Anti-vibration hinge bolt anti-rotation / anti-looseness integrated device for aircraft control plane

Abstract

The invention relates to the technical field of aircraft anti-vibration control surface structures, in particular to an aircraft control surface anti-vibration hinge bolt anti-rotation / anti-looseness integrated device which is provided with an anti-rotation / anti-looseness clamping plate, and the other end of the anti-rotation / anti-looseness clamping plate is installed on the outer side of the head of a hinge bolt in a sleeved mode. The side face of the anti-rotation / anti-looseness clamping plate is meshed with the plane portion of the head of the hinge bolt to form an anti-rotation measure of the hinge bolt, and a second-level anti-looseness measure of the hinge bolt is formed between the anti-rotation / anti-looseness clamping plate and the head of the hinge bolt in a combined mode of a slotted nut and a cotter pin. On the premise that basic anti-rotation measures are designed for the hinge bolt, damage safety design measures for hinge looseness prevention are additionally provided, and the problem that whether the control surface hinge bolt can continue to be locked or not after the basic anti-looseness measures at the tail end of the control surface hinge bolt fail due to control surface vibration is solved. And the use reliability and safety of the aircraft control surface in a vibration environment are improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft vibration-resistant control surface structure technology, and to an integrated anti-rotation / anti-loosening device for aircraft control surface vibration-resistant hinge bolts. Background Technology

[0002] As a crucial component of aircraft control surfaces, control surface hinge bolts not only bear and transmit loads acting on the control surfaces but also maintain their deflection function. In addition to strength and rigidity requirements, the design process for control surface hinge bolts must consider: 1) an anti-rotation design between the bolt and the lug to prevent relative rotation between the pin and the lug hole, which could lead to wear on the pin surface and affect the bolt's strength; 2) an anti-loosening design to prevent the bolt, with its head pointing downwards, from detaching from the hinge in the event of accidental nut loss, thus affecting the normal functioning of the control surface.

[0003] Current control surface hinge bolts employ anti-rotation measures such as installing an anti-rotation clamp on the bolt head and anti-loosening measures such as installing a cotter pin in the nut slot. These anti-loosening and anti-rotation measures are unrelated. Under vibration, the basic anti-loosening measures are prone to accidental failure, causing the hinge bolt to gradually loosen, rendering the anti-rotation measures ineffective, and ultimately leading to the bolt detaching from the hinge and affecting the control surface's function. Therefore, an integrated design solution for preventing rotation and loosening of the control surface vibration-resistant hinge bolts is needed. Summary of the Invention

[0004] To address the aforementioned problems, this application provides an integrated anti-rotation / anti-loosening device for aircraft control surface anti-vibration hinge bolts, comprising:

[0005] Hinge suspension connector, hinge suspension arm, hinge bolt, anti-rotation / anti-loosening clamp, slotted nut, cotter pin, washer, slotted nut, cotter pin, anti-rotation bolt, washer, and self-locking nut, wherein:

[0006] The hinge suspension joint and the hinge suspension arm are connected by hinge bolts to form a ball joint kinematic pair. The tail end of the hinge bolt is fixed by a slotted nut and a cotter pin to form a basic anti-loosening measure for the hinge bolt.

[0007] The head of the hinge bolt is fitted with an anti-rotation / anti-loosening clamp, forming an anti-rotation measure and a secondary anti-loosening measure for the hinge bolt;

[0008] One end of the anti-rotation / anti-loosening plate is attached to the lug surface of the hinge suspension joint and is fixed by a combination of anti-rotation bolts, washers and self-locking nuts;

[0009] The other end of the anti-rotation / anti-loosening clamp is fitted onto the outside of the hinge bolt head, and its side engages with the flat part of the hinge bolt head to form an anti-rotation measure for the hinge bolt. The anti-rotation / anti-loosening clamp and the hinge bolt head are connected by a combination of slotted nuts and cotter pins to form a secondary anti-loosening measure for the hinge bolt.

[0010] Preferably, the side of the anti-rotation / anti-loosening plate and the flat portion of the hinge bolt head are provided with an installation gap δ.

[0011] Preferably, the inner cavity shape of the anti-rotation / anti-loosening clamp plate that mates with the hinge bolt head is polygonal.

[0012] Preferably, the hinge bolt head is hexagonal, and the anti-rotation / anti-loosening plate has a rectangular groove that mates with it.

[0013] Preferably, a washer is provided between the anti-rotation / anti-loosening clamp and the slotted nut.

[0014] Preferably, the hinge bolt is made of high-strength alloy steel to withstand dynamic loads.

[0015] Preferably, the difference between the width of the rectangular groove and the width of the hinge bolt head is the installation clearance δ.

[0016] Preferably, a washer is provided between the slotted nut and the hinge suspension joint.

[0017] Preferably, the hinge bolt has an annular groove at the washer position.

[0018] This invention provides an integrated anti-rotation / anti-loosening device on the aircraft control surface hinge suspension joint. While ensuring that the hinge bolt meets the anti-rotation design, it also provides a secondary anti-loosening measure for the hinge bolt, that is, it incorporates a breakage safety design for the bolt anti-loosening. This solves the problem of whether the hinge bolt can continue to maintain anti-loosening and locking after the basic anti-loosening measures at the tail end of the hinge bolt fail due to control surface vibration, thereby improving the reliability and safety of the control surface. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of an integrated anti-rotation / anti-loosening device for aircraft anti-vibration control surface hinge bolts according to an embodiment of the present invention.

