Combined-distributed morphing aircraft

Abstract

The utility model relates to the technical field of aircrafts, in particular to a combined-distributed morphing aircraft which comprises four groups of aircraft monomers and a combined-separated system, each group of single aircraft body consists of a load cabin and wings, and the wings are hinged with the load cabin through a connecting rod mechanism; the combination and separation system comprises a center motor and a load bin center positioning block, the center motor is located among the four sets of load bins, the center motor is embedded in the load bin center positioning block, the load bin center positioning block is connected with the load bins in a buckled mode, and a center limiting block is assembled at the output end of the center motor. The aircraft assembly is formed by combining a plurality of single-wing aircraft single bodies, has the advantages of stable spinning, long hang time, strong load capacity, strong clustering capacity and the like, has a larger detection range and larger aerodynamic lift force, can perform collaborative search and collaborative cargo deployment at low cost, and has a wide application prospect. And the survivability and the overall efficiency of the unmanned aerial vehicle cluster can be effectively improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, and in particular to a combined-distributed variant aircraft. Background Art

[0002] Existing airdropped cargo is mostly spread by parachute, which is a large target and easy to be discovered by terrorists. In addition, the aircraft in the prior art are mostly assembled by using multiple single-wing structures. There is no combination or separation between single wings, and the functions are limited. The wings cannot be folded. During transportation, it occupies a large space and has low practicality, which cannot meet the complex and changeable mission requirements. Therefore, it is of great significance to develop an aircraft with foldable wings, small targets, and the ability to combine and separate and have variant capabilities. Utility Model Content

[0003] In view of the existing deficiencies, the utility model provides a combined-distributed variant aircraft to solve the problems raised in the above background technology. The aircraft assembly is composed of multiple single-wing aircraft monomers, and has the advantages of spin stability, long hovering time, strong load capacity, and strong clustering ability.

[0004] In order to achieve the above purpose, the technical solution adopted by the utility model is:

[0005] A combined-distributed variant aircraft comprises four groups of aircraft monomers and a combined-separation system; each group of aircraft monomers consists of a load compartment and a wing, the wing and the load compartment are hinged by a connecting rod mechanism, and the wing can rotate around the hinge; the combined-separation system comprises a rubber band, a rubber band limit block, a limit connecting rod, a central limit block, a central motor and a load compartment central positioning block, the central motor is located between the four groups of load compartments, the central motor is embedded in the load compartment central positioning block, the load compartment central positioning block is buckled and connected to the load compartment, the central motor output end is equipped with a central limit block, the limit connecting rod passes through the load compartment near the top, and one end thereof is in contact with the central limit block, and the other end is hinged with a rubber band limit block, and a rubber band is sleeved on the outer side of the rubber band limit block.

[0006] Furthermore, when the aircraft is in an assembled state, the load bin on each single unit is in a square structure surrounding the central motor and is positioned and connected by the central positioning block of the load bin. A trapezoidal groove is provided at the top edge of the load bin, and the rubber band limit block is embedded in the trapezoidal groove, and the rubber band limit block is hinged to the trapezoidal groove. A square groove is provided near the top of the load bin, and the limit connecting rod passes through the square groove.

[0007] Furthermore, the connecting rod mechanism consists of a hinged head, a limiting groove, a lower buckle, a spring and a wing root connecting rod. The hinged head is fixed on the load bin annular surface. A limiting groove is fixed on the load bin annular surface on the lower side of the hinged head. A lower buckle is hinged inside the limiting groove. A spring is fixed between the lower buckle and the load bin annular surface. The wing root connecting rod is fixed at the root of the wing, and the wing root connecting rod is hinged to the hinged head.

[0008] Furthermore, a wing root buckle with a hook-shaped structure is fixedly provided on the outer side of the wing root connecting rod, and the wing root buckle can be buckled and connected with the lower buckle.

[0009] Furthermore, a long connecting rod is hinged at the root of the wing, and the long connecting rod is arranged on the right side of the wing root connecting rod, a short connecting rod is hinged at the end of the long connecting rod, a servo is arranged on the load bin annular surface on the right side of the limiting groove, and the lower end of the short connecting rod is fixedly connected to the output end of the servo.

