Distributed power cluster type unmanned child-mother aircraft and use method

Abstract

The invention discloses a distributed power cluster type unmanned child-mother aircraft and a use method, belongs to the field of aerodynamic layout design of aircrafts, and aims to solve the problem that an existing cluster type unmanned child-mother aircraft is not suitable for taking off in extreme environments such as island reefs and dense forests. The child-mother aircraft comprises a carrier mother aircraft and a plurality of propeller type child aircrafts, the carrier mother aircraft comprises an aircraft body, a horizontal tail is arranged at the tail of the aircraft body through a vertical tail, wings are arranged on the two sides of the aircraft body, inner side flaps, outer side flaps and ailerons are arranged on the rear edges of the wings, and a plurality of rotating shafts are arranged on the front edges of the wings at intervals in the spanwise direction; the propeller type sub-machines are detachably connected with the rotating shafts in a one-to-one correspondence mode, signal receiving and control units are arranged in the propeller type sub-machines, and wingtips of the wings are rotationally connected with main propellers. In the take-off stage, the propeller type sub-aircrafts are connected to the wings, the main propeller and propellers of the propeller type sub-aircrafts are arranged upwards perpendicular to the ground, and the problem that the unmanned child-mother aircraft is inconvenient to take off in an extreme environment is solved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aircraft aerodynamic layout design, and particularly relates to a distributed power cluster type unmanned mother-son aircraft and a use method. BACKGROUND

[0002] At present, with the continuous development of unmanned aerial vehicle technology, the rapid growth of the types and quantities of unmanned aerial vehicles, the layout form, function and application scene of unmanned aerial vehicles are constantly breaking through. However, a single type of unmanned aerial vehicle often cannot meet the needs of multi-task targets, which has given birth to the rapid development and multi-field application of cluster type unmanned aerial vehicles. Among them, in the military field, cluster type unmanned aerial vehicles gradually become one of the most active elements in the battlefield. In the civil field, the application of cluster type unmanned aerial vehicles is also becoming more and more extensive, such as logistics transportation, agricultural plant protection, environmental monitoring, etc., which requires unmanned aerial vehicles to have higher intelligent level and cluster operation ability. As can be seen, cluster type unmanned aerial vehicles have great use prospect in both military field and civil field, and therefore have obtained the key support of many countries. Therefore, it is necessary to carry out research on cluster type unmanned aerial vehicles, accumulate technical experience, empower advanced technologies such as artificial intelligence and directional energy, accelerate the conversion speed of scientific and technological achievements, and promote the leap-forward development of the field of cluster type unmanned aerial vehicles.

[0003] The cluster unmanned aerial vehicle is not suitable for long-distance flight, so the carrier mother machine is often used to transport the cluster unmanned aerial vehicle to the target area and then release it. The invention patent with publication number CN108216621A discloses a wing tip connected parallel type mother-son aircraft, and the utility model patent with publication number CN207191430U discloses a sea search unmanned mother-son aircraft, both of which transport the cluster unmanned aerial vehicle through the carrier mother machine, but the existing carrier mother machine is not suitable for taking off in extreme environments such as islands and dense forests through taxiing. SUMMARY

[0004] The purpose of the present application is to provide a distributed power cluster type unmanned mother-son aircraft and a use method to solve the problem that the existing cluster type unmanned mother-son aircraft is not suitable for taking off in extreme environments such as islands and dense forests. The technical solution adopted by the present application is as follows: A distributed power cluster type unmanned mother-son aircraft, comprising a carrier mother machine, the carrier mother machine comprising a fuselage, a horizontal tail being arranged at the tail of the fuselage through a vertical tail, both sides of the fuselage being provided with wings, the trailing edge of the wing being provided with an inboard aileron, an outboard aileron and ailerons, further comprising a plurality of propeller type sub-machines, a plurality of rotating shafts being arranged along the span direction at the leading edge of the wing, the plurality of propeller type sub-machines being in one-to-one correspondence with the plurality of rotating shafts and being disconnectably connected, the propeller type sub-machine being internally provided with a signal receiving and control unit, and the wing tip being rotatably provided with a main propeller; In the take-off stage, the propeller sub-machines are connected to the wings, and the main propeller and the propellers of the propeller sub-machines are vertically upward, in the cruising stage, the propeller sub-machines are connected to the wings, and the main propeller and the propellers of the propeller sub-machines are horizontally forward, in the task stage, the propeller sub-machines are separated from the wings, and form a task group.

