CN210047624U - Roll control structure of a new type of flapping aircraft - Google Patents

Abstract

The utility model discloses a roll control structure of a novel flapping aircraft, comprising a rocker arm, a crank, a push-pull rod lengthening device, a push-pull rod, a first connecting rod, a winglet rod, a gear, a main and auxiliary connecting rod, a small wing There are two gears, one end of the rocker arm is connected to the gear, the other end of the rocker arm is connected to one end of the crank, and the other end of the crank is connected to one end of the push-pull rod lengthening device. , the other end of the push-pull rod lengthening device is connected with one end of the push-pull rod, the winglet fixing rod and the shoulder wing rod are arranged side by side, and the two ends of the winglet fixing rod and the shoulder wing rod are connected with a first connecting rod, and the winglet fixing rod , The shoulder wing rod and the first connecting rod form a four-link structure, the other end of the push-pull rod is connected with one end of the main and auxiliary connecting rods, the shoulder wing rod and the push-pull rod are arranged side by side, and one side of the shoulder wing rod is connected with the main and auxiliary connecting rods. The other end is connected, the other side of the shoulder wing rod is connected with the push-pull rod lengthening device, and the winglet rod is connected with the winglet fixing rod.

Description

Roll control structure of a new type of flapping aircraft

technical field

The utility model relates to the field of aviation technology, in particular to a roll control structure of a novel flapping-wing aircraft.

Background technique

At present, the roll of the flapper is controlled by the change of the tail angle or the change of the lift caused by the twist of the flapper. However, the above methods all have complex structures. The most important thing is that the yaw motion must be generated during the roll. Control is difficult, and at low speeds, the tail control efficiency is extremely low due to the low forward flight speed.

SUMMARY OF THE INVENTION

In order to solve the above technical problems, the utility model provides a roll control structure of a novel flapping-wing aircraft.

The utility model adopts the following technical solutions: a roll control structure of a novel flapping aircraft, comprising a rocker arm, a crank, a push-pull rod lengthening device, a push-pull rod, a first connecting rod, a winglet rod, a gear, a main and auxiliary connecting rod , winglet fixing rod, shoulder wing rod, the gears are provided with two, and the gears are meshed and connected, one end of the rocker arm is connected with the gear, the other end of the rocker arm is connected with one end of the crank, the other end of the crank is connected with the pusher One end of the pull rod lengthening device is connected, the other end of the push-pull rod lengthening device is connected with one end of the push-pull rod, the winglet fixing rod and the shoulder wing rod are arranged side by side, and the two ends of the winglet fixing rod and the shoulder wing rod A first connecting rod is connected, the winglet fixing rod, the shoulder wing rod, and the first connecting rod form a four-link structure, the other end of the push-pull rod is connected with one end of the main and auxiliary connecting rods, and the shoulder wing rod is connected with the push-pull rod Arranged side by side, one side of the shoulder wing rod is connected with the other end of the main and auxiliary connecting rods, the other side of the shoulder wing rod is connected with the push-pull rod lengthening device, and the winglet rod is connected on the winglet fixing rod ;

The push-pull rod lengthening device includes a sleeve, a gear transmission box, a rack, a brushed motor, and a worm. The rack and the worm are all arranged in the sleeve, and one side of the rack is meshed with the worm, and the other side of the rack. One side is connected with the push-pull rod, the brushed motor is connected with the gear transmission case, and the gear transmission case is fixedly mounted on the sleeve.

Preferably, the center of the gear is set on the fixed point of the frame, and the rocker arm is linked with the gear through the fixed point of the frame.

Preferably, one side of the shoulder wing rod is connected with one end of the push-pull rod lengthening device through a second connecting rod.

Preferably, the upper surface of the gear box is connected to one side of the sleeve through the motor fixing seat.

Preferably, the other side of the sleeve is provided with a worm fixing box, the worm fixing box is fixedly connected to the sleeve through a worm fixing member, and the worm fixing box is used to limit the displacement of the worm in other directions except rotation.

