TWI738299B - Flight equipment - Google Patents

Abstract

A flying equipment comprises a fuselage body having a cabin and a plurality of first acting devices disposed in the cabin, wherein a bottom side of the cabin is hollowed out to generate forces from the plurality of first acting devices outside a bottom of the flying equipment, and the first action device is covered by the cabin, so that when each of the first action devices generates the forces, an airflow around the fuselage body is prevented from interfering with the forces, and a reaction force corresponding to the forces can be reduced by a pressure in the cabin, so the flight equipment can be smoothly lifted vertically.

Description

Flight equipment

The present invention relates to a kind of flying equipment, especially a kind of unmanned aerial vehicle flying equipment.

In view of the wide range of uses of drones, such as delivery, survey, rescue, etc., the development of the drone industry is extremely rapid.

The design of existing UAVs is more popular in the industry, such as rotary wing aircraft. In addition, a fixed-wing type drone that needs to take off and sprint can use its wings to glide.

However, in the existing UAVs, if they take off vertically in areas with complex environments (such as forest areas), the rotorcraft's propellers are exposed outside the casing and are easily interfered by the surrounding airflow (wind resistance), which makes the UAV easy Shaking, or the propeller easily touches obstacles, or hits trees, or even crashes.

Therefore, how to overcome the various shortcomings of the conventional technology is actually a technical problem that all walks of life urgently want to solve.

In view of the various deficiencies of the above-mentioned conventional technologies, the present invention provides a flying equipment, which includes: a fuselage body with a cabin and at least one opening communicating with the cabin for air to flow into the cabin, wherein the bottom side of the cabin Is a hollow shape; and a plurality of first acting devices are spaced apart in the nacelle, wherein each of the first acting devices has opposite first and second sides, and the nacelle covers the first acting device The first side, and the second side of the first acting device is correspondingly located on the bottom side of the nacelle, so that the opening is used as an air inlet port corresponding to the plurality of first acting devices, and the first side is used as an airflow inlet port, The second side serves as an air outlet port.

In the aforementioned flight equipment, the fuselage system defines a layout section, and a first section and a second section adjacent to opposite sides of the layout section, and the plurality of first action devices are arranged on the layout section .

In the aforementioned flying equipment, the inlet vector of the opening is perpendicular to the outlet vector of the second side.

In the aforementioned flying equipment, the opening is formed on the side fuselage of the fuselage body, so that the opening is located diagonally above the plurality of first acting devices based on the nacelle.

In the aforementioned flying equipment, the plurality of first action devices are arranged in a rectangular array into a plurality of mutually separated action modules, and a single action module includes a plurality of the first action devices. For example, the plural action modules are made into a single unit. Alternatively, the deployment range of the opening is greater than or equal to the deployment range of a single function module. Further, the distance between the plurality of acting modules is greater than the distance between the plurality of first acting devices.

In the aforementioned flying equipment, the first acting device is a ducted fan type.

In the aforementioned flight equipment, the first acting device is arranged upright or inclined relative to the bottom side of the cabin.

In the aforementioned flying equipment, the first side of the first acting device is provided with a first air guiding element, and the second side is connected with a second air guiding element as an airflow outlet port, so that the first air guiding element The air is guided into the first action device, and the air is led out of the nacelle by the second air guide. For example, the second side is directly connected to the second air deflector to lead the air out of the bottom side of the nacelle. Or, the second air deflector is arranged under the wing. Further, the first air guide or the second air guide is pivotally connected to the first acting device.

In the aforementioned flying equipment, the side fuselage of the fuselage body is equipped with a plurality of second acting devices, so that the plurality of second acting devices generate another force toward the side fuselage of the fuselage body. For example, the second acting device is a duct fan type, and the angle formed between the air outlet direction of the second acting device and the air outlet direction of the first acting device is an acute angle. Alternatively, the opening is connected to the second acting device, so that the air flows locally to the second acting device after taking in from the opening, so that the second acting device can generate the other acting force. Or, the nacelle is formed with another opening corresponding to the second acting device, so that air flows only to the second acting device after taking in from the other opening. Further, the opening corresponding to the first acting device and the other opening corresponding to the second acting device are not connected to each other.

