A soft joint hard stitched composite control surface structure

Abstract

The application discloses a kind of soft connection hard suture composite surface structure, including composite surface (2), composite surface (2) and composite stabilizer (4) are connected by soft connection fiber woven cloth (1) preposition in the layup of both sides;Composite surface (2) and the soft connection of composite stabilizer (4) are provided with two pairs of hinge installation grooves (3) along the span direction;Hinge is sutured in hinge installation groove (3).The utility model effectively guarantees the surface structure appearance and surface efficiency, improves the connection strength of surface and stabilizer, simultaneously satisfies the design principle of low cost, light weight, easy assembly.

Description

Technical Field

[0001] This utility model relates to the field of composite material technology, and in particular to a soft-connection hard-stitch composite material rudder surface structure. Background Technology

[0002] During flight missions, aircraft require multiple ascents, descents, and turns, in which the control surface structure plays a crucial role. The span of control surfaces varies considerably depending on the aircraft's actual operating requirements. Control surfaces with a shorter span only need to be directly connected to the servo motor at their root; however, control surfaces with a longer span often have a larger stabilizing surface at their front. In this case, the control surface not only needs to be connected to the servo motor but also to the trailing edge or tip of the stabilizing surface to maintain its stability.

[0003] The commonly used control surface and stabilizer connection structure requires additional parts and corresponding bearings to be installed at the tip of the stabilizer to ensure the coaxiality of the control surface shaft and the servo motor output shaft. The control surface structure and its assembly process are relatively complex and the structure is heavy. This method is not suitable for low-cost products. While the soft connection between the control surface and the stabilizer is simplified in terms of structure and assembly process by simply using aramid cloth or high molecular weight polyethylene cloth, the soft connection cloth may delaminate or tear under heavy loads, resulting in a deviation between the control surface deflection angle and the actual steering angle. Utility Model Content

[0004] The purpose of this invention is to provide a flexible-connection, hard-stitched composite material control surface structure. This invention effectively ensures the shape and efficiency of the control surface structure, improves the connection strength between the control surface and the stabilizer, and meets the design principles of low cost, lightweight, and easy assembly.

[0005] The technical solution of this utility model: A flexible-connection-hard-stitch composite material rudder surface structure, comprising a composite material rudder surface, wherein the composite material rudder surface and the composite material stabilizing surface are flexibly connected by a flexible connecting fiber woven fabric pre-placed in the layup of the two; two pairs of hinge mounting grooves are provided along the spanwise direction at the flexible connection between the composite material rudder surface and the composite material stabilizing surface; hinges are stitched into the hinge mounting grooves.

[0006] In the aforementioned soft-connection hard-stitch composite rudder surface structure, the soft-connection fiber woven fabric is made of aramid or high molecular weight polyethylene.

[0007] In the aforementioned soft-connection hard-stitch composite rudder surface structure, the hinge includes a double-eared flap and a single-eared flap. The double-eared flap is sewn into the hinge mounting groove of the composite rudder surface by fiber stitching, and the single-eared flap is sewn into the hinge mounting groove of the composite stabilizer surface by fiber stitching. The single ear of the single-eared flap is inserted into the double ears of the double-eared flap and aligned, and then connected by the hinge pivot.

[0008] In the aforementioned soft-connection hard-stitch composite rudder surface structure, the hinge shaft is limited by right-angle bends at both ends.

[0009] In the aforementioned soft-connection hard-stitch composite rudder surface structure, the hinge is made of 30CrMnSiA.

[0010] In the aforementioned soft-connection hard-stitch composite rudder surface structure, the hinge shaft is made of 55CrSi. The beneficial effects of this utility model are as follows: This utility model provides a composite material rudder surface structure with a flexible fiber woven fabric connection and a fiber-impregnated resin hard-stitched metal hinge, which is suitable for the connection between the rudder surface and the stabilizer under heavy loads. Moreover, the fiber stitching protrudes much less from the rudder surface than standard parts such as screws and nuts, effectively ensuring the shape and efficiency of the rudder surface structure, improving the connection strength between the rudder surface and the stabilizer, and meeting the design requirements of low cost, lightweight, and easy assembly.

