power routing inspection, and movie and television photography.

Existing drones are generally divided into fixed-wing drones and multi-rotor drones, which require longer runways, and both multi-rotor drones and helicopters require larger parking ramps. Their take-off and landing need specific fields, and can not adapt to take-off and landing of more complex terrains such as cities.

Therefore, for solving the above problems, a foldable reconfigurable unmanned aerial vehicle is needed, which can be switched between a fixed-wing unmanned aerial vehicle and a multi-rotor unmanned aerial vehicle in both directions, and which can take off and land in a narrow or complex city.

Disclosure of Invention

In view of the above, the present invention provides a foldable reconfigurable drone that can be switched between a fixed wing drone and a multi-rotor drone in both directions, and that can be adapted to take-off and landing in urban areas on narrower or more complex terrain.

The foldable reconfigurable unmanned aerial vehicle comprises a fuselage, two pairs of wings rotatably mounted on the fuselage, a forward propeller mounted at the head of the fuselage, an empennage mounted at the tail of the fuselage and a ducted fan arranged on the wings, wherein the wings can be driven to rotate to be approximately parallel to the fuselage to form a folded state or approximately perpendicular to the fuselage to form an unfolded state or obliquely crossed with the fuselage to form a semi-unfolded state.

Further, the wing comprises thin beams, main beams and positioning beams which are arranged in parallel, a plurality of supporting plates which simultaneously penetrate through the beams and are arranged along the length direction of the beams, and a rod head which is simultaneously connected to the tail end of each beam, the ducted fan is arranged on the rod head, and when the wing is in an open state, the thin beams, the main beams and the positioning beams are sequentially arranged from back to front.

Further, the fuselage includes the mainboard body that the level set up and is located the lower plate body of mainboard body below and connects in the lower tie-beam between mainboard body and the lower plate body, No. one installation position has been formed between mainboard body and the lower plate body.

Furthermore, the wings are connected with the fuselage through a steering driving piece, and the rotating driving piece can directly drive the wings to horizontally rotate so as to form a folding state or an unfolding state or a semi-unfolding state.

Further, the fuselage still includes the last plate body that the level set up and connects the last tie-beam between mainboard body and last plate body, it is located mainboard body afterbody position top to go up the plate body, No. two installation positions have been formed between last plate body and the mainboard body.

Further, a pair of wings positioned on the front side are installed in the first installation position, and a pair of wings positioned on the rear side are installed in the second installation position.

Furthermore, the empennage comprises an empennage mounting seat and an empennage body, the empennage mounting seat is mounted in the second mounting position, and the empennage mounting seat extends backwards out of the second mounting position and then is connected with the empennage body.

Further, the supporting plate is approximately in a drop shape with a wide head and a sharp tail.

The invention has the beneficial effects that:

the unmanned aerial vehicle can switch the landing mode and the flight mode according to the terrain, is favorable for adapting to complex terrain, can realize stable flight in various application scenes, and has more flexible application range. When the wings of the structure are folded, the wings are horizontally stored to the two sides of the aircraft body, so that the occupied area required by the take-off and landing of the whole aircraft can be greatly reduced. Its structure of unmanned aerial vehicle of this structure is comparatively simple, does benefit to and realizes lightweight design. The mode of switching the flight mode to lift force sources can reduce energy consumption and improve energy utilization efficiency. The size of the unmanned aerial vehicle body is reduced, and high space utilization rate is achieved;

the unmanned aerial vehicle can realize more efficient, faster and more time-saving take-off and landing in a smaller field or a limited space, has stronger take-off condition adaptability, and can basically adapt to take-off and landing in any space or terrain;

unmanned people in the invention can realize free and rapid movement over the ground traffic with urban congestion; and the unmanned aerial vehicle can realize parking and take-off and landing within a single vehicle range equivalent to an outdoor open parking lot.

Drawings

The invention is further described below with reference to the figures and examples.