Compared with the prior art, the utility model has the advantages: the utility model can solve the problem of realizing a more reliable and effective roll control scheme when the double-joint flapping-wing aircraft takes off and at a low forward flying speed, and avoids the need for the roll control. The coupling effect between the differential torsion of the winglets and the thrust generated by the linked torsion and flutter of the winglets improves the pitch and roll control law of the aircraft during take-off or low-speed gliding flight, and enhances the anti-crosswind. Performance, compared to controlling aileron twist or winglet deflection, roll control can be achieved at low forward speeds with higher efficiency.

Description of drawings

Fig. 1 is the transmission structure diagram of the present utility model.

Figure 2 is a schematic diagram of the mechanism of the present utility model.

3 is a schematic diagram of the push-pull rod lengthening device of the present invention.

Description of reference numerals: 1, rocker arm 2, crank 3, push-pull rod lengthening device 4, push-pull rod 5, first connecting rod 6, winglet rod 7, frame fixing point 8, gear 9, main and auxiliary connecting rods 10, Small wing fixing rod 11, shoulder wing rod 12, motor fixing seat 13, sleeve 14, gear box 16, motor 17, worm fixing part 18, worm fixing box 19, worm.

Detailed ways

The preferred embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, and the protection scope of the present invention can be more clearly defined.

In this embodiment, it is to be understood that the terms "middle", "upper", "lower", "top", "right side", "left end", "upper", "back", "middle", etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention, rather than indicating or implying that the indicated device or element must have a specific orientation, be constructed and operated in a specific orientation , so it should not be construed as a limitation of the present invention.

Please refer to Figure 1, Figure 2, Figure 3, a roll control structure of a new type of flapping aircraft, including a rocker arm (1), a crank (2), a push-pull rod lengthening device (3), a push-pull rod (4), The first connecting rod (5), the winglet rod (6), the gear (8), the main and auxiliary connecting rods (9), the winglet fixing rod (10), the shoulder wing rod (11), the gear (8) is provided with There are two, and the gears (8) are meshed and connected. One end of the rocker arm (1) is connected to the gear (8), and the other end of the rocker arm (1) is connected to one end of the crank (2). The other end is connected with one end of the push-pull rod lengthening device (3), the other end of the push-pull rod lengthening device (3) is connected with one end of the push-pull rod (4), the winglet fixing rod (10), the shoulder wing The rods (11) are arranged side by side, and the two ends of the winglet fixing rod (10) and the shoulder wing rod (11) are connected with a first connecting rod (5), the winglet fixing rod (10), the shoulder wing rod (11) ), the first connecting rod (5) forms a four-link structure, the other end of the push-pull rod (4) is connected with one end of the main and auxiliary connecting rods (9), and the shoulder wing rod (11) is side by side with the push-pull rod (4) Arrangement, one side of the shoulder wing rod (11) is connected with the other end of the main and auxiliary connecting rods (9), and the other side of the shoulder wing rod (11) is connected with the push-pull rod lengthening device (3), so The winglet rod (6) is connected to the winglet fixing rod (10);

The push-pull rod lengthening device (3) includes a sleeve (13), a gear transmission case (14), a rack, a brushed motor (16), and a worm (19), and the rack and worm (19) are provided with Inside the sleeve (13), one side of the rack is meshed with the worm (19), the other side of the rack is connected with the push-pull rod (4), and the brushed motor (16) is connected with the gear box (14) , and the gear box (14) is fixedly mounted on the sleeve (13).

Preferably, the center of the gear (8) is set on the frame fixing point (7), and the rocker arm (1) is linked with the gear (8) through the frame fixing point (7).

Preferably, one side of the shoulder wing rod (11) is connected with one end of the push-pull rod lengthening device (3) through a second connecting rod.

Preferably, the upper surface of the gear box (14) is connected to one side of the sleeve (13) through the motor fixing seat (12).

Preferably, the other side of the sleeve (13) is provided with a worm fixing box (18), the worm fixing box (18) is fixedly connected to the sleeve (13) through the worm fixing piece (17), and the worm fixing box (18) It is used to limit the displacement of the worm (19) in other directions except rotation.