[0011] This invention provides a design reference for the connection and rotation between various thin-skin (composite material) structures.

[0012] The hinge of this utility model is installed in the groove between the rudder surface and the stabilizer surface, which effectively ensures the aerodynamic shape.

[0013] This invention utilizes a flexible connecting fiber woven fabric and a hinge to maintain a reliable connection between the control surface and the stabilizer, thus ensuring control surface efficiency.

[0014] This utility model features a self-bending axial limit for the rotating shaft, which reduces the number of parts and improves assembly efficiency.

[0015] This utility model uses fiber yarn to replace standard parts such as screws and nuts, reducing structural weight and manufacturing costs. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the control surface and stabilizer structure; Figure 2 This is a schematic diagram of a hinge structure; Figure 3 This is a diagram illustrating the threading of a through-and-through suture. Figure 4 This is a schematic diagram of the overall structure. Detailed Implementation

[0017] Example 1. A flexible-connected, hard-stitched composite material rudder surface structure, such as... Figures 1-4 As shown, it includes a composite material rudder surface 2, which is softly connected to the composite material stabilizer surface 4 by a soft connecting fiber woven fabric 1 pre-placed in the layup of the two; the soft connection between the composite material rudder surface 2 and the composite material stabilizer surface 4 is provided with two pairs of hinge mounting grooves 3 along the spanwise direction; hinges are sewn into the hinge mounting grooves 3.

[0018] The aforementioned flexible connecting fiber woven fabric 1 is made of aramid or high molecular weight polyethylene.

[0019] The aforementioned hinge includes a double-eared hinge plate 5 and a single-eared hinge plate 6. The double-eared hinge plate 5 is sewn into the hinge mounting groove 3 of the composite material rudder surface 2 by fiber suture 11. The single-eared hinge plate 6 is sewn into the hinge mounting groove 3 of the composite material stabilizing surface 4 by fiber suture 11. The single ear of the single-eared hinge plate 6 is inserted into the double ears of the double-eared hinge plate 5 and aligned, and then connected by the hinge pivot 7.

[0020] The aforementioned hinge shaft 7 is limited by right-angle bends at both ends.

[0021] The aforementioned hinge is made of 30CrMnSiA.

[0022] The aforementioned hinge shaft 7 is made of 55CrSi.

[0023] The composite rudder surface 2 and the composite stabilizer surface 4 are connected by the flexible connecting fiber woven fabric 1 in the layup and two sets of hinges installed by stitching. Specific operating instructions are as follows: First, assemble the double-eared hinge pieces 5, the single-eared hinge piece 6, and the hinge shaft 7 into a single hinge. The shaft achieves axial self-locking through a tip bend. Remove foreign objects and excess flexible connecting fabric from the hinge mounting groove 3. Use adhesive to position the hinge on the hinge mounting groove 3 of the rudder surface and stabilizer surface. Drill stitching holes on the rudder surface and stabilizer surface through the holes 8 on the hinge. Impregnate the stitching thread 11 with resin and stitch it through the upper and lower stitching path (see [reference]). Figure 3 The back threading trajectory 9 (dashed line) and the front threading trajectory 10 (solid line) are used to install the hinge in place; vacuum pressure and heating are applied to completely cure the resin; excess resin overflowing onto the rudder surface and stabilizer surface is removed; rudder action is simulated to measure the rudder surface angle deviation and verify whether the hinge installation is qualified.

[0024] This flexible-connection, hard-stitched composite rudder surface structure provides a design reference for the connection between various thin-skin structures and other parts, effectively reducing the number of parts, simplifying the structural features of parts, improving assembly efficiency, reducing structural weight, and lowering manufacturing costs.

