Plane multi-connecting-rod type control surface adjusting mechanism

Abstract

The invention belongs to the technical field of aviation, and particularly relates to a plane multi-connecting-rod type control surface adjusting mechanism, a control surface, a connecting rod mechanism and a driving device. The tip end of the control surface is a windward end, and the wide body end of the control surface is a tail end; one side of the wide body end is hinged to the edge of a lower wall plate of the aircraft air inlet, and the other side is hinged to the driving device through a connecting rod mechanism; the connecting rod mechanism comprises a first connecting rod, a second connecting rod, a third connecting rod and a rocker arm, one end of the first connecting rod is hinged to the control surface, the other end of the first connecting rod is hinged to the second connecting rod, the second connecting rod is hinged to the third connecting rod, and the third connecting rod is hinged to the rocker arm; hinge holes in the two ends of the second connecting rod are perpendicular to each other, the same-plane connecting rod mechanism is formed, the space limitation of a low profile is met, the rocker arm forms a lever structure, and the load input of high hinge moment is met.

Description

Technical Field

[0001] The present application belongs to the field of aviation technology, and in particular relates to a planar multi-link type rudder surface adjustment mechanism. Background Art

[0002] Some aircrafts need to be equipped with both turbine engines and ramjet engines due to their high flight speed, so it is necessary to design an adaptive lower lip to adjust the intake volume. In addition, in order to meet the requirements of adjusting the engine exhaust volume, the intake duct area needs to be adjusted, so it is necessary to design an intake duct lower lip adjustment mechanism.

[0003] Since the lower lip of the air inlet needs to maintain coordinated movement, the lower lip of the air inlet needs to be realized through mechanical hydraulic movement. In addition, the lower limit position of the lower lip of the air inlet needs to meet the minimum throat area requirement for engine ignition; at the same time, due to the large space requirements of the traditional rudder control mechanism, the rudder control function cannot be realized in a limited space. The above multiple design constraints bring great difficulties to the design of the rudder adjustment mechanism of hypersonic aircraft. Summary of the invention

[0004] In order to solve the above problems, the present application provides a planar multi-link rudder surface adjustment mechanism, comprising:

[0005] Rudder surfaces, linkages and drive devices;

[0006] The rudder surface is wedge-shaped, with its tip being the windward end and the wide end being the tail end; one side of the wide end is hinged on the edge of the lower wall plate of the aircraft air inlet, and the other side is hinged to the driving device through a connecting rod mechanism; the connecting rod mechanism comprises: a first connecting rod, a second connecting rod, a third connecting rod and a rocker arm, one end of the first connecting rod is hinged to the rudder surface, and the other end is hinged to the second connecting rod, the second connecting rod is hinged to the third connecting rod, the third connecting rod is hinged to the rocker arm, and the rocker arm is hinged to the fuselage and the driving device respectively; the hinge holes at both ends of the second connecting rod are perpendicular to each other.

[0007] Preferably, the rudder surface includes an upper profile and a lower profile, the upper profile and the lower profile are connected at the front end to form the tip, and are connected at the rear end through a support plate to form a wide body end, and the upper profile overlaps the lower wall panel of the aircraft air inlet.

[0008] Preferably, one side of the wide body end close to the upper profile is hinged to the edge of the lower wall panel of the aircraft air inlet, and one side of the wide body end close to the lower profile is hinged to the first connecting rod.

[0009] Preferably, the hinge holes at both ends of the first connecting rod are parallel to the lower mold surface, and the hinge holes at both ends of the third connecting rod are perpendicular to the hinge holes at both ends of the first connecting rod.

[0010] Preferably, the connecting rod mechanism and the driving device are located in the plane where the lower wall plate of the air inlet duct is located.

[0011] Preferably, one end of the rocker arm is hinged to the machine body, and the other end is hinged to the driving device, and the third connecting rod is hinged to the middle position of the rocker arm to form a lever structure; the hinge holes of the rocker arm are parallel to the hinge holes of the third connecting rod.

[0012] Preferably, the drive means comprises a hydraulic jack.

[0013] Preferably, both the upper mold surface and the lower mold surface include arc-shaped surfaces, and the curvature of the upper mold surface is greater than the curvature of the lower mold surface.

[0014] The advantages of the present application include: the hinge hole of the second connecting rod is vertical to form a connecting rod mechanism in the same plane, so that it meets the space limitation of the low profile, and the rocker arm forms a lever structure to meet the load input of high hinge torque. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of a planar multi-link rudder surface adjustment mechanism of the present application.

[0016] Figure 2 It is a schematic diagram of a rudder surface of the present application.

[0017] Figure 3 It is a schematic diagram of the rocker arm of this application. DETAILED DESCRIPTION

[0018] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0019] like Figure 1 - Figure 3 As shown, in order to solve the above problems, the present application provides a planar multi-link rudder surface adjustment mechanism, comprising:

[0020] The rudder surface 1, the connecting rod mechanism and the driving device 6; in some optional embodiments, the driving device 6 adopts a hydraulic actuator;

[0021] The rudder surface 1 is wedge-shaped, with its tip being the windward end and the wide end being the tail end; one side of the wide end is hinged to the edge of the lower wall plate of the aircraft air inlet, and the other side is hinged to the driving device 6 through a connecting rod mechanism; the connecting rod mechanism includes: a first connecting rod 2, a second connecting rod 3, a third connecting rod 4 and a rocker arm 5, one end of the first connecting rod 2 is hinged to the rudder surface 1, and the other end is hinged to the second connecting rod 3, the second connecting rod 3 is hinged to the third connecting rod 4, the third connecting rod 4 is hinged to the rocker arm 5, and the rocker arm 5 is respectively hinged to the fuselage and the driving device 6; the hinge holes at both ends of the second connecting rod 3 are perpendicular to each other. Among them, the lower wall plate of the air inlet is a wall away from the fuselage.