[0010] Furthermore, a brushless motor is embedded on the wing, a propeller is mounted on the output end of the brushless motor, and the brushless motor drives the propeller to rotate to provide power for the aircraft.

[0011] Furthermore, the center limit block is arranged as a cross-shaped structure, and the convex part on the center limit block is an arc-shaped structure with a side surface that is concave inwardly, and the end of the limit connecting rod close to the center limit block is an arc-shaped structure, and this end is inserted into the inwardly concave arc-shaped structure on the center limit block and is connected with it in abutment.

[0012] Compared with the prior art, the utility model has the following beneficial effects:

[0013] 1. The aircraft of the utility model not only has foldable wings and a small size, but also has propellers on the wings that can provide power to increase aerodynamic lift and thus increase the effective load; each aircraft unit is controlled by a combination and separation device to control the combination and separation of the aircraft units, thereby realizing the coordinated deployment of cargo and the expansion of environmental situation awareness.

[0014] 2. The aircraft assembly of the utility model is composed of multiple single-wing aircraft monomers arranged in a circular combination. After being spread, they can be combined and flown or fly alone like a wing fruit. The multi-wing layout of the aircraft assembly has greater lift than a single body, can produce stable spin, and ensure a longer hovering time. At the same time, propellers are added to the wings to provide thrust, so that the spin speed is accelerated to produce greater lift to maintain the hovering state. At the same time, the acceleration of the spin speed can also accelerate the detection and scanning speed of the detector in the payload compartment. During the falling process, the load, detection, maneuvering, clustering and other functions can be jointly realized, and at the right time, it can be self-separated into multiple single-wing aircraft monomers; the aircraft monomer has a single-wing layout of a bionic wing fruit, which can also produce stable spin and slowly fall. At the same time, the propeller on the wing can also provide spin power in time, and can independently realize the functions of load, detection, maneuvering, clustering and other functions. It is expected to achieve collaborative search and collaborative deployment of goods at a lower cost, which can effectively improve the survivability and overall efficiency of drone clusters.

[0015] 3. The wings of the utility model can be folded together, which can reduce the aerodynamic resistance during gliding and the space occupied during transportation; the wing root connecting rod at the wing root and the long connecting rod and short connecting rod on the load compartment together constitute a connecting rod mechanism, and the connecting rod is driven by the servo fixed on the load body to control the rotation of the wing. In the spinning state, the wing is controlled by the servo fixed on the load body to open, and the wing is locked when it is opened to the specified position to ensure the stability of the aircraft during flight.

[0016] 4. The utility model adopts a separate combination-separation control device, which can release the limit connecting rod on each aircraft unit at the same time by rotating the central positioning block connected to the output shaft of the central motor, so that the separation control has a high degree of synchronization.

[0017] 5. The utility model is based on the flight principle of maple seeds and proposes a combined structure of a monoplane aircraft. The aerodynamic structure of the combined aircraft is a symmetrical aerodynamic layout composed of a single-wing asymmetric aerodynamic layout. A propeller motor is added to the wing to provide power, so that the combined aircraft has a faster rotation acceleration, greater aerodynamic lift, and longer hovering time. Compared with general single-rotor aircraft, it has the advantages of lightweight, low power consumption, stability, and long endurance time. It also provides a new idea for the future development of aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall structure of the utility model when the rear wings are unfolded.

[0019] Figure 2 for Figure 1 A schematic diagram of the enlarged structure at point A in the middle.

[0020] Figure 3It is a structural schematic diagram of the utility model in the assembled rear wing folded state.

[0021] Figure 4 It is a front cross-sectional view of the utility model.

[0022] Figure 5 It is a structural schematic diagram of the aircraft monomer in the utility model.

[0023] Figure 6 It is a structural schematic diagram of the wing in the utility model.

