Full-motion horizontal tail amplification steerage control mechanism of glider

Abstract

The utility model discloses a glider full-motion horizontal tail amplification steerage control mechanism, which comprises horizontal tails, side plates and a special-shaped rocker arm, the two horizontal tails are arranged at the tail part of a glider body, the special-shaped rocker arm is arranged between the two horizontal tails, the special-shaped rocker arm is clamped between the two side plates, and the special-shaped rocker arm is provided with a spar groove, a rotating shaft hole, a rocker arm limiting groove and a steel wire hole. The steel wire hole is connected with a servo steering engine through a push-pull steel wire. The horizontal tail is reasonable and ingenious in structural design, the servo steering engine is used for controlling rotation of the special-shaped rocker arm, so that the turnover angle of the horizontal tail is changed, the flight angle range of the horizontal tail is enlarged, the controllability of the glider is enhanced, the horizontal tail can be close to the vertical state, the glider vertically descends, and the flight space needed by landing of the glider is reduced.

Description

Technical Field

[0001] The utility model relates to a full-moving horizontal tail amplification rudder effect control mechanism for a glider. Background Art

[0002] During the takeoff and landing process of a glider model, in order to control the flight direction of the airframe, ailerons are arranged on the wings. When the glider lands, by controlling the elevation angle of the ailerons, the glider can dive. The maneuverability of the glider has certain limitations and has relatively high requirements for the occupied space required for landing. Content of the Utility Model

[0003] In order to overcome the above deficiencies, the utility model provides a full-moving horizontal tail amplification rudder effect control mechanism for a glider, making the glider have stronger maneuverability.

[0004] To achieve this purpose, the structure adopted by the utility model is: a full-moving horizontal tail amplification rudder effect control mechanism for a glider, including a horizontal tail, side plates and a special-shaped rocker arm. Two horizontal tails are symmetrically arranged on both sides of the tail of the airframe. A wing beam is inserted between the two horizontal tails. A special-shaped rocker arm is arranged between the two horizontal tails. The special-shaped rocker arm is connected to the side plates at the tail of the airframe. The special-shaped rocker arm and the horizontal tail are connected to each other through a limiting rod and a connecting block. A servo actuator is arranged at the head of the airframe. The servo actuator is connected to the special-shaped rocker arm through a push-pull wire.

[0005] A wing beam groove, a rotating shaft hole, a rocker arm limiting groove and a wire hole are arranged on the special-shaped rocker arm. The wing beam passes through the wing beam groove; the special-shaped rocker arm is connected to the two side plates through a rotating shaft, and the rotating shaft passes through the rotating shaft hole; the limiting rod passes through the rocker arm limiting groove.

[0006] The connecting block is a long strip-shaped block structure. The connecting block is arranged between the side plate and the horizontal tail. A wing beam hole and a limiting hole are arranged on the connecting block. The two ends of the limiting rod are respectively inserted into the limiting holes on the two connecting blocks on both sides; the wing beam passes through the wing beam hole and is connected to the horizontal tail. Rivets are arranged on the connecting block to fix the wing beam; a plurality of cutouts are arranged on the connecting block, and convex blocks corresponding to the cutouts are arranged on the surface of the horizontal tail in contact with the connecting block for mating connection.

[0007] An arc-shaped groove is arranged on the side plate, and the limiting rod passes through the arc-shaped groove.

[0008] Its beneficial effects are: the structure design of the utility model is reasonable and ingenious. By using the servo actuator to control the rotation of the special-shaped rocker arm, the flipping angle of the horizontal tail is changed, the flight angle range of the horizontal tail is increased, the maneuverability of the glider is enhanced, the horizontal tail can be close to the vertical state, enabling the glider to descend vertically, and reducing the flight space required for the glider to land. Description of the Drawings

[0009] The utility model will be described by way of examples with reference to the accompanying drawings, where:

[0010] Figure 1 It is a schematic diagram of the mechanism of the present utility model installed on a glider;

[0011] Figure 2 It is a three-dimensional structure diagram of the present utility model;

[0012] Figure 3 It is a partial structure diagram of the present utility model;

[0013] Figure 4 It is a schematic diagram of the special-shaped rocker arm structure;

[0014] Figure 5 It is a schematic diagram of the connecting block structure;

[0015] Figure 6 It is a schematic diagram of the horizontal tail in the horizontal state;

[0016] Figure 7 It is a schematic diagram of the horizontal tail in the elevation angle state. Detailed implementation manners

[0017] Now, the present utility model will be further described in detail with reference to the accompanying drawings. These drawings are all simplified schematic diagrams, only illustrating the basic structure of the present utility model in a schematic manner, so they only show the components related to the present utility model.

[0018] In the description of the utility model, it should be noted that the orientation or positional relationship indicated by the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, so it cannot be understood as a limitation to the present utility model. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0019] In the description of the utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "provided with", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements; the fixed connection can be welding or bonding. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific situations.

[0020] Such as Figures 1 - 3The full-moving horizontal tail amplification rudder effect control mechanism of the glider shown includes a horizontal tail 2, side plates 6, and a special-shaped rocker arm 3. Two horizontal tails 2 are symmetrically arranged on both sides of the tail of the fuselage 1. A wing beam 8 is inserted between the two horizontal tails 2. A special-shaped rocker arm 3 is arranged between the two horizontal tails 2. The special-shaped rocker arm 3 is connected to the side plates 6 at the tail of the fuselage 1. The special-shaped rocker arm 3 and the horizontal tail 2 are connected to each other through a limit rod 10 and a connecting block 7. A servo actuator 5 is arranged at the head of the fuselage 1. The servo actuator 5 is connected to the special-shaped rocker arm 3 through a push-pull wire 4.