It can be seen from the above that, in the flying equipment of the present invention, sufficient force is generated mainly by the arrangement of a plurality of first acting devices, and the first side of the first acting devices is covered by the cabin, so that the first side of each of the first acting devices is covered. When an action device generates an action force, it can prevent the airflow around the fuselage body from interfering with the action force, and the pressure of the cabin in the cabin can alleviate the force of the reaction force of the action force. Therefore, compared with the conventional technology, The flying equipment of the present invention can balance and stabilize the vertical lift-off when rising upwards, avoiding the problem of collision with surrounding objects due to shaking, thereby avoiding crash accidents.

The following specific examples illustrate the implementation of the present invention. Those familiar with the art can easily understand the other advantages and effects of the present invention from the contents disclosed in this specification.

It should be noted that the structure, ratio, size, etc. shown in the drawings in this manual are only used to match the content disclosed in the manual for the understanding and reading of those who are familiar with the art, and are not intended to limit the implementation of the present invention. Therefore, it does not have any technical significance. Any structural modification, proportional relationship change or size adjustment should still fall within the original The technical content disclosed by the invention can be covered. At the same time, the terms "on", "first", "second" and "one" cited in this specification are only for ease of description and are not used to limit the scope of the present invention. The change or adjustment of the relative relationship shall be regarded as the scope of the implementation of the present invention without substantial change in the technical content. The following specific examples illustrate the implementation of the present invention. Those familiar with the art can easily understand the other advantages and effects of the present invention from the contents disclosed in this specification.

1A and 1B are schematic plan views of different viewing angles of the flying device 1 of the present invention. As shown in Figures 1A and 1B, the flying equipment 1 includes a fuselage body 1a, a plurality of first acting devices 11 and a plurality of second acting devices 12, wherein the plurality of first acting devices 11 are defined as An action module 1d (four action modules 1d as shown in the figure), that is, a ducted fan module, the first action device 11 and the second action device 12 can be regarded as power devices or lifting devices.

In this embodiment, based on the configuration of the flying equipment 1, the arrow direction X in each drawing indicates the front and rear direction, the arrow direction Y in each drawing indicates the left and right direction, and the arrow in each drawing The direction Z indicates the up and down direction.

Furthermore, the flying equipment 1 is, for example, a fixed-rotor compound wing drone, and its fuselage body 1a is provided with a set of wings 1b and a tail 1c, and the wing 1b is erected on the fuselage body 1a. Above, and the tail 1c is a wing structure. For example, the tail 1c can be equipped with a propeller 15 as required to generate propulsion power forward (moving direction X1) when rotating. Or, as shown in Figures 2A and 2B, the wings 2b are provided on the left and right sides of the fuselage body 2a, and the tail 2c is a short-tail shell structure.

The fuselage body 1a has a nacelle 10 and at least one opening 100 connecting the nacelle 10, wherein the bottom side 10b of the nacelle 10 (as shown in Figure 1B) is hollowed out (as shown in Figure 1C). Shown), and the nacelle 10 is equipped with a supporting structure (not shown), such as a fixed frame, to fix (such as screwing, welding, pasting or other methods) the first acting devices 11, wherein each of the first action devices 11 There is an interval between one acting device 11 (for example, a plurality of connecting members 110 shown in Figure 1C are used to connect each of the first acting devices 11, and each of the plurality of connecting members 110 is also connected, and the supporting structure is fixed to the The connecting piece 110) is arranged, and each of the action modules 1d and the nacelle 10 (such as the top side 10a) are kept at a distance (such as a cavity interval), so as to be generated by each of the action modules 1d in the nacelle 10 With sufficient pressure, the jet vector is generated after the cabin 10 is pressurized.

As shown in Figures 1B and 2B, in this embodiment, the fuselage body 1a, 2a is a housing structure, which is defined along the front and rear direction or the length of the fuselage (arrow direction X). The first section A1 (nose to front wheel) on the front side of the body body 1a, 2a, and a layout section A2 (front wheel to waiting wheel) adjacent to the first section A1 and equipped with the first acting device 11 It is adjacent to the second section A3 (rear wheel to the tail) of the fuselage body 1a, 2a adjacent to the layout section A2, and the nacelle 10 is located at the layout section A2, so that the nacelle 10 is located Between the first section A1 and the second section A3, and in the first section A1 and the second section A3, at least one accommodating space S for carrying goods is respectively arranged. For example, the casing structure of the fuselage body 1a, 2a at the nacelle 10 is equipped with an organic door 101 to open or close the left and right fuselages 10c of the nacelle 10 for users to inspect and maintain.