[0024] In the figure: 1. Payload compartment; 101. Hinge; 102. Limiting groove; 103. Square groove; 104. Trapezoidal groove; 2. Wing; 201. Wing root connecting rod; 202. Wing root buckle; 203. Propeller; 204. Brushless motor; 3. Payload compartment center positioning block; 4. Center motor; 5. Center limiting block; 6. Limit connecting rod; 7. Rubber band limiting block; 8. Rubber band; 9. Long connecting rod; 10. Short connecting rod; 11. Lower buckle; 12. Spring; 13. Servo. DETAILED DESCRIPTION

[0025] The following will be combined with the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0026] Example:

[0027] like Figures 1 to 6As shown, a combination-distributed variant aircraft includes four groups of aircraft monomers and a combination-separation system; each group of aircraft monomers is composed of a payload compartment 1 and a wing 2, the wing 2 is hinged to the payload compartment 1 through a connecting rod mechanism, and the wing 2 can rotate around the hinge; the combination and separation system includes a rubber band 8, a rubber band limit block 7, a limit connecting rod, a center limit block 5, a center motor 4 and a payload compartment center positioning block 3, the center motor 4 is located between the four groups of payload compartments 1, the center motor 4 is embedded in the payload compartment center positioning block 3, the payload compartment center positioning block 3 is buckled and connected to the payload compartment 1, and a center limit is assembled on the output end of the center motor 4 Block 5, the limit connecting rod 6 passes through the load compartment 1 near the top, and one end of it is connected to the central limit block 5, and the other end is hinged with a rubber limit block 7, and a rubber band 8 is sleeved on the outer side of the rubber limit block 7. This design solves the problems that the existing airdrop cargo is mostly spread by parachute, the target is large, and it is easy to be discovered by terrorists, and the aircraft in the prior art mostly uses multiple single-wing structures for simple assembly, there is no combination or split connection between the single wings, the function is limited, and the wing 2 is not foldable. During transportation, it occupies a large space, has low practicality, and cannot meet the complex and changeable mission requirements.

[0028] The elastic force applied by the rubber band 8 to the aircraft monomer is greater than the maximum centrifugal force when the combined aircraft rotates, so that the separation of the combined aircraft can only be controlled by the central motor 4.

[0029] When the aircraft is in the assembled state, the load compartment 1 on each single body is in a square structure surrounding the central motor 4, and is positioned and connected by the load compartment center positioning block 3. A trapezoidal groove 104 is opened at the top edge of the load compartment 1, and the rubber band limit block 7 is embedded in the trapezoidal groove 104, and the rubber band limit block 7 is hinged to the trapezoidal groove 104. A square groove 103 is opened near the top of the load compartment 1, and the limit connecting rod 6 passes through the square groove 103.

[0030] The connecting rod mechanism is composed of an articulated joint 101, a limiting groove 102, a lower buckle 11, a spring 12 and a wing root connecting rod 201. The articulated joint 101 is fixed on the annular surface of the load compartment 1. The limiting groove 102 is fixed on the annular surface of the load compartment 1 at the lower side of the articulated joint 101. The lower buckle 11 is hinged inside the limiting groove 102. A spring 12 is fixed between the lower buckle 11 and the annular surface of the load compartment 1. The wing root connecting rod 201 is fixed at the root of the wing 2, and the wing root connecting rod 201 is hinged to the articulated joint 101. The wing 2 and the load compartment 1 are movably connected by the provided connecting rod mechanism, so as to realize the rotation adjustment of the angle of the wing 2.

[0031] A hook-shaped wing root buckle 202 is fixedly arranged on the outside of the wing root connecting rod 201, and the wing root buckle 202 can be buckled and connected with the lower buckle 11. The wing root buckle 202 provided in this design can cooperate with the lower buckle 11 to lock the wing 2, so that the wing 2 is positioned at the current angle. The four groups of wings 2 are gathered and opened, and the angle is 90°. When the wing 2 is opened, the wing root buckle 202 will press down the buckle 11. When the buckle is buckled, the buckling force of the lower buckle 11 is provided by the spring 12. After buckling, the angle of the wing 2 remains unchanged.