[0025] Example 2. A flexible-connected, hard-stitched composite material rudder surface structure, such as... Figures 1-4As shown, to achieve a reliable connection between the composite rudder surface structure and the composite stabilizer surface, a soft connecting layer fiber woven fabric can be set as the intermediate layer of the composite layup assembly during the layup process. The soft connecting layer fiber woven fabric can be made of fibers with high areal density and good ductility, such as aramid or high molecular weight polyethylene. The rudder surface and stabilizer surface are integrally manufactured through a molding process to increase the connection strength between the soft connecting layer and the stabilizer surface and rudder surface. During the forming process of the stabilizer surface and rudder surface, a hinge mounting groove is created, and each hinge assembly is divided into three parts. (Single-ear blade, double-ear blade, shaft) The blade material can be high-strength alloy steel 30CrMnSiA, etc., and the shaft can be spring steel 55CrSi, etc. The single-ear blade is installed in the rudder surface groove, and the double-ear blade is installed in the stabilizer surface groove to avoid the hinge stitching extending beyond the theoretical outer surface of the rudder surface and stabilizer surface, thus increasing aerodynamic drag. The single-ear and double-ear blade shaft holes are installed with a gap between them and the shaft. When assembling the hinge, the shaft is bent at a right angle on both sides of the double-ear blade shaft hole, retaining a portion of right-angle deformation at the root of the bend. Partially cut off the remaining portion to achieve axial positioning and fixation of the pivot, thus completing the assembly of the single and double lugs, i.e., the hinge. The soft connection layer at the hinge pivot needs to be removed to avoid interference between the hinge and the rudder surface during rotation. The hinge can be pre-positioned in the grooves of the stabilizer and rudder surface using adhesive, simulating the set angle of rudder surface rotation. By observing whether the hinge detaches during rotation, it is ensured that the hinge pivot installation position is coaxial with the rudder pivot. Then, through the holes on the hinge, stitching holes are drilled on the stabilizer and rudder surface. The hinge is then fixed to the grooves on the stabilizer and rudder surface. During installation, the mounting surface must be coated with a high-toughness adhesive. If necessary, the hinge surface should be roughened to increase the bonding strength between the hinge and the stabilizer and rudder surface. After the fiber thread is impregnated with resin, the top and bottom through-sewing process must be completed before the resin gels. During the sewing process, the sewing thread must not be twisted. The sewing thread must be straightened and tightened, and the thread end must be buried in the hole to prevent the sewing thread from bending and not adhering to the hinge surface after the resin cures, which would affect the load-bearing efficiency of the sewing thread. After the hinge is sewn, the rudder connection end is clamped to conduct a rudder action test to check whether the action angle meets the design requirements.

Claims

1. A flexible-connected, hard-stitched composite material rudder surface structure, characterized in that, The composite material rudder surface (2) and the composite material stabilizer surface (4) are softly connected by a soft connecting fiber woven fabric (1) pre-placed in the layup of the two; two pairs of hinge mounting grooves (3) are provided along the spanwise direction at the soft connection between the composite material rudder surface (2) and the composite material stabilizer surface (4); hinges are sewn into the hinge mounting grooves (3).

2. The flexible-connection, hard-stitched composite material rudder surface structure according to claim 1, characterized in that, The flexible connecting fiber woven fabric (1) is made of aramid or high molecular weight polyethylene.

3. The flexible-connection, hard-stitched composite material rudder surface structure according to claim 1, characterized in that, The hinge includes a double-eared flap (5) and a single-eared flap (6). The double-eared flap (5) is sewn into the hinge mounting groove (3) of the composite rudder surface (2) by a fiber suture (11). The single-eared flap (6) is sewn into the hinge mounting groove (3) of the composite stabilizing surface (4) by a fiber suture (11). The single ear of the single-eared flap (6) is inserted into the double ears of the double-eared flap (5) and then connected by the hinge pivot (7).

4. The flexible-connection, hard-stitched composite material rudder surface structure according to claim 3, characterized in that, The hinge pivot (7) is limited by right-angle bends at both ends.

5. The flexible-connection, hard-stitched composite material rudder surface structure according to claim 1, characterized in that, The hinge is made of 30CrMnSiA.

6. The flexible-connection, hard-stitched composite material rudder surface structure according to claim 3, characterized in that, The hinge shaft (7) is made of 55CrSi.

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