The utility model is realized in this way: through the fixed gear (8) installed on the fixed point (7) of the frame, the rocker arm (1) and the gear (8) are linked to drive the swing of the crank (2), through the four-link structure , drive the shoulder wing bar (11) and the winglet bar (6) to flutter, thereby driving the shoulder wing and the winglet fixed on it to flutter. The push-pull rod lengthening device (3) is connected with the crank (2), the push-pull rod lengthening device (3) changes the push-pull rod (4) to move in the sleeve (13), and the quadrilateral structure composed of the connecting rod (5) is used The movement of the push-pull rod is transformed into the change of the angle between the winglet rod 6 and the shoulder wing rod 11 . When the two sides are symmetrical, the flapper does not roll; when the two sides are asymmetrical, the flapper rolls accordingly. The brushed motor (16) fixed on the motor holder (12) outputs the torque, and the torque is transmitted to the worm (19) through the reduction gear box (14), and the worm (19) converts the torque by meshing with the rack. For the displacement of the rack, the rack is connected to the push-pull rod (4), and the push-pull rod (4) is driven to reciprocate in the sleeve (13) by the rack, so that the length of the push-pull rod (4) changes, so as to cause The angles of the shoulder wings (11) and the winglets (6) change. When the angles of the shoulder wings and winglets on both sides are asymmetrical, the lift generated by the flapping on both sides will change, resulting in a difference in lift. This will make the aircraft roll. The worm fixing member (17) is used to fix the sleeve (13), and the worm fixing box (18) is used to limit the displacement of the worm (19) in other directions except the rotation.

Not limited to this, any changes or substitutions that are not thought of through creative work should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope defined by the claims.

Claims (5)

1. A roll control structure of a novel flapping aircraft, characterized in that it comprises a rocker arm (1), a crank (2), a push-pull rod lengthening device (3), a push-pull rod (4), a first connecting rod ( 5), winglet rod (6), gear (8), main and auxiliary connecting rods (9), winglet fixing rod (10), shoulder wing rod (11), the gears (8) are provided with two, and The gears (8) are meshed and connected, one end of the rocker arm (1) is connected to the gear (8), the other end of the rocker arm (1) is connected to one end of the crank (2), and the other end of the crank (2) is connected to the push-pull rod One end of the lengthening device (3) is connected, the other end of the push-pull rod lengthening device (3) is connected with one end of the push-pull rod (4), the winglet fixing rod (10) and the shoulder wing rod (11) are juxtaposed The two ends of the winglet fixing rod (10) and the shoulder wing rod (11) are connected with a first connecting rod (5), the winglet fixing rod (10), the shoulder wing rod (11), the first connecting rod The rod (5) forms a four-link structure, the other end of the push-pull rod (4) is connected with one end of the main and auxiliary connecting rods (9), and the shoulder wing rod (11) is arranged side by side with the push-pull rod (4). One side of the wing rod (11) is connected with the other end of the main and auxiliary connecting rods (9), the other side of the shoulder wing rod (11) is connected with the push-pull rod lengthening device (3), and the small wing rod ( 6) Connect to the winglet fixing rod (10); The push-pull rod lengthening device (3) includes a sleeve (13), a gear transmission case (14), a rack, a brushed motor (16), and a worm (19), and the rack and worm (19) are provided with Inside the sleeve (13), one side of the rack is meshed with the worm (19), the other side of the rack is connected with the push-pull rod (4), and the brushed motor (16) is connected with the gear box (14) , and the gear box (14) is fixedly mounted on the sleeve (13). 2. The roll control structure of the novel flapping-wing aircraft according to claim 1, wherein the center of the gear (8) is set on the frame fixing point (7), and the rocker arm (1) passes through the frame The fixed point (7) is linked with the gear (8). 3. The roll control structure of the novel flapping wing aircraft according to claim 1, wherein one side of the shoulder wing rod (11) passes through the second connecting rod and one end of the push-pull rod lengthening device (3) connect. 4. The roll control structure of the novel flapping-wing aircraft according to claim 1, wherein the upper surface of the gear box (14) is connected to one side of the sleeve (13) through the motor holder (12) . 5. The roll control structure of the novel flapping-wing aircraft according to claim 1, wherein the other side of the sleeve (13) is provided with a worm fixing box (18), and the worm fixing box (18) is fixed by a worm The piece (17) is fixedly connected with the sleeve (13), and the worm fixing box (18) is used to limit the displacement of the worm (19) in other directions except the rotation.

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