FIG. 1 is a schematic view of a wing deployment configuration;

FIG. 2 is a schematic view of a wing fold configuration;

FIG. 3 is a schematic view of a semi-deployed configuration of a wing;

FIG. 4 is a schematic view of a wing configuration;

FIG. 5 is a schematic illustration of a fuselage structure;

FIG. 6 is a side view of the structure of FIG. 5;

Detailed Description

As shown in the figures, the present embodiment provides a foldable reconfigurable unmanned aerial vehicle, which includes a fuselage 10, two pairs of wings 20 rotatably mounted on the fuselage, a forward propeller 30 mounted on the head of the fuselage, an empennage 40 mounted on the tail of the fuselage, and a ducted fan 50 disposed on the wings, wherein the wings can be driven to rotate to form a folded state approximately parallel to the fuselage or an unfolded state approximately perpendicular to the fuselage or a half-unfolded state obliquely crossed with the fuselage.

The pair of wings here refers to two paired wings installed on both sides of the fuselage, and the pair of wings are symmetrically arranged on both sides of the fuselage; the approximately parallel meaning is that the wings are parallel to the length direction of the fuselage and are allowed to have deviation of +/-15 degrees, the corresponding approximately perpendicular meaning is that the wings are perpendicular to the length direction of the fuselage and are allowed to have deviation of +/-15 degrees, and the specific relative angle between the wings and the fuselage can be correspondingly adjusted according to the actual working condition;

as shown in fig. 1, the bottom of the fuselage is also connected with a fixed undercarriage 60, a battery is installed inside the fuselage, a brushless motor is installed in the front end of the fuselage to drive the forward propeller to rotate, and the intersection of the central connecting lines of the four ducts of the unmanned aerial vehicle coincides with the mass center of the fuselage, so that attitude adjustment and stability during flight can be ensured;

in fig. 1, the wings are unfolded to form an unfolded state, at the moment, the wings are perpendicular to the fuselage, in this state, the unmanned aerial vehicle is a fixed-wing unmanned aerial vehicle, and forward power is provided through a forward propeller 30 and the unmanned aerial vehicle is required to glide to rise and fall when the unmanned aerial vehicle rises and falls, in fig. 2, the wings are folded to form a corresponding wing folded state, in this state, the unmanned aerial vehicle is in a storage state after landing to reduce the occupied space, in fig. 3, the wings are in a half-unfolded state, at the moment, the wings are distributed in an X shape and are matched with a ducted fan 50 to provide power, so that the unmanned aerial vehicle is converted into a multi-rotor unmanned aerial vehicle which can be used for vertical rising and falling; the unmanned aerial vehicle with the structure can adaptively switch the rising and falling modes and the flight modes according to terrain, is beneficial to adapting to complex terrain, can realize stable flight in various application scenes, and enables the operation to be more flexible; the wings of the structure are horizontally stored to two sides of the aircraft body when being folded, so that the landing floor area of the whole aircraft can be greatly reduced; its structure of the unmanned aerial vehicle of this structure is comparatively simple, does benefit to and realizes lightweight design, reduces the energy consumption to do benefit to and reduce unmanned aerial vehicle's fuselage volume, realize high space utilization.

In this embodiment, the wing 20 includes thin beams 21, main beams 22 and positioning beams 23 arranged in parallel, a plurality of support plates 24 arranged in a row along the length direction of each beam and simultaneously penetrating each beam, and a rod head 25 connected to the end of each beam, and the ducted fan 50 is arranged on the rod head, and in the wing spread state, the thin beams 21, the main beams 22 and the positioning beams 23 are arranged in sequence from back to front. The rear refers to one side of the wing close to the tail of the fuselage, and the front refers to one side of the wing close to the head of the fuselage; as shown in fig. 4, each support plate and each beam body are matched to form a frame of the wing, a skin is wrapped outside the frame to form an outer contour of the wing, three assembly holes are formed in each support plate and used for being matched with the three beams, the diameter of each thin beam 21 is smaller than that of each main beam 22 and each positioning beam 23, the thin beams are located on the rear side of the wing and adapted to the appearance of the wing, and the wing with the structure is beneficial to ensuring the effective structural strength and rigidity of the wing, so that the light-weight design is realized, and the energy consumption is reduced.

