Composite material rudder sheet for aircraft

Abstract

The utility model discloses a composite material rudder sheet for an aircraft, which belongs to the technical field of aircraft accessories and comprises two mounting plates, the two mounting plates are fixedly connected through two connecting rods, two side plates are rotatably connected between the two mounting plates, and the two side plates are rotatably connected in a sectional manner; the upper end and the lower end of each side plate are slidably arranged on the mounting plate through a supporting plate. Reinforcing plates are fixedly arranged in the side plates, and honeycomb plates are fixedly arranged in the side plates; the adjusting assembly is arranged between the two mounting plates and used for driving the angle of the two side plates, and the adjusting assembly comprises two sliding grooves symmetrically formed in the sectional type side plates and adjusting rods slidably arranged in the sliding grooves; the monitor is fixedly installed on the side plate and used for monitoring an impacted object, the shape of the monitor is effectively changed, the shape of the monitor can be changed when the monitor is impacted, and therefore impact force borne by equipment is effectively reduced, and use safety of the monitor is further guaranteed.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of aircraft accessory technology, especially relates to a composite material rudder for aircraft. BACKGROUND

[0002] The aircraft rudder refers to the aerodynamic surface that uses deflection to make the aircraft produce balance force and control force to control its flight, also called control surface, the traditional composite material has higher specific strength and specific modulus, but when suffering from high-speed small object impact (such as bird impact, foreign matter impact), easy to produce delamination, crack and other damages, affect the structural integrity and performance of the rudder, and even possibly lead to rudder failure, and the traditional rudder does not have the ability of buffering due to its fixed shape, thereby leading to certain disadvantages of the equipment when in use, and then affecting the use of the equipment. SUMMARY

[0003] In view of the problems existing in the prior art, the utility model provides a composite material rudder for aircraft, solves the problem that the existing rudder has poor impact resistance and is easy to be damaged by impact.

[0004] The utility model is realized in this way, a composite material rudder for aircraft, including two installation boards, two installation boards are fixedly connected through two connecting rods, two installation boards are rotatably connected with two side plates, still include:

[0005] Two side plates are rotatably connected in a segmented mode;

[0006] Two side plates are rotatably connected in a segmented mode;

[0007] The inside of the side plate is fixedly provided with a reinforcing plate, and the inside of the side plate is fixedly provided with a honeycomb plate;

[0008] An adjusting assembly is arranged between the two installation boards and is used for adjusting the angle of the two side plates, comprising two sliding grooves symmetrically arranged on the segmented side plate and an adjusting rod slidingly arranged in the sliding groove;

[0009] A monitor is fixedly installed on the side plate and is used for monitoring the impact object.

[0010] As preferred in the utility model, the segmented side plate is hinged through the hinge column arranged in a rotating mode, and the ends of the side plate are respectively hinged on the installation plate.

[0011] As preferred in the utility model, the honeycomb plate is arranged at the rear side of the reinforcing plate, the reinforcing plate is made of aluminum alloy material, and the honeycomb plate is made of aramid paper honeycomb material.

[0012] As the utility model is preferred, the adjusting assembly further comprises a sliding block hinged to the end of the adjusting rod, the sliding block is slidingly arranged in the sliding groove, a rotating shaft is rotatably arranged between the two mounting plates, a crankshaft corresponding to the adjusting rod is arranged on the rotating shaft, the other end of the adjusting rod is hinged to the crankshaft, and the rotating shaft is driven by a driving source.

[0013] As the utility model is preferred, the side plate and the mounting plate are filled with corrugated rubber material.