[0005] Further, the rotating shaft is provided with a sliding rail seat, and the propeller sub-machine is provided with a sliding block, when the propeller sub-machine is connected to the wing, the sliding block is connected with the sliding rail seat in a clamping mode and is mechanically locked.

[0006] Further, the eight propeller sub-machines are symmetrically arranged, and four propeller sub-machines are arranged on each wing.

[0007] Further, the wing is a single wing.

[0008] Further, the leading edge of the wing is not a swept wing.

[0009] Further, the main propeller is connected with the power system through a pivoting mechanism.

[0010] The application also provides a use method of the distributed power cluster type unmanned mother-child aircraft, which is realized by relying on the above-mentioned distributed power cluster type unmanned mother-child aircraft, and comprises the following steps. Step one, in the take-off stage, the main propeller and the propellers of the propeller sub-machines are used as power devices, and are deflected vertically upward, so that the unmanned mother-child aircraft takes off vertically; Step two, when the unmanned mother-child aircraft exceeds the height of the take-off obstacle, the transition stage is entered, the main propeller and the propellers of the propeller sub-machines are gradually deflected forward from the vertical upward, and the transition stage ends when the cruising height is reached; Step three, in the cruising stage, the main propeller and the propellers of the propeller sub-machines are used as power devices, and are deflected forward, so as to provide the pulling force required by the unmanned mother-child aircraft in high-speed cruising, at the same time, the inside aileron, the outside aileron and the elevator are used for maneuvering, so that the unmanned mother-child aircraft efficiently reaches the designated area, and the high-speed cruising stage ends; Step four, in the airborne separation stage, the propellers of the propeller sub-machines are rotated vertically upward, so that the unmanned mother-child aircraft hovers in the air, the sliding block and the sliding rail seat are unlocked through signal control, the sliding block is separated from the sliding rail seat by the self-power of the propeller sub-machine, after the propeller sub-machines are separated from the wings, the propeller sub-machines are used as small cluster unmanned aircrafts, and independently perform the task stage, the signal receiving and control unit built in the propeller sub-machine is activated, the heading control is completed by receiving the base signal, and the operation area is reached; Step five, the main propeller as a power device, rely on the inner side flap, the outer side flap and the aileron to maneuver, so that the carrier aircraft returns, the carrier aircraft returns to make up for the next task.

[0011] Compared with the prior art, the present application has the beneficial effects that: The unmanned mother-son aircraft of the present application rotates the main propeller and the propellers of the several propeller sub-machines vertically upward to provide upward pulling force, which facilitates take-off and completion of work tasks in extreme environments such as islands and dense forests, can save the cost of the runway for take-off, and improves the maneuverability of the work, in the cruising stage, the main propeller and the propellers of the several propeller sub-machines are rotated horizontally forward to provide forward pulling force, and the problem of difficulty in take-off of the unmanned mother-son aircraft in extreme environments and slow flight speed in the cruising stage is solved by rotating the main propeller and the several propeller sub-machines. BRIEF DESCRIPTION OF DRAWINGS

[0012] Figure 1 is the vertical take-off stage state of the unmanned mother-son aircraft of the present application; Figure 2 is the vertical take-off stage state of the unmanned mother-son aircraft of the present application; Figure 3 is the vertical take-off stage state of the unmanned mother-son aircraft of the present application; Figure 4 is the transition stage state of the unmanned mother-son aircraft of the present application; Figure 5 is the cruising stage state of the unmanned mother-son aircraft of the present application; Figure 6 is the state of the carrier aircraft releasing the propeller sub-machines and returning after the return stage; Figure 7 is the schematic diagram of the several propeller sub-machines forming a drone cluster after being separated from the aircraft; Figure 8 is the connection schematic diagram of the slide rail seat and the slide block.

[0013] In the figure, 1. horizontal tail, 2. vertical tail, 3. fuselage, 4. inner side flap, 5. outer side flap, 6. aileron, 7. main propeller, 8. propeller sub-machine, 9. wing, 10. slide rail seat, 11. slide block, 12. rotating shaft. DETAILED DESCRIPTION

[0014] To make the objectives, technical solutions, and advantages of this invention clearer, the invention is described below with reference to specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely exemplary and not intended to limit the scope of the invention. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concept of the invention.