Furthermore, the openings 100 are formed on the side body 10c in the left and right directions (arrow direction Y) of the body 1a (as shown on the door 101 in Fig. 1B) to correspond to some The air inlet port of the first acting device 11 allows air to flow into the nacelle 10 (as shown in the airflow direction P in Figure 1C). For example, the opening 100 is based on the nacelle 10 correspondingly located diagonally above the functional module 1d (as shown in Figure 1C) and is configured based on the side fuselage 10c in a manner aligned with the functional module 1d, so that the The intake vector (the airflow direction P shown in Figure 1C) is perpendicular to the outflow vector (the airflow direction P2 shown in Figure 1C). Specifically, as shown in FIG. 1B, the opening 100 is a rectangular or elongated hole, and the layout range (or length L1) of the single opening 100 is greater than or equal to the layout range (or length L2) of the single function module 1d. Alternatively, as shown in Figure 2B, the opening 200 can also be a streamlined opening or arc opening, which is based on the side body 10c being arranged in a manner that is not aligned with the function module 1d, and the opening 200 partially covers or The function module 1d is overlapped spatially, and the opening 200 is still located obliquely above the function module 1d based on the nacelle 10, so that the air intake vector is perpendicular to the air output vector. It should be understood that the position and shape of the opening on the fuselage body can be designed according to requirements, as long as the air intake vector is perpendicular to the air output vector, and there is no particular limitation.

In addition, at least one functional device 13 is arranged outside the bottom of the first section A1 of the fuselage body 1a, 2a, such as a photoelectric ball type image capturing device, to facilitate the user to control the flying equipment 1,2.

In addition, a communication connection (or electrical connection) between the first action device 11 and the second action device 12 can be arranged at the upper part of the nacelle 10 to actuate the control device 14 of the first action device 11 and the second action device 12. For example, the control device 14 can be equipped with a control system and a hybrid power module, so that the user can remotely control the control device 14 to control the operation of the first action device 11 and the second action device 12.

As shown in Figure 1C, the first acting device 11 is arranged in the nacelle 10, wherein each of the first acting devices 11 has a first side 11a and a second side 11b opposite to each other. The top side 10a covers the first side 11a of the first acting device 11, and the second side 11b of the first acting device 11 is exposed on the bottom side 10b of the nacelle 10 so that the first acting devices 11 face A jet force F is generated outside the bottom side 10b of the nacelle 10.

In this embodiment, the first acting devices 11 are of the ducted fan type, and the first side 11a is used as the air inlet port, and the second side 11b is used as the air outlet port, so that the single ducted fan The jet force F is about 15-20 kilograms force (kgf), and the first acting devices 11 are arranged in an array on the bottom side 10b of the cabin 10 (that is, at the belly) for the lifting balance of the flying equipment 1 Group. For example, the first acting devices 11 can be modularized, and a plurality of (such as six) first acting devices 11 are arranged in a rectangular array into one acting module 1d (a total of four acting modules 1d), and The function modules 1d are made into a single unit, such as a Levitation Power Deck, so as to facilitate the disassembly and assembly of the suspension power deck, each function module 1d, or each first function device 11 in the nacelle 10 as required The bottom side 10b. Specifically, as shown in Figure 1A, the nacelle 10 is roughly a rectangular parallelepiped space (as shown in Figure 1A, the vertical plane projection of the nacelle 10 toward its top side 10a is rectangular, and its long side corresponds to the side of the nacelle 10. Body 10c), each of the action modules 1d is arranged at each corner of the nacelle 10 in a spaced manner (e.g., cavity state) based on the top side 10a, so that the two sets of action modules 1d are close to the nose (e.g. One section A1), and two groups of function modules 1d are close to the tail (such as the second section A3), and the long sides of the rectangular array of each function module 1d correspond to the side fuselage 10c of the nacelle 10, rectangular The short side of the array corresponds to the nose or tail 1c of the nacelle 10, and the front and rear spacing D1 of each functional module 1d is greater than the left and right spacing D2 of each functional module 1d, wherein each of the first The distance t between the action devices 11 is smaller than the distance D1, D2 between the action modules 1d. This configuration method can improve the balance of thrust and improve wind resistance.