[0014] Compared with the prior art, the utility model has the beneficial effects as follows:

[0015] The utility model discloses through changing the shape of the side plate, the rudder piece formed by the side plate can effectively reduce the impact force outside, through the change of shape, can effectively buffer the impact force, thereby improving the carrying capacity and the damage resistance of the rudder piece, delaying the service life of the equipment, and through the internally arranged reinforcing plate and honeycomb plate, the heat resistance and the strength of the rudder piece can be effectively improved, so that the equipment is more solid during use, and the service life is stronger. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is the front side view angle structure schematic diagram of the utility model;

[0017] Figure 2 It is the right side view angle internal structure schematic diagram of the utility model;

[0018] Figure 3 It is the front side view angle internal structure schematic diagram of the utility model;

[0019] Figure 4 It is the internal view angle structure schematic diagram of the side plate of the utility model;

[0020] Figure 5 It is the structure schematic diagram of the utility model after deformation.

[0021] In the drawing:

[0022] 1, mounting plate;2, connecting rod;3, side plate;4, reinforcing plate;5, honeycomb plate;6, sliding groove;7, adjusting rod;8, sliding block;9, rotating shaft;10, crankshaft;11, driving source;12, hinge column;13, support plate;14, monitor. DETAILED DESCRIPTION

[0023] In order to further understand the utility model content, characteristics and efficacy of the utility model, the following examples are cited, and the following is described in detail in conjunction with the drawings.

[0024] The structure of the utility model is described in detail below in conjunction with the drawings.

[0025] As Figures 1 to 5As shown, the utility model embodiment provides a kind of composite material rudder piece for aircraft, including two mounting plate 1, two mounting plate 1 between by two connecting rods 2 fixed connection, two mounting plate 1 between rotatably connected with two side plates 3, still include:

[0026] Two side plates 3 are connected in rotation in section;

[0027] Two side plates 3 upper and lower ends are slidably arranged on mounting plate 1 by a support plate 13;

[0028] Reinforcing plate 4 is fixedly arranged in side plate 3, and honeycomb plate 5 is fixedly arranged in side plate 3;

[0029] Adjusting assembly is arranged between two mounting plate 1, for adjusting the angle of two side plates 3, including two sliding grooves 6 symmetrically opened on sectional side plate 3, and adjusting rod 7 slidably arranged in sliding groove 6;

[0030] Fixedly installed on side plate 3, for monitoring monitor 14 of impacting object.

[0031] As preferred in the utility model, sectional side plate 3 is hinged by rotatably arranged hinge column 12, and end of side plate 3 is hinged on mounting plate 1 respectively, so that the shape of side plate 3 can be changed, so that the impact force of side plate 3 can be reduced when it is impacted, to avoid damage to side plate 3 by impact.

[0032] As preferred in the utility model, honeycomb plate 5 is arranged at the rear side of reinforcing plate 4, reinforcing plate 4 uses aluminum alloy material, and honeycomb plate 5 uses aramid paper honeycomb material, so that the strength of side plate 3 can be increased, to further avoid damage to side plate 3 by impact.

[0033] As preferred in the utility model, adjusting assembly further includes sliding block 8 hinged at the end of adjusting rod 7, sliding block 8 is slidably arranged in sliding groove 6, one rotating shaft 9 is rotatably arranged between two mounting plate 1, crankshaft 10 corresponding with adjusting rod 7 is arranged on rotating shaft 9, the other end of adjusting rod 7 is hinged on crankshaft 10, rotating shaft 9 is driven by one drive source 11, effectively adjust the shape of side plate 3, realize the automatic adjustment of shape, so that it is more convenient when using.

[0034] As preferred in the utility model, corrugated rubber material is filled between side plate 3 and mounting plate 1, so that the sealing property between mounting plate 1 and side plate 3 can be further increased, to avoid damage to its inside by gas impact.

[0035] The working principle of the utility model:

[0036] Reference Figure 4The reinforcing plate 4 can improve the impact resistance and overall rigidity of the side plate 3, the reinforcing plate 4 can effectively disperse impact force, reduce local stress concentration, prevent delamination and crack generation, meanwhile, the reinforcing plate 4 can also enhance the fatigue resistance of the side plate 3 under alternating load, prolong the service life, the honeycomb plate 5 can significantly improve the strength and rigidity of the side plate 3 without increasing excessive weight, meanwhile, the honeycomb plate 5 can also improve the fatigue resistance, the honeycomb plate 5 also has good heat insulation performance, which is helpful to reduce the influence of heat on the composite material;