[0015] The connections mentioned in this invention are divided into fixed connections and detachable connections. Fixed connections, also known as non-detachable connections, include but are not limited to conventional fixed connection methods such as folded connections, riveted connections, adhesive connections, and welded connections. Detachable connections include but are not limited to conventional disassembly methods such as bolted connections, snap-fit ​​connections, pin connections, and hinged connections. When a specific connection method is not explicitly defined, it is assumed that at least one existing connection method can be found to achieve this function, and those skilled in the art can choose according to their needs. For example, a welded connection can be chosen for fixed connections, and a bolted connection can be chosen for detachable connections.

[0016] The present invention will be further described in detail below with reference to the accompanying drawings. The following embodiments are explanations of the present invention, but the present invention is not limited to the following embodiments.

[0017] Example 1: As Figures 1-8 As shown, a distributed-powered cluster-type unmanned mother-daughter aircraft includes a carrier aircraft, which includes a fuselage 3, a horizontal stabilizer 1 and a vertical stabilizer 2 at the tail of the fuselage 3, wings 9 on both sides of the fuselage 3, an inner flap 4, an outer flap 5 and an aileron 6 on the trailing edge of the wings 9, and several propeller-type daughter aircraft 8. Several rotating shafts 12 are arranged at intervals along the span of the leading edge of the wings 9. The several propeller-type daughter aircraft 8 are detachably connected to the several rotating shafts 12 in a one-to-one correspondence. The propeller-type daughter aircraft 8 have built-in signal receiving and control units. The wingtips of the wings 9 are rotatably equipped with main propellers 7. During takeoff, the propeller-driven sub-units 8 are connected to the wing 9, and the propellers of the main propeller 7 and the propellers of the several propeller-driven sub-units 8 are all set vertically upward. During cruise, the propeller-driven sub-units 8 are connected to the wing 9, and the propellers of the main propeller 7 and the several propeller-driven sub-units 8 are all set horizontally forward. During the mission phase, the several propeller-driven sub-units 8 detach from the wing 9 and form a mission group. The mission phase refers to the phase in which the several propeller-driven sub-units 8 detach from the carrier aircraft and independently perform operational tasks.

[0018] The unmanned mother-child aircraft in the present application rotates the propellers of the main propeller 7 and the several propeller sub-machines 8 vertically upward in the take-off stage to provide upward pulling force, which facilitates take-off and completion of the task in extreme environments such as islands and dense forests, can save the runway cost of take-off, and improves the maneuverability of the task.

[0019] The eight propeller sub-machines 8 are symmetrically arranged, and four propeller sub-machines 8 are arranged on each wing 9.

[0020] The main propeller 7 is connected with the power system through a pivoting mechanism.

[0021] The wing 9 is a single wing, which increases the stability during cruising.

[0022] The leading edge of the wing 9 is not a swept wing, which facilitates the arrangement of the distributed leading edge propeller 8.

[0023] The rotating shaft 12 is provided with a sliding rail seat 10, and the propeller sub-machine 8 is provided with a sliding block 11, when the propeller sub-machine 8 is connected to the wing 9, the sliding block 11 is connected and matched with the sliding rail seat 10, and is mechanically locked, as shown in Figure 8 .