In another embodiment, as shown in Figures 2A and 2B, the nacelle 10 can extend to the first section A1 and the second section A3, and the nacelle 10 is substantially streamlined or a rod-shaped space (such as The vertical plane projection of the nacelle 10 shown in Figure 2A toward its top side 10a is streamlined or rod-shaped, and its long arc side corresponds to the wing 2b), so that each function module 1d is arranged in the nacelle in a balanced configuration 10 before, after, left and right. For example, each of the action modules 1d is arranged in the nacelle 10 in a spaced manner (such as a cavity state) based on the top side 10a, so that a set of action modules 1d (nose modules) are located in the nacelle. 10 front side (such as close to the nose), the short side of its rectangular array is facing the wing 2b, the long side of the action module 1d is facing the nose, and a group of action modules 1d is located on the rear side of the nacelle 10 ( For example, near the tail, the tail module), the short side of the rectangular array is facing the wing 2b, the long side of the function module 1d is toward the tail 2c, and the other two groups of function modules 1d are left and right. The side-by-side (the long sides of the function modules 1d are adjacent to each other) are located between the nose module and the tail module of the nacelle 10, and the long sides of the rectangular array are facing the wing 2b. Specifically, the distance D3, D4 between at least one of the two action modules 1d in the middle and the action modules 1d on the front and back sides may be the same or different, but the distances D3, D4 are both larger than the middle The distance D5 between the two function modules 1d.

Furthermore, as shown in Figure 1C, the first acting device 11 can be set upright relative to the bottom side 10b of the nacelle 10 to generate a direct downward force F toward the bottom side 10b of the nacelle 10; As shown in Figure 3A, among the first acting devices 11 arranged in the left and right directions, the first acting device 11 can be inclined relative to the bottom side 10b of the nacelle 10 as required, so as to face the bottom side of the nacelle 10 An oblique downward force F'is generated outside 10b. The force F and the force F'form an acute angle. The first side 11a is an airflow inlet port, and the second side 11b is an airflow outlet port. It should be understood that the inclination angle of the inclined arrangement of the first acting device 11 can be adjusted according to requirements. The inclination angle of the acting device 11 is increased from the middle to the front and the rear ends to generate different inclination forces F', F" toward the bottom side 10b of the nacelle 10, and a force F, F', F" is sandwiched between Acute angle.

In addition, the first acting device 11 can be arranged flat relative to the bottom side 10b of the nacelle 10 according to requirements, that is, the first side 11a and the second side 11b face the front and rear directions (or left and right directions), such as 4A As shown in the figure, a first air guide 41 is respectively arranged on the first side 11a and the second side 11b of the first acting device 11 And the second guide 42 (L tube, V tube, or curved tube can be used), so that the first guide 41 serves as an airflow inlet port, which guides air (airflow direction P) to the first side 11a , And the second air guiding element 42 serves as an airflow outlet port, so that the air entering from the first side 11a is guided out of the bottom side 10b of the nacelle 10 through the second air guiding element 42 from the second side 11b. Generate a force F directly below. Furthermore, the first air guiding element 41 or the second air guiding element 42 can be pivotally connected to the first acting device 11 according to requirements, and can swing according to requirements (as shown in FIG. 4A, the first acting device 11 is relatively front and rear The axial direction or arrow direction X is clockwise or counterclockwise rotation of the arrow direction W to the left and right to drive the first guide 41 or the second guide 42 to move) for the user to adjust the force F The ejection direction (such as the force F', F" in different oblique directions). It should be understood that the first or second deflector 41 or 42 can be inclined in the forward and backward directions as required to produce an oblique The downward force F', F" can be matched with the swing design (as shown in Figure 4B, the direction of the arrow rotates clockwise or counterclockwise to the left and right) to facilitate the generation of the oblique downward force of the multi-directional jet F',F".