[0032] A long connecting rod 9 is hinged at the root of the wing 2, and the long connecting rod 9 is arranged on the right side of the wing root connecting rod 201. A short connecting rod 10 is hinged at the end of the long connecting rod 9. A steering gear 13 is arranged on the annular surface of the load compartment 1 on the right side of the limiting groove 102, and the lower end of the short connecting rod 10 is fixedly connected to the output end of the steering gear 13. The steering gear 13 drives the short connecting rod 10 to rotate, and the short connecting rod 10 drives the long connecting rod 9 to rotate, thereby driving the wing 2 to rotate relative to the load compartment 1 to change the angle. The wing 2 and the load compartment 1 can be folded together at 180°, or they can be unfolded to a position perpendicular to the axis of the load compartment 1 under the action of the steering gear 13 and limited and locked by the engagement of the wing root buckle 202 and the lower buckle 11.

[0033] A brushless motor 204 is embedded on the wing 2, and a propeller 203 is installed on the output end of the brushless motor 204. The brushless motor 204 drives the propeller 203 to rotate to provide power for the aircraft. The rotation of the propeller 203 can generate thrust. Under the action of the thrust, the combined-distributed variant aircraft spins around its center of mass, thereby obtaining lift.

[0034] The central limit block 5 is set to a cross-shaped structure, and the side of the protrusion on the central limit block 5 is an arc-shaped structure that is concave inwards. The end of the limit link 6 close to the central limit block 5 is an arc-shaped structure, and this end is inserted into the inwardly concave arc-shaped structure on the central limit block 5 and is connected with it. When the rubber band 8 applies force to the rubber band limit block 7, the limit link 6 supports the rubber band limit block 7, and the central limit block 5 limits the limit link 6; the central motor 4 drives the central limit block 5 to release the limit link 6 to release the limit block 7 from limiting the rubber band 8, thereby releasing the elastic force of the rubber band 8 to release the aircraft monomer, and the aircraft monomer enters the distribution mode from the combination mode.

[0035] The working principle of this combined-distributed variant aircraft:

[0036] 1. When the aircraft is not spreading, the aircraft is in a combined state and the four wings 2 of the aircraft are folded together to achieve a smaller occupied space; after spreading at high altitude, the four wings 2 of the aircraft are unfolded for gliding;

[0037] 2. When the aircraft is in the combined gliding state, it has less aerodynamic resistance than when the wings 2 are open, and can achieve faster gliding speed and gliding distance; after the aircraft flies to the target airspace, the servo 13 provides torque to make the four wings 2 open to the specified position, and the wing root buckle 202 cooperates with the lower buckle 11 to lock and limit the wing 2, and then the wing 2 always remains perpendicular to the axis of the load compartment 1. After the wings 2 are unfolded, the aerodynamic resistance increases, and the aircraft is in the deceleration stage. At the same time, due to the aerodynamic force of the wings 2, the aircraft will slightly rotate around its own central axis; when the speed decreases to a certain value, the central axis of the aircraft is perpendicular to the ground. At this time, the aircraft rotates around its central axis under the aerodynamic force of its wings 2, and the overall flight altitude slowly decreases;

[0038] 3. The propeller 203 on the wing 2 is driven by the brushless motor 204 to rotate simultaneously to provide the aircraft with thrust for rotating around the central axis, so that the aircraft speed is increased, the lift provided by the wing 2 is increased, and the aircraft will maintain or increase the flight altitude to achieve long-term stay in the air and reconnaissance detection;

[0039] 4. When the target appears, the rubber band 8 is quickly released through the combination-separation system, so that the combined aircraft is quickly distributed into four aircraft monomers that spin around their respective aerodynamic centers under the action of the rotating centrifugal force. In this process, the central motor 4 drives the central limit block 5 to rotate 45 degrees, so that the end of the limit connecting rod 6 slides into the arc structure that is concave inwardly on the central limit block 5, and the upper part of the rubber band limit block 7 is driven inward by the limit connecting rod 6. The supporting force received by the rubber band 8 disappears, and it falls off from the rubber band limit block 7 under the action of its own elastic force, so that the load compartment 1 is separated. The central limit block 5, the load compartment center positioning block 3, the central motor 4 and the rubber band 8 complete their work tasks and are discarded. At this point, the aircraft enters the distributed working state.

[0040] In summary, the utility model has a large detection range and a large aerodynamic lift, can conduct collaborative search and collaborative deployment of cargo at low cost, and can effectively improve the survivability and overall effectiveness of the drone cluster.