[0021] As Figure 4 shown, a wing beam groove 31, a rotating shaft hole 32, a rocker arm limit groove 34, and a wire hole 33 are arranged on the special-shaped rocker arm 3. The wing beam 8 passes through the wing beam groove 31. The wing beam groove 31 is a butterfly-shaped through hole symmetrically arranged up and down. The special-shaped rocker arm 3 is connected to the two side plates 6 through a rotating shaft 9. The rotating shaft 9 passes through the rotating shaft hole 32. The special-shaped rocker arm 3 can rotate around the rotating shaft 9. The limit rod 10 passes through the rocker arm limit groove 34. The limit groove 34 is an oblong through hole. A sleeve is sleeved on the outer side of one end of the wing beam 8 between the two side plates 6. The diameter of the sleeve is adjusted according to needs. The sleeve is sleeved in the wing beam groove 31 to limit the movement of the wing beam 8 within the range of the wing beam groove 31.

[0022] As Figure 5 shown, the connecting block 7 is a long strip-shaped block structure. The connecting block 7 is arranged between the side plate 6 and the horizontal tail 2. A wing beam hole 73 and a limit hole 74 are arranged on the connecting block 7. The two ends of the limit rod 10 are respectively inserted into the limit holes 74 on the two connecting blocks 7. The wing beam 8 passes through the wing beam hole 73 and is connected to the horizontal tail 2. A rivet 75 is arranged on the connecting block 7 to fix the wing beam 8. A plurality of cutouts 72 are arranged on the connecting block 7. A convex block corresponding to the cutout 72 is arranged on the surface of the horizontal tail 2 in contact with the connecting block 7 for mating connection. The connecting block 7 drives the horizontal tail 2 to rotate around the wing beam 8.

[0023] An arc-shaped groove is arranged on the side plate 6. The limit rod 10 passes through the arc-shaped groove.

[0024] The servo actuator 5 is connected to the wire 4 through an eccentric connecting piece to achieve the push-pull effect of the wire 4 during rotation. When the wire 4 is not pushed or pulled, the horizontal tail 2 remains in a horizontal state. As Figure 6 shown, at this time, the glider maintains level flight. When the wire 4 is pushed, the special-shaped rocker arm 3 rotates around the rotating shaft 9. The horizontal tail 2 is driven by the limit rod 10 to flip to the limit state. As Figure 7 shown, at this time, the horizontal tail 2 is in an almost vertical state. Therefore, the glider loses the aerodynamic lift and will not continue to glide but enters a deep stall vertical descent. At the same time, during the descent, by pulling the special-shaped rocker arm 3, it can be easily recovered, enabling the glider to maintain effective operation in various states and achieving highly maneuverable flight.

[0025] Based on the inspiration of the present utility model, through the above description, relevant staff can completely make various changes and modifications without departing from the technical idea of this utility model. The technical scope of this utility model is not limited to the content in the specification, and its technical scope must be determined according to the scope of the claims.

Claims

1. A full-moving horizontal tail amplifying rudder effect control mechanism for a glider, characterized in that: The invention comprises a horizontal tail (2), a side plate (6) and a special-shaped rocker arm (3). Two horizontal tails (2) are symmetrically arranged on both sides of the tail of a machine body (1). A wing beam (8) is inserted between the two horizontal tails (2). A special-shaped rocker arm (3) is arranged between the two horizontal tails (2). The special-shaped rocker arm (3) is connected to the side plate (6) at the tail of the machine body (1). The special-shaped rocker arm (3) and the horizontal tail (2) are connected to each other through a limit rod (10) and a connecting block (7). A servo steering engine (5) is arranged at the head of the machine body (1). The servo steering engine (5) is connected to the special-shaped rocker arm (3) through a push-pull steel wire (4).

2. The glider full-moving horizontal tail amplified rudder effect control mechanism according to claim 1, characterized in that: The special-shaped rocker arm (3) is provided with a wing beam groove (31), a rotating shaft hole (32), a rocker arm limiting groove (34) and a wire hole (33); the wing beam (8) passes through the wing beam groove (31); the special-shaped rocker arm (3) is connected to the side plates (6) on both sides through a rotating shaft (9); the rotating shaft (9) passes through the rotating shaft hole (32); and the limiting rod (10) passes through the rocker arm limiting groove (34).

3. The glider full-moving horizontal tail amplified rudder effect control mechanism according to claim 1, characterized in that: The connecting block (7) is a long strip block structure. The connecting block (7) is arranged between the side plate (6) and the horizontal tail (2). The connecting block (7) is provided with a spar hole (73) and a limit hole (74). The two ends of the limit rod (10) are respectively inserted into the limit holes (74) on the connecting blocks (7) on both sides. The spar (8) passes through the spar hole (73) to be connected with the horizontal tail (2). Rivets (75) are arranged on the connecting block (7) to fix the spar (8). A plurality of missing blocks (72) are arranged on the connecting block (7). A convex block corresponding to the missing block (72) is arranged on a side of the horizontal tail (2) in contact with the connecting block (7) to be matched and connected therewith.

4. The glider full-moving horizontal tail amplified rudder effect control mechanism according to claim 1, characterized in that: The side plate (6) is provided with an arc-shaped groove, and the limiting rod (10) passes through the arc-shaped groove.

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