Reinforced layout structure applied to thrust vector control wing

Abstract

The invention relates to the technical field of multi-physics field complex working condition plate shell structure enhancement, in particular to a reinforced layout structure applied to a thrust vector control wing. The problem that under the high-temperature and high-load working conditions, the rigidity and strength of the lightweight thrust vector control wing are insufficient is solved. The ribs are reasonably arranged, so that the buckling resistance of the thrust vector control wing bottom plate is improved, and the maximum deformation degree of the thrust vector control wing bottom plate is reduced. While the rigidity and the strength of the thrust vector control wing are improved, the requirement of lightweight design is met, and the net weight of the ribs is not increased. In addition, parameterized expression is beneficial to rapid modeling during engineering application.

Description

Technical Field

[0001] The present invention relates to the technical field of plate and shell structure reinforcement under multi-physical field complex working conditions, and in particular to a ribbed layout structure applied to a thrust vector control wing. Background Art

[0002] The thrust vector control wing can adjust the direction of the tail flame jet of the vector engine by swinging, thereby realizing the steering of fighter jets, missiles, etc. The thrust vector control wing will be in high temperature and high load conditions caused by the tail flame jet during operation. At this time, the traditional upright orthogonal reinforcement layout is usually difficult to effectively suppress the deformation and buckling of the thrust vector control wing bottom plate. The traditional upright orthogonal reinforcement scheme usually improves the strength and stiffness performance of the thrust vector control wing bottom plate by increasing the thickness or height of the ribs, but this will significantly increase the net weight of the ribs, which is not in line with the concept of lightweight design. Summary of the invention

[0003] In view of the above technical problem, the present invention provides a ribbed layout structure applied to a thrust vector control wing.

[0004] The technical means adopted by the present invention are as follows:

[0005] A rib layout structure applied to a thrust vector control wing, consisting of a main-level rib layout and a secondary-level rib layout. The main-level rib layout includes the first rib, the second rib, the third rib, the seventh rib and the twelfth rib, as well as the sixteenth rib, the seventeenth rib, the eighteenth rib, the nineteenth rib, the twentieth rib, the twenty-first rib and the twenty-second rib, wherein the twentieth rib is a central longitudinal rib. The secondary-level rib layout includes the eighth rib, the ninth rib, the tenth rib, the eleventh rib, the fourth rib, the fifth rib, the sixth rib, the thirteenth rib, the fourteenth rib and the fifteenth rib. The overall ribbed structure layout of the present invention is symmetrical about the central axis, and the position of each rib is determined by the mutual connection relationship of the key nodes P1 to P9. Figure 1 The PO point shown in is the coordinate origin.

[0006] Place the coordinate origin PO at the connection position between the actuator support or other types of actuating structures and the control wing bottom plate; when the specific transmission connection position is unclear, the coordinate origin PO can be placed at the center of gravity of the control wing bottom plate. The distance between P0 and P1 is L.

[0007] At this time, the coordinates of nodes P1 to P9 are: P1 = (0, -L), P2 = (0, L),

[0008] Among the main-level ribs, the first rib, the second rib, and the third rib are curved ribs. The first rib passes through P3, P9, and the symmetric node of P9, and the three points are fitted by a spline curve, and extended to the control wing shell, thereby determining the position of the rib; the second rib passes through the origin P0, P7, P8, and the symmetric nodes of P7 and P8, and the five points are fitted by a spline curve, and extended to the control wing shell, thereby determining the position of the rib; the third rib passes through P1, P4, P5, P8, and the corresponding symmetric nodes, and the seven points are fitted by a spline curve, thereby determining the position of the rib.

[0009] In the main-level ribs, three points P6, P8, and P9 are fitted by spline curves, and the fitting line is extended to the control wing shell and intersects at points B1 and B2. By connecting B1 and P8, the position of the twelfth rib can be determined, and the seventh rib is symmetrical to it; by connecting P8 and P9, the position of the eighteenth rib can be determined, and the twenty-second rib is symmetrical to it; by connecting P9 and B2, the position of the nineteenth rib can be determined, and the twenty-first rib is symmetrical to it; by connecting P8 and P2, the position of the sixteenth rib can be determined, and the seventeenth rib is symmetrical to it; the twentieth rib passes through P1, P0, P2, and P3, and is located at the symmetrical center line of the entire rib layout. At this point, the layout positions of all main-level ribs can be determined.

[0010] In the sub-level ribs, the three points P7, P5, and P6 are fitted by spline curves, and the fitting line is extended to the control wing shell and intersects at point B3. Connecting P7 and P5 can determine the position of the fifteenth rib, and the fourth rib is symmetrical with it; connecting P5 and P6 can determine the position of the fourteenth rib, and the fifth rib is symmetrical with it; connecting P6 and B3 can determine the position of the thirteenth rib, and the sixth rib is symmetrical with it; the positions of the eighth rib, the ninth rib, the tenth rib, and the eleventh rib need to be determined in combination with the shape of the actual control wing shell. Drawing a vertical line from point P4 to the control wing shell, the position of the tenth rib can be determined, and the ninth rib is symmetrical with it; drawing a vertical line from point P5 to the control wing shell, the position of the eleventh rib can be determined, and the eighth rib is symmetrical with it. So far, the layout position of all sub-level ribs can be determined. The eighth rib, the ninth rib, the tenth rib, and the eleventh rib are parallel and connected to the shell. The specific size parameters of each rib are not within the scope of the claims of the present invention. It is recommended to select the height of the secondary rib within a range of one quarter to one third of the height of the primary rib. The specific width and height parameters of the rib need to be flexibly selected according to the actual situation such as the weight requirements of the parts.