[0037] Reference Figure 1 When the side plate 3 is impacted by external foreign matters, the monitor 14 drives the driving source 11 through detection results, and when the driving source 11 works, the driving source 11 drives the rotating shaft 9 to rotate (the driving source 11 can be an existing driving motor), when the rotating shaft 9 rotates, the crankshaft 10 installed on the rotating shaft 9 pulls the adjusting rod 7 to move, when the adjusting rod 7 moves, the sliding block 8 at the end of the adjusting rod 7 slides in the sliding groove 6, meanwhile, the adjusting rod 7 pulls the segmented side plate 3 to rotate around the hinge column 12, meanwhile, the upper and lower support plates 13 on the side plate 3 move on the mounting plate 1, so that the two support plates 13 are close to each other, when the crankshaft 10 rotates to the appropriate position, the side plate 3 forms the state shown in the figure, at this time, when the side plate 3 is impacted, the side plate 3 is in an inclined state relative to the initial state, which can effectively reduce the external impact force, and avoid the case that the side plate 3 is damaged due to too strong external impact force when the equipment is used, when the side plate 3 is impacted, the side plate 3 can be reset by reversing the operation of the driving source 11, so that the shape of the side plate 3 can be effectively changed; Figure 2 Figure 5 The utility model discloses the shape of the side plate 3 is changed, the rudder piece formed by the side plate 3 can effectively reduce the external impact force, through the change of shape, the impact force can be effectively buffered, thereby improving the bearing capacity and damage resistance of the rudder piece, delaying the service life of the equipment, meanwhile, the reinforcing plate 4 and the honeycomb plate 5 arranged internally can effectively improve the heat resistance and strength of the rudder piece, so that the equipment is more solid when being used, and the service life is stronger.

[0038] It should be noted that, in this document, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0039] It should be noted that, in this document, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0040] ​Although the embodiments of the present application have been shown and described, it is to be understood that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present application, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A composite material rudder for an aircraft, comprising two mounting plates (1), the two mounting plates (1) being fixedly connected by two connecting rods (2), and two side plates (3) being rotatably connected between the two mounting plates (1), characterized in that: Also include: Two said side plate (3) is connected by rotating in sections; Two said side plate (3) upper and lower ends are both through a support plate (13) slidingly arranged on the mounting plate (1); The side plate (3) is internally fixed with a reinforcing plate (4), and the side plate (3) is internally fixed with a honeycomb plate (5); Adjusting assembly, arranged between two mounting plates (1), for adjusting the angle of two side plates (3), including two sliding grooves (6) symmetrically opened on the segmented side plate (3), and adjusting rod (7) slidingly arranged in the sliding groove (6); Fixedly installed on the side plate (3), for monitoring the impact object monitor (14).

2. A composite material tailplane for an aircraft as claimed in claim 1, characterised in that: The segmented side plate (3) is hinged by the hinge column (12) arranged by rotating, and the end of the side plate (3) is hinged on the mounting plate (1).

3. A composite material tailplane for an aircraft as claimed in claim 2, characterised in that: The honeycomb plate (5) is arranged on the rear side of the reinforcing plate (4), the reinforcing plate (4) uses aluminum alloy material, and the honeycomb plate (5) uses aramid paper honeycomb material.

4. A composite material tailplane for an aircraft as claimed in claim 3, characterised in that: The adjusting assembly further comprises a sliding block (8) hinged at the end of the adjusting rod (7), the sliding block (8) is slidingly arranged in the sliding groove (6), a rotating shaft (9) is rotatably arranged between two mounting plates (1), the rotating shaft (9) is provided with a crankshaft (10) corresponding to the adjusting rod (7), the other end of the adjusting rod (7) is hinged on the crankshaft (10), and the rotating shaft (9) is driven by a driving source (11).

5. A composite material tailplane for an aircraft as claimed in claim 4, characterised in that: The side plate (3) and the mounting plate (1) are filled with corrugated rubber material.

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