In addition, the second air deflector 42, 42' can be arranged under the wings 1b, 2b according to requirements, so that the air entering from the first side 11a is discharged from the second air deflector 42, 42' Below the wings 1b and 2b, the forces F, F', F" are generated. For example, the second side 11b of the first action device 11 is connected to a guide pipe 420 (as shown in Fig. 4C) One end of the guide pipe 420 is arranged to extend to the wing 1b, 2b, so that the other end of the guide pipe 420 is equipped with the second guide piece 42, 42', so that the first The two guides 42, 42' serve as air outlet ports.

Therefore, there are many configurations of the first acting device 11, which are not limited to the above, and only need to be able to generate jetting forces F, F', F" toward the bottom side 10b of the nacelle 10.

The second acting device 12 is arranged on the left and right side bodies 10c of the main body 1a, 2a, so that the air outlets of the second acting devices 12 face the left and right sides of the main body 1a, 2a The outside of the body 10c is shown in Figures 1A, 1B, 2A, and 2B.

In this embodiment, the second acting devices 12 are ducted fan types, which are respectively arranged on the second section A3 of the fuselage body 1a, 2a near the bottom of the left and right fuselage 10c and close to The tails 1c and 2c allow the control device 14 to actuate the second acting device 12 so that the second acting device 12 generates another force R toward the left or right rear of the fuselage body 1a, 2a for the user Regulate the flying device 1 to turn to the left (moving direction R1 as shown in Figure 1A) or to the right (moving direction R2 as shown in Figure 1A) to fly (such as yaw YAW). For example, adjusting the magnitude of the spray force R of the two second acting devices 12, or finely adjusting the orientation of the second acting devices 12 in the front and rear directions (as shown in the arrow direction R in Figure 1A) to swing the The second acting device 12 enables the flight equipment 1,2 to perform steering flight. Specifically, the range of the outlet vector (such as the jet force R) of the second acting device 12 is between the extending direction of the wings 1b, 2b and the tail 1c, 2c (or propeller 15), such as side The angle θ between the jet force R and the jet vector (such as force F) of the first acting device 11 is a right angle or an acute angle in space, and the jet vector of the second acting device 12 (such as The angle θ between the acting force R) and the propeller 15 is also an acute angle.

Furthermore, the second acting device 12 can also be equipped with a flow guide (such as the first flow guide 41 or the second flow guide 42) according to requirements.

Moreover, as shown in Figure 1B, the opening 100 corresponding to the first acting device 11 can be connected to the two second acting devices 12, so that air is taken in from the opening 100 and then flows locally to the second acting device 12 for the second acting device 12 The second acting device 12 generates another force R; or, as shown in Fig. 2B, the nacelle 10 may form another opening 200' corresponding to the second acting device 12, so that air can only be taken in from the opening 200' Flowing to the second acting device 12, the opening 200 ′ is an independent channel for supplying air to the second acting device 12. Therefore, the nacelle 10 can be formed with at least a first opening (such as opening 200) corresponding to the first acting device 11 and at least a second opening (such as opening 200') corresponding to the second acting device 12, and An opening and the second opening are not connected to each other.

When operating the flying equipment 1 and 2, the first action device 11 is operated by the control device 14, and air enters the cabin 10 from the openings 100, 200 (as shown in the airflow direction P, P1 in Figure 1C), Used by the first acting device 11, so that the first acting device 11 generates jetting force F, F', F" toward the bottom side 10b of the fuselage body 1a, 2a (as shown in the airflow direction in Figure 1C) P2), so that the flying equipment 1,2 can rise upward (as shown in the moving direction Z1 in Figure 1B).

Therefore, the flight equipment 1, 2 is arranged in an array of a plurality of first acting devices to generate sufficient jet force F, F', F", and each of the first acting devices is covered by the enclosed nacelle 10 The design of 11, as shown in Figure 1C, helps to increase the cabin pressure of the cabin 10 and is conducive to generating the thrust required for take-off (such as force F, F', F"), so each of the first When the action device 11 generates the spray force F, F', F", it can prevent the airflow around the fuselage body 1a, 2a (such as front, rear, left and right) from interfering with the force F, F', F", And by the cabin pressure in the cabin 10, the force of the reaction force of the force F, F', F" can be alleviated, so that the flying equipment 1,2 can be balanced and stably lifted into the air when it rises upwards, and make More rotors have higher fault tolerance.