[0041] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not limitations on the implementation methods of the present invention. For ordinary technicians in the relevant field, other different forms of changes or modifications can be made on the basis of the above description. It is impossible to list all the implementation methods here. All obvious changes or modifications derived from the technical solution of the present invention are still within the protection scope of the present invention.

Claims

1. A combined-distributed variant aircraft, characterized in that: include Four sets of aircraft monomers and assembly-separation systems; Each set of aircraft monomers is composed of a load compartment (1) and a wing (2), wherein the wing (2) is hinged to the load compartment (1) via a connecting rod mechanism, and the wing (2) can rotate around the hinge; The combination and separation system comprises a rubber band (8), a rubber band limit block (7), a limit connecting rod (6), a central limit block (5), a central motor (4) and a load bin central positioning block (3), wherein the central motor (4) is located between four groups of load bins (1), the central motor (4) is embedded in the load bin central positioning block (3), the load bin central positioning block (3) is snap-fitted and connected to the load bin (1), the central motor (4) is equipped with a central limit block (5) on the output end, the limit connecting rod (6) passes through the load bin (1) near the top, and one end of the limit connecting rod is in contact with the central limit block (5), and the other end is hinged with the rubber band limit block (7), and the rubber band limit block (7) is sleeved with a rubber band (8) on the outside.

2. The combined-distributed morphing aircraft according to claim 1, characterized in that: When the aircraft is in an assembled state, the load compartment (1) on each single body is in a square structure surrounding the central motor (4) and is positioned and connected by the load compartment central positioning block (3); a trapezoidal groove (104) is provided at the top edge of the load compartment (1); the rubber band limiting block (7) is embedded in the trapezoidal groove (104), and the rubber band limiting block (7) is hinged to the trapezoidal groove (104); a square groove (103) is provided near the top of the load compartment (1), and the limiting connecting rod (6) passes through the square groove (103).

3. The combined-distributed morphing aircraft according to claim 1, characterized in that: The connecting rod mechanism consists of a hinge joint (101), a limiting groove (102), a lower buckle (11), a spring (12) and a wing root connecting rod (201); the hinge joint (101) is fixedly arranged on the annular surface of the load compartment (1); a limiting groove (102) is fixedly arranged on the annular surface of the load compartment (1) at the lower side of the hinge joint (101); a lower buckle (11) is hingedly arranged inside the limiting groove (102); a spring (12) is fixedly arranged between the lower buckle (11) and the annular surface of the load compartment (1); the wing root connecting rod (201) is fixedly arranged at the root of the wing (2), and the wing root connecting rod (201) is hingedly connected to the hinge joint (101).

4. The combined-distributed morphing aircraft according to claim 3, characterized in that: A wing root buckle (202) with a hook-shaped structure is fixedly disposed on the outer side of the wing root connecting rod (201), and the wing root buckle (202) can be buckled and connected with the lower buckle (11).

5. The combined-distributed morphing aircraft according to claim 4, characterized in that: A long connecting rod (9) is hingedly connected to the root of the wing (2), and the long connecting rod (9) is arranged on the right side of the wing root connecting rod (201). A short connecting rod (10) is hingedly connected to the end of the long connecting rod (9). A steering gear (13) is arranged on the annular surface of the load compartment (1) on the right side of the limiting groove (102), and the lower end of the short connecting rod (10) is fixedly connected to the output end of the steering gear (13).

6. The combined-distributed morphing aircraft according to claim 1, characterized in that: A brushless motor (204) is embedded on the wing (2), a propeller (203) is mounted on the output end of the brushless motor (204), and the brushless motor (204) drives the propeller (203) to rotate to provide power for the aircraft.

7. The combined-distributed morphing aircraft according to claim 1, characterized in that: The central limiting block (5) is arranged as a cross-shaped structure, and the convex part of the central limiting block (5) is an arc-shaped structure with a side surface that is inwardly concave; one end of the limiting connecting rod (6) close to the central limiting block (5) is an arc-shaped structure, and the end is inserted into the inwardly concave arc-shaped structure on the central limiting block (5) and is in contact with and connected therewith.

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