[0024] Embodiment two: as shown in Figures 1-8 , a use method of a distributed power cluster type unmanned mother-child aircraft, realized by relying on the distributed power cluster type unmanned mother-child aircraft in embodiment one, comprising the following steps: Step one, in the take-off stage, the propellers of the main propeller 7 and the propeller sub-machines 8 are used as power devices, and are deflected vertically upward, so that the unmanned mother-child aircraft takes off vertically, as shown in Figures 1-3 . Step two, when the unmanned mother-child aircraft exceeds the height of the take-off obstacle, it enters the transition stage, the propellers of the main propeller 7 and the propeller sub-machines 8 are gradually deflected forward from the vertical upward, as shown in Figure 4 , in this stage, the pulling direction of the power system is obliquely upward, which can provide forward and upward pulling force at the same time, and the transition stage ends when the cruising altitude is reached; Step three, in the cruising stage, the propellers of the main propeller 7 and the propeller sub-machines 8 are used as power devices, and are deflected forward to provide the pulling force required by the unmanned mother-child aircraft during high-speed cruising, as shown in Figure 5 , at the same time, rely on the inboard flap 4, the outboard flap 5 and the aileron 6 to maneuver, so that the unmanned mother-child aircraft efficiently reaches the designated area, and the cruising stage ends; Step four, airborne separation stage, the propeller of each propeller sub-machine 8 rotates vertically upward, so that the unmanned sub-mother aircraft hovers in the air, the sliding block 11 is unlocked from the sliding rail seat 10 through signal control, each propeller sub-machine 8 respectively makes the sliding block 11 separate from the sliding rail seat 10 by means of its own power, after each propeller sub-machine 8 separates from the wing 9, it is used as a small cluster unmanned aerial vehicle, independently performs the task stage, the signal receiving and control unit built in the propeller sub-machine 8 is activated, the heading control is completed by receiving the base signal, and the cluster unmanned aerial vehicle reaches the operation area, as shown in the figure, the cluster unmanned aerial vehicle can be formed according to the task purpose, and the tasks such as environmental survey and logistics transportation can be completed; Figure 7 As shown in the figure, the cluster unmanned aerial vehicle can be formed according to the task purpose, and the tasks such as environmental survey and logistics transportation can be completed; Step five, return stage, the main propeller 7 is used as a power device, and the inner side flap 4, the outer side flap 5 and the aileron 6 are used for maneuvering to make the carrier mother machine return, as shown in the figure, the carrier mother machine returns and is trimmed for the next task. Figure 6 As shown in the figure, the carrier mother machine returns and is trimmed for the next task.

[0025] The fuselage 3 of the carrier mother machine has a length of 8.32 meters, a volume of 10.50 cubic meters, an overhead projection area of 5.28 square meters and a side projection area of 5.55 square meters. The wing 9 has a GAW-1 airfoil, an expansion length of 15.75 meters, a wing tip chord length of 0.87 meters, a wing root chord length of 1.16 meters, a wing 9 trailing edge sweep angle of 5.50°, and a wing 9 overhead projection area of 7.19 square meters. The tail 1 has a NACA0012 airfoil, an expansion length of 1.55 meters, a wing tip chord length of 0.76 meters, a wing root chord length of 0.91 meters, a tail 1 leading edge sweep angle of 8.62°, a tail 1 trailing edge sweep angle of 4.50°, and a tail 1 overhead projection area of 1.06 square meters. The vertical tail 2 has a NACA0012 airfoil, a height of 1.38 meters, a leading edge sweep angle of 14.78°, and no trailing edge sweep. The vertical tail 2 and the fuselage 3 are connected to each other through a simple fairing design to ensure smooth transition and improve aerodynamic performance. The inner side flap 4 extends from 15% to 40% of the wing span, and the chord length is 26% of the local chord length. The outer side flap 5 extends from 40% to 65% of the wing span, and the chord length is 26% of the local chord length. The inner side flap 4 and the outer side flap 5 can be integrated and linked, or can be controlled separately. The flap deflection is ±30 degrees. The aileron 6 extends from 65% to 80% of the wing span, and the chord length is 26% of the local chord length. The aileron 6 deflection is ±20 degrees. The main propeller 7 has an SC1095 airfoil, a blade angle of 43.75°, a propeller diameter of 2.15 meters, and a hub length of 2.68 meters. The main propeller 7 is connected to the wing tip of the wing 9 through a pivoting mechanism, so that the main propeller 7 can be rotated from a horizontal state to a vertical state. The propeller of the propeller sub-machine 8 has an SC1095 airfoil, a blade angle of 43.75°, a propeller diameter of 1.08 meters, and a hub length of 0.87 meters. The propeller sub-machine 8 is connected to the leading edge of the wing 9 through a rotating shaft 1210, so that each propeller sub-machine 8 can be rotated from a horizontal state to a vertical state.

[0026] The above examples are only illustrative of the present application and do not limit the scope of protection of the present application. Those skilled in the art can make partial changes to them without departing from the spirit of the present application, and all such changes are within the scope of protection of the present application.