Furthermore, the flight equipment 1,2 of the present invention is built-in the control device 14 in the nacelle 10, which can reduce the power consumption during cruise and reduce the radar reflection area, and the flight equipment 1,2 will not affect the aircraft due to the reduced speed. Posture control of body 1a, 2a. In one embodiment, air enters the nacelle 10 through the openings 100 and 200, and part of the airflow may pass near the control device 14 or directly contact the airflow, so as to dissipate the control device 14.

In addition, the flying equipment 1 and 2 of the present invention utilize the first action device 11 (ducted fan) arranged in a plurality of arrays on the bottom side 10b of the nacelle 10, which not only has a high efficiency ratio of the forces in the take-off and landing mode, but also The configuration of the wings 1b, 2b does not limit the speed and the load capacity of the accommodating space S.

On the other hand, after the flying equipment 1,2 rises to a predetermined height (vertical take-off and landing), air enters the cabin 10 from the opening 100, 200' for the second action device 12 to use, so that the second action The device 12 generates a jet force R toward the rear of the fuselage body 1a, 2a, so that the flying equipment 1,2 can fly forward (as shown in the moving direction X1 in Figures 1A and 1B), and cooperate with the control The device 14 rotates the propeller 15 of the tail 1c to generate forward propulsion power.

Furthermore, by adjusting the magnitude or direction of the spray force R of each of the second action devices 12, the flying equipment 1,2 can fly in the left and right directions as required when flying forward (as shown in 1A) Show the direction of movement R1, R2).

In summary, the flying equipment of the present invention mainly generates sufficient lift-off force by arraying a plurality of first acting devices, and the cabin (the front, rear, left, and right directions have a shell structure) Cover the first side of the first acting devices, so that when each of the first acting devices generates a force, it can prevent the airflow around the fuselage body from interfering with the force, and can be relieved by the cabin pressure in the cabin The force of the reaction force of the force enables the flying equipment to balance and stabilize the vertical lift when it rises upwards, so it can avoid collisions with surrounding objects (such as trees, branches, houses, etc.) due to unexpected deviation (such as shaking) Or other problems), which can avoid the occurrence of crashes and make more rotors more fault-tolerant.

Furthermore, the flying equipment of the present invention can reduce power consumption and radar reflection area during cruising, and the flying equipment will not affect the attitude control of the fuselage body due to the reduced speed.

The above-mentioned embodiments are used to exemplify the principles and effects of the present invention, but not to limit the present invention. Anyone who is familiar with this technique can modify the above-mentioned embodiments without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the rights of the present invention should be listed in the scope of patent application described later.

1,2: Flight equipment 1a, 2a: main body 1b, 2b: wings 1c, 2c: tail 1d: Function module 10: Cabin 10a: Top side 10b: bottom side 10c: Side body 100,200,200’: opening 101: Door 11: The first acting device 11a: first side 11b: second side 110: connecting piece 12: Second acting device 13: Functional device 14: Control device 15: Propeller 41: The first deflector 42,42’: The second deflector 420: Guide line A1: The first section A2: Laying out section A3: Second section D1, D2, D3, D4, D5, t: pitch F,F’,F” ,R: force L1, L2: length P, P1, P2: airflow direction S: accommodating space W, X, Y, Z, r: arrow direction X1, Z1, R1, R2: moving direction θ: included angle

Figure 1A is a schematic top plan view of the flying equipment of the present invention.

Figure 1B is a schematic plan view of the left side of Figure 1A.

Figure 1C is a partial schematic view of the bottom side of the flying equipment of the present invention.

Fig. 2A is a schematic top plan view of another embodiment of Fig. 1A.

Figure 2B is a schematic plan view of the left side of Figure 2A.

Fig. 3A is a schematic front view of one arrangement of the first action device of the flying equipment of the present invention.

Figure 3B is a schematic left view of another arrangement of the first action device of the flying equipment of the present invention.