[0022] In some optional embodiments, the control surface 1 includes an upper profile and a lower profile, the upper profile and the lower profile are connected at the front end to form the tip, and are connected at the rear end through a support plate to form a wide body end, and the upper profile overlaps the lower wall plate of the aircraft air inlet. Both the upper profile and the lower profile include arc-shaped surfaces, and the curvature of the upper profile is greater than the curvature of the lower profile.

[0023] In some optional embodiments, the hinge holes at both ends of the second connecting rod 3 are perpendicular to each other, the hinge holes at both ends of the first connecting rod 2 are parallel to the lower profile, and the hinge holes at both ends of the third connecting rod 4 are perpendicular to the hinge holes at both ends of the first connecting rod 2, so that the connecting rod mechanism and the driving device 6 are located in the plane where the lower wall plate of the air inlet is located. Thus, the space limitation of the low profile is met;

[0024] In some optional embodiments, one side of the wide body end close to the upper profile is hinged to the edge of the lower wall panel of the aircraft air inlet, and one side of the wide body end close to the lower profile is hinged to the first connecting rod 2 .

[0025] In some optional embodiments, one end of the rocker arm 5 is hinged to the machine body, and the other end is hinged to the driving device 6. The third connecting rod 4 is hinged to the middle position of the rocker arm 5 to form a lever structure. The hinge holes of the rocker arm 5 are parallel to the hinge holes of the third connecting rod 4.

[0026] The above technical features can enable the rocker arm 5 to form a lever structure, meet the load input of high hinge torque, and enable the rudder surface 1 to withstand a higher load.

[0027] In some optional embodiments, when the area of ​​the air inlet needs to be reduced, the hydraulic actuator push rod is extended to push the tip of the rudder surface 1 to rotate toward the air inlet, and the area of ​​the air inlet throat becomes smaller; conversely, when the hydraulic actuator push rod is shortened, the tip of the rudder surface 1 is pushed to rotate away from the air inlet, and the area of ​​the throat increases. By designing the rod length of the mechanism, it can be ensured that the area of ​​the air inlet throat becomes smaller. In addition, by designing the rod length of the mechanism, it is also ensured that the movement range of the lower lip meets the minimum throat area requirement for engine ignition.

[0028] The advantages of the present application include: the hinge hole of the second connecting rod is vertical to form a connecting rod mechanism in the same plane, so that it meets the space limitation of the low profile, and the rocker arm forms a lever structure to meet the load input of high hinge torque.

[0029] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A planar multi-link rudder surface adjustment mechanism, characterized in that: include: A rudder surface (1), a connecting rod mechanism and a driving device (6); The rudder surface (1) is wedge-shaped, with its tip being the windward end and its wide end being the tail end; One side of the wide body end is hinged to the edge of the lower wall plate of the aircraft air inlet, and the other side is hinged to the driving device (6) through a connecting rod mechanism; the connecting rod mechanism comprises: a first connecting rod (2), a second connecting rod (3), a third connecting rod (4) and a rocker arm (5); one end of the first connecting rod (2) is hinged to the rudder surface (1), and the other end is hinged to the second connecting rod (3); the second connecting rod (3) is hinged to the third connecting rod (4); the third connecting rod (4) is hinged to the rocker arm (5); the rocker arm (5) is hinged to the body and the driving device (6) respectively; the hinge holes at both ends of the second connecting rod (3) are perpendicular to each other.

2. The planar multi-link rudder surface adjustment mechanism according to claim 1, characterized in that: The rudder surface (1) comprises an upper profile and a lower profile, wherein the upper profile and the lower profile are connected at the front end to form the tip, and are connected at the rear end through a support plate to form a wide body end, and the upper profile overlaps the lower wall plate of the aircraft air inlet.

3. The planar multi-link rudder surface adjustment mechanism according to claim 2, characterized in that: One side of the wide body end close to the upper profile is hinged to the edge of the lower wall plate of the aircraft air inlet, and one side of the wide body end close to the lower profile is hinged to the first connecting rod (2).

4. The planar multi-link rudder surface adjustment mechanism according to claim 2, characterized in that: The hinge holes at both ends of the first connecting rod (2) are parallel to the lower profile surface, and the hinge holes at both ends of the third connecting rod (4) are perpendicular to the hinge holes at both ends of the first connecting rod (2).

5. The planar multi-link rudder surface adjustment mechanism according to claim 4, characterized in that: The connecting rod mechanism and the driving device (6) are located in the plane where the lower wall plate of the air inlet duct is located.

6. The planar multi-link rudder surface adjustment mechanism according to claim 5, characterized in that: One end of the rocker arm (5) is hinged on the machine body, and the other end is hinged on the driving device (6). The third connecting rod (4) is hinged at the middle position of the rocker arm (5) to form a lever structure. The hinge holes of the rocker arm (5) are parallel to the hinge holes of the third connecting rod (4).

7. The planar multi-link rudder surface adjustment mechanism according to claim 1, characterized in that: The driving device (6) comprises a hydraulic jack.

8. The planar multi-link rudder surface adjustment mechanism according to claim 1, characterized in that: The upper mold surface and the lower mold surface both include arc-shaped surfaces, and the curvature of the upper mold surface is greater than the curvature of the lower mold surface.

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