Claims

1. A distributed power cluster unmanned mother-child aerial vehicle, comprising a carrier mother machine, the carrier mother machine comprising a fuselage (3), a flat tail (1) arranged at the tail of the fuselage (3) through a vertical tail (2), and wings (9) arranged on both sides of the fuselage (3), the trailing edge of the wings (9) being provided with an inboard flap (4), an outboard flap (5) and an aileron (6), characterized in that: Also include several propeller sub-machine (8), the leading edge of the wing (9) is spaced along the span several rotating shaft (12), several propeller sub-machine (8) and several rotating shaft (12) one-to-one corresponding detachable connection, propeller sub-machine (8) built-in signal receiving and control unit, the wing tip of the wing (9) is rotatably provided with a main propeller (7); In the take-off phase, the propeller sub-machine (8) is connected to the wing (9), and the main propeller (7) and the propellers of the several propeller sub-machines (8) are all vertically upward, in the cruising phase, the propeller sub-machine (8) is connected to the wing (9), and the main propeller (7) and the propellers of the several propeller sub-machines (8) are all horizontally forward, in the task phase, the several propeller sub-machines (8) are all separated from the wing (9), and form a task group.

2. A distributed power swarm of unmanned mother and child aerial vehicles according to claim 1, wherein: The rotating shaft (12) is provided with a sliding rail seat (10), and the propeller sub-machine (8) is provided with a sliding block (11), when the propeller sub-machine (8) is connected to the wing (9), the sliding block (11) is matched with the sliding rail seat (10) and is mechanically locked.

3. A distributed power swarm of unmanned mother and child aerial vehicles according to claim 2, wherein: Eight propeller sub-machines (8) are symmetrically arranged, and four propeller sub-machines (8) are arranged on each wing (9).

4. A distributed power swarm of unmanned mother and child aerial vehicles according to claim 1, wherein: The wing (9) is a single wing.

5. A distributed power swarm of unmanned mother and child aerial vehicles according to claim 1, wherein: The leading edge of the wing (9) is not a swept wing.

6. A distributed power swarm of unmanned sub-parent aerial vehicles according to any one of claims 1-5, characterized in that: The main propeller (7) is connected with the power system through a pivoting mechanism.

7. A method for using a distributed power swarm unmanned mother-child aerial vehicle, implemented by the distributed power swarm unmanned mother-child aerial vehicle according to any one of claims 1-6, characterized in that, The method comprises the following steps: Step one, in the take-off phase, the main propeller (7) and the propellers of each propeller sub-machine (8) are all used as power devices, and are deflected vertically upward, so that the unmanned mother-child aircraft takes off vertically; Step two, when the unmanned mother-child aircraft exceeds the height of the take-off obstacle, enter the transition phase, the main propeller (7) and the propellers of each propeller sub-machine (8) are gradually deflected from vertical upward to forward, and the transition phase ends when reaching the cruising altitude; Step three, in the cruising phase, the main propeller (7) and the propellers of each propeller sub-machine (8) are used as power devices, and are deflected forward to provide the required pulling force when the unmanned mother-child aircraft cruises at high speed, at the same time, the inside aileron (4), the outside aileron (5) and the elevator (6) are used for maneuvering, so that the unmanned mother-child aircraft efficiently reaches the designated area, and the high-speed cruising phase ends; Step four, in the airborne separation phase, the propellers of each propeller sub-machine (8) are rotated vertically upward, so that the unmanned mother-child aircraft hovers in the air, the sliding block (11) is unlocked from the sliding rail seat (10) through signal control, each propeller sub-machine (8) makes the sliding block (11) separate from the sliding rail seat (10) by means of its own power, after each propeller sub-machine (8) is separated from the wing (9), each propeller sub-machine (8) is used as a small cluster unmanned aerial vehicle, and independently performs the task phase, the signal receiving and control unit built in the propeller sub-machine (8) is activated, the heading control is completed by receiving the base signal, and the operation area is reached; Step five, in the return phase, the main propeller (7) is used as a power device, and the inside aileron (4), the outside aileron (5) and the elevator (6) are used for maneuvering, so that the carrier mother machine returns, and the carrier mother machine is repaired after returning to prepare for the next task.

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