[0011] Compared with the traditional upright orthogonal reinforcement layout, the present invention has the following advantages:

[0012] The present invention can solve the problem of insufficient stiffness and strength of lightweight thrust vector control wings under high temperature and high load conditions. By rationally arranging the ribs, the anti-buckling ability of the thrust vector control wing bottom plate is improved, and the maximum deformation degree of the thrust vector control wing bottom plate is reduced. In terms of engineering implementation, the rib layout of the thrust vector control wing can be completed by scaling and moving the rib layout scheme of the present invention according to the actual shape of the thrust vector control wing. The design efficiency is similar to that of the traditional rib layout, but the strength and stiffness performance of the structure are better than the traditional upright orthogonal rib layout scheme. While improving the stiffness and strength of the thrust vector control wing, the present invention also meets the needs of lightweight design without increasing the net weight of the ribs. In addition, parametric expression helps to achieve rapid modeling in engineering applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a top view of a ribbed layout structure applied to a thrust vector control wing in a specific implementation manner of the present invention.

[0014] Figure 2 It is a schematic structural diagram of a thrust vector control wing without reinforcement used in a specific embodiment of the present invention.

[0015] Figure 3 It is a schematic structural diagram of a thrust vector control wing using the ribbed layout of the present invention in a specific implementation manner of the present invention.

[0016] Figure 4 It is a schematic structural diagram of a thrust vector control wing using a conventional upright orthogonal ribbed layout in a specific implementation manner of the present invention.

[0017] Figure 5 This is a complex load condition set in a specific implementation manner of the present invention.

[0018] Figure 6 It is the temperature condition set in the specific implementation mode of the present invention.

[0019] Figure 7 In order to compare the performance of the thrust vector control wing structure using the rib layout of the present invention and the conventional upright orthogonal rib layout in terms of maximum displacement.

[0020] Figure 8 In order to compare the performance of the thrust vector control wing structure using the rib layout of the present invention and the traditional upright orthogonal rib layout in terms of maximum stress.

[0021] Fig. 9 In order to compare the performance of the thrust vector control wing structure using the rib layout of the present invention and the traditional upright orthogonal rib layout from the first-order buckling aspect.

[0022] Fig.10In order to compare the performance of the thrust vector control wing structure using the rib layout of the present invention and the traditional upright orthogonal rib layout in terms of second-order buckling.

[0023] In the figure: 1 the first rib; 2 the second rib; 3 the third rib; 4 the fourth rib; 5 the fifth rib; 6 the sixth rib; 7 the seventh rib; 8 the eighth rib; 9 the ninth rib; 10 the tenth rib; 11 the eleventh rib; 12 the twelfth rib; 13 the thirteenth rib; 14 the fourteenth rib; 15 the fifteenth rib; 16 the sixteenth rib; 17 the seventeenth rib; 18 the eighteenth rib; 19 the nineteenth rib; 20 the twentieth rib; 21 the twenty-first rib; 22 the twenty-second rib. DETAILED DESCRIPTION

[0024] In order to make the technical problems solved by the present invention, the technical solutions adopted and the technical effects achieved more detailed, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It is understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for the convenience of description, only the relevant parts of the present invention are shown in the accompanying drawings, rather than the entire contents.

[0025] Embodiment 1:

[0026] like Figure 1 As shown in FIG. 1 , a ribbed layout structure for a thrust vector control wing according to the present invention is shown. Figure 2 The figure shows a typical thrust vector control wing shell structure without rib reinforcement. Figure 1 The coordinate origin of the reinforcement layout is placed at the position of the actuator support or other types of actuating structures, and the appropriate proportional control dimension L is determined, so that the coordinates of all key nodes can be obtained, and then the layout positions of all ribs can be determined according to the key nodes, and the reinforcement layout can be obtained. The size parameters of the main-level ribs and the secondary-level ribs can be determined by the actual weight limit index. In Example 1, L is 71.5mm, and the part material is titanium alloy TA15. The final thrust vector control wing design is as follows: Figure 3 shown.

[0027] Create a control example, use the orthogonal reinforcement scheme, and layout the ribs of a typical thrust vector control wing structure. Also use titanium alloy TA15, such as Figure 4 To ensure the fairness of the comparison, Figure 4 The total structural weight of the structure shown is Figure 3 The overall weight of the structure shown remains approximately the same, specifically, Figure 3 The overall mass of the structure is 1.964 kg. Figure 4 The overall mass of the structure is 2.024 kg, which means that the orthogonal reinforcement scheme uses more material.

[0028] for Figure 3 and Figure 4 The reinforcement schemes shown are subjected to the same complex load conditions, such as Figure 5 As shown. The influence of temperature on structural performance is not involved at this time. Static finite element analysis is performed on the two reinforcement schemes to obtain the maximum displacement, maximum stress and the first two order buckling load factors of the structure. The comparison bar chart is shown in Figure 7 shown.

[0029] for Figure 3 and Figure 4 The reinforcement scheme shown is applied simultaneously Figure 5 The load conditions and Figure 6 Under conditions closer to the actual working environment of the thrust vector control wing, the two reinforcement schemes were subjected to thermal-mechanical coupling finite element analysis, and their respective maximum structural displacement, maximum stress value and minimum critical buckling load factor were recorded. The comparison bar chart is shown in the figure below. Figure 7 shown.

[0030] The smaller the maximum displacement value, the better the stiffness performance of the structure; the smaller the maximum stress value, the better the strength performance of the structure; the smaller the critical buckling load factor, the better the anti-buckling performance of the structure. Figure