In this embodiment, the body 10 includes a main board body 11 horizontally disposed, a lower board body 12 located below the main board body, and a lower connecting beam 13 connected between the main board body and the lower board body, and a first installation location 14 is formed between the main board body and the lower board body. As shown in fig. 3 and 5, the lower connecting beam 13 is provided with four lower connecting beams which are arranged in four corners, the lower board body 12 is smaller than the main board body, so that the main board body extends backwards to the rear side of the lower board body 12 to form a similar cantilever structure, at the moment, the lower board body is connected with an inclined strut 18 which is supported at the cantilever position of the main board body, a fixed undercarriage is connected to the bottom of the lower board body 12, a battery, a flight control panel, a circuit original, a GPS system, a forward propeller brushless motor and the like are all placed in a first installation position, the integrated installation of each part of the unmanned aerial vehicle is facilitated through the arrangement of the first installation position, the unmanned aerial vehicle is more flexibly controlled by using the positioning function of the GPS, the rotating speed of each propeller is adjusted according to the height and longitude and latitude of the GPS positioning information, so as to achieve the purpose of fixed-point hovering, and the unmanned aerial vehicle can work more efficiently during the work such as surveying and mapping;

in this embodiment, the wings 20 are connected to the fuselage 10 by a steering driving member 26, which directly drives the wings to rotate horizontally to form a folded state or an unfolded state or a semi-unfolded state. The steering driving piece 26 adopts a steering engine, and the corresponding speed of wing driving is improved by a direct connection structure of the steering engine; during takeoff, the four steering engines start to work after receiving electric signals of the control panel, and the wings are transformed into an unfolded state or a semi-unfolded state when being folded; vertical take-off and landing is then achieved by four ducted fans, or gliding take-off is achieved by forward propellers 30.

In this embodiment, the fuselage 10 still includes the last plate body 15 of level setting and connects the last tie-beam 16 between the mainboard body and last plate body, go up plate body 15 and be located mainboard body 11 afterbody position top, No. two installation positions 17 have been formed between last plate body 15 and the mainboard body 11. The upper connecting beams 16 are four and arranged in four corners, the main plate body, the upper plate body and the lower plate body are made of carbon fiber plates, the thickness of each carbon fiber plate is not more than 3mm, and the strength is calculated to be enough for placing unmanned aerial vehicle accessories and the like; the lower connecting beam 13 and the upper connecting beam 16 both adopt copper columns with the diameter of about 5mm, the unmanned aerial vehicle body is also provided with a shell, each plate body is wrapped in the shell, the appearance of the shell of the unmanned aerial vehicle body adopts a streamline design, the wind resistance can be effectively reduced, the resistance consumption of the unmanned aerial vehicle is reduced, and the cruising ability can be guaranteed; its simple structure of unmanned aerial vehicle of this structure, light in weight, span is steerable about 1000mm under the expansion state, and the fuselage length is steerable about 600mm, and the width of fuselage is steerable about 260mm under fold condition, does benefit to and reduces unmanned aerial vehicle's volume, realizes long-time continuation of the journey, and suits the flight of complicated topography.

In this embodiment, the pair of wings on the front side are installed in the first installation site 14, and the pair of wings on the rear side are installed in the second installation site 17. Referring to fig. 6, steering actuators are respectively installed on the left side and the right side in the first installation position 14, and steering actuators are respectively installed on the left side and the right side in the second installation position 17, so that the installation stability of each wing can be guaranteed through the arrangement of the two installation positions.

In this embodiment, the tail 40 includes a tail mounting seat 41 and a tail body 42, the tail mounting seat is mounted in the second mounting position 17, and the tail mounting seat extends backward beyond the second mounting position 17 and is connected to the tail body 42. As shown in fig. 6, the tail mounting seat 41 is fixed on the main plate body, the tail of the tail mounting seat 41 is provided with a mounting hole, and the tail body 42 is mounted in the mounting hole in an inserting manner, so that the mounting of the tail is facilitated, and the structural stability of the tail is improved.

In this embodiment, the support plate 24 is approximately drop-shaped with a wide head and a sharp tail. As shown in fig. 4, the tail of the strut 24 is sharp, and the structure is adapted to the skin structure of the wing, so that the wing is streamlined to achieve good fluid performance.

Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.