4A and 4B are three-dimensional schematic diagrams of other different embodiments of the first acting device of the flying equipment of the present invention.

Figure 4C is a partial three-dimensional schematic diagram of another configuration of the second guide of the flying equipment of the present invention.

1: flight equipment

1a: main body

1b: Wing

1c: tail

10: Cabin

10a: Top side

10b: bottom side

10c: Side body

100: opening

101: Door

11: The first acting device

11a: first side

11b: second side

12: Second acting device

13: Functional device

14: Control device

15: Propeller

A1: The first section

A2: Laying out section

A3: Second section

F, R: force

L1, L2: length

S: accommodating space

X, Z: arrow direction

X1, Z1: moving direction

θ: included angle

Claims (20)

A kind of flying equipment, including: The fuselage body has a nacelle and at least one opening communicating with the nacelle for air to flow into the nacelle, wherein the bottom side of the nacelle is hollow; and A plurality of first acting devices are modularized and arranged at intervals in the nacelle, wherein each of the first acting devices has opposite first and second sides, and the nacelle covers the first of the first acting devices Side, and the second side of the first acting device is correspondingly located on the bottom side of the nacelle, so that the opening is used as the inlet port corresponding to the plurality of first acting devices, and the first side is used as the air inlet port, and the The second side serves as an air outlet port. As for the flight equipment described in item 1 of the scope of patent application, the fuselage system defines a layout section, and a first section and a second section adjacent to opposite sides of the layout section, and the plurality of first sections The action device is arranged on the arrangement section. The flying device according to the first item of the scope of patent application, wherein the air intake vector of the opening is perpendicular to the air output vector of the second side. According to the flying equipment described in claim 1, wherein the opening is formed on the side fuselage of the fuselage body, so that the opening is located obliquely above the plurality of first acting devices based on the nacelle. The flying equipment described in claim 1, wherein the plurality of first action devices are arranged in a rectangular array into a plurality of mutually separated action modules, and a single action module contains a plurality of the first action modules. Function device. For the flight equipment described in item 5 of the scope of patent application, the plural function modules are modularized into a single unit. For the flight equipment described in item 5 of the scope of the patent application, the deployment range of the opening is greater than or equal to the deployment range of a single functional module. The flying equipment described in item 5 of the scope of patent application, wherein the distance between the plurality of action modules is greater than the distance between the plurality of first action devices. For the flying equipment described in item 1 of the scope of patent application, the first acting device is a duct fan type. The flying equipment described in item 1 of the scope of patent application, wherein the first acting device is arranged upright or inclined relative to the bottom side of the cabin. The flying equipment described in the first item of the scope of patent application, wherein the first side of the first acting device is provided with a first air guiding element, and the second side is connected with a second air guiding element as an airflow outlet port , So that the first air deflector guides the air into the first action device, and the air is led out of the nacelle by the second air deflector. The flight equipment described in item 11 of the scope of patent application, wherein the second side is directly connected to the second air deflector so as to lead the air out of the bottom side of the cabin. The flying equipment described in item 11 of the scope of patent application, wherein the second air deflector is arranged under the wing. The flying equipment described in item 11 of the scope of patent application, wherein the first air guide or the second air guide is axially connected to the first acting device. The flying equipment as described in the first item of the scope of patent application, wherein the side fuselage of the fuselage body is equipped with a plurality of second acting devices so that the plurality of second acting devices face outwards of the side fuselage of the fuselage body Create another force. The flying equipment described in item 15 of the scope of patent application, wherein the second acting device is a ducted fan type. As for the flying equipment described in item 15 of the scope of patent application, the angle formed between the air outlet direction of the second acting device and the air outlet direction of the first acting device is a right angle or an acute angle in space. As for the flying equipment described in item 15 of the scope of patent application, the opening is connected to the second acting device, so that the air flows into the second acting device locally after taking in from the opening, so that the second acting device generates the other Force. As for the flight equipment described in item 15 of the scope of patent application, the nacelle further includes another opening corresponding to the second acting device, so that air can flow independently to the second acting device after being taken in from the other opening. The flying equipment according to item 19 of the scope of patent application, wherein the opening corresponding to the first acting device and the other opening corresponding to the second acting device are not connected to each other.

Images