[0020] Figure 2 This is a schematic diagram of an integrated anti-rotation / anti-loosening device for aircraft anti-vibration control surface hinge bolts according to an embodiment of the present invention. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings. Figure 1 This is a schematic diagram of an integrated anti-rotation / anti-loosening device for aircraft control surface hinge bolts according to the present invention.

[0022] like Figure 1 As shown, the hinge suspension joint 1 and the hinge suspension arm 2 are connected by a hinge bolt 3 to form a ball joint motion pair. The tail end of the hinge bolt 3 is fixed by a washer 8, a slotted nut 9 and a cotter pin 10 to form the basic anti-loosening measure of the hinge bolt 3. The head of the hinge bolt 3 is fitted with an anti-rotation / anti-loosening clamp 4 to form an anti-rotation measure and a secondary anti-loosening measure of the hinge bolt. One end of the anti-rotation / anti-loosening clamp 4 is attached to the lug surface of the hinge suspension joint 1 and fixed by a combination of an anti-rotation bolt 11, a washer 12 and a self-locking nut 11. The other end of the anti-rotation / anti-loosening clamp 4 is fitted onto the outside of the head of the hinge bolt 3, and its side engages with the flat part of the head of the hinge bolt 3 to form an anti-rotation measure of the hinge bolt. Its bottom surface and the protruding stud of the head of the hinge bolt 3 are connected by a combination of a washer 5, a slotted nut 6 and a cotter pin 7 to form a secondary anti-loosening measure of the hinge bolt 3.

[0023] In some embodiments, the anti-rotation / anti-loosening clamping plate 4 and the lug surface of the hinge suspension joint 1 can also be fixed by a combination of bolts, slotted nuts, washers and cotter pins.

[0024] In some embodiments, the inner cavity shape of the anti-rotation / anti-loosening plate 4 that mates with the head of the hinge bolt 3 can also be an internal hexagon.

[0025] Extensive calculations, analyses, and experiments have demonstrated that using this device to prevent rotation and loosening of aircraft control surface hinge bolts solves the problem of whether hinge bolts can remain locked after the basic anti-loosening measures at the tail end of the hinge bolt fail, thus improving the reliability and safety of control surfaces.

[0026] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An integrated anti-rotation / anti-loosening device for aircraft control surface vibration-resistant hinge bolts, characterized in that, include: Hinge suspension joint (1), hinge suspension arm (2), hinge bolt (3), anti-rotation / anti-loosening clamp (4), slotted nut (6), cotter pin (7), washer (8), slotted nut (9), cotter pin (10), anti-rotation bolt (11), washer (12), and self-locking nut (13), wherein: The hinge suspension joint (1) and the hinge suspension arm (2) are connected by a hinge bolt (3) to form a ball joint motion pair. The tail end of the hinge bolt (3) is fixed by a slotted nut (9) and a cotter pin (10) to form the basic anti-loosening measure of the hinge bolt (3). The head of the hinge bolt (3) is fitted with an anti-rotation / anti-loosening clamp (4), forming an anti-rotation measure and a secondary anti-loosening measure for the hinge bolt (3); One end of the anti-rotation / anti-loosening plate (4) is attached to the lug surface of the hinge suspension joint (1) and fixed by a combination of anti-rotation bolt (11), washer (12) and self-locking nut (13); The other end of the anti-rotation / anti-loosening clamp (4) is fitted onto the outside of the head of the hinge bolt (3), and its side engages with the flat part of the head of the hinge bolt (3) to form an anti-rotation measure for the hinge bolt (3). The anti-rotation / anti-loosening clamp (4) and the head of the hinge bolt (3) are connected by a combination of slotted nut (6) and cotter pin (7) to form a secondary anti-loosening measure for the hinge bolt (3).

2. The integrated anti-rotation / anti-loosening device for aircraft control surface anti-vibration hinge bolts as described in claim 1, characterized in that, The side of the anti-rotation / anti-loosening plate (4) and the flat part of the head of the hinge bolt (3) are provided with an installation gap δ.

3. The integrated anti-rotation / anti-loosening device for aircraft control surface vibration-resistant hinge bolts as described in claim 1, characterized in that, The inner cavity shape of the anti-rotation / anti-loosening plate (4) that mates with the head of the hinge bolt (3) is polygonal.

4. The integrated anti-rotation / anti-loosening device for aircraft control surface vibration-resistant hinge bolts as described in claim 3, characterized in that, The hinge bolt (3) has a hexagonal head, and the anti-rotation / anti-loosening plate (4) has a rectangular groove that matches it.

5. The integrated anti-rotation / anti-loosening device for aircraft control surface anti-vibration hinge bolts as described in claim 1, characterized in that, A washer (5) is provided between the anti-rotation / anti-loosening clamp (4) and the slotted nut (6).

6. The integrated anti-rotation / anti-loosening device for aircraft control surface vibration-resistant hinge bolts as described in claim 1, characterized in that, The hinge bolt (3) is made of high-strength alloy steel to withstand dynamic loads.

7. The integrated anti-rotation / anti-loosening device for aircraft control surface vibration-resistant hinge bolts as described in claim 41, characterized in that, The difference between the width of the rectangular groove and the width of the hinge bolt (3) head is the installation clearance δ.

8. The integrated anti-rotation / anti-loosening device for aircraft control surface vibration-resistant hinge bolts as described in claim 1, characterized in that, A washer (8) is provided between the slotted nut (9) and the hinge suspension joint (1).

9. The integrated anti-rotation / anti-loosening device for aircraft control surface vibration-resistant hinge bolts as described in claim 8, characterized in that, The hinge bolt (3) has an annular groove at the position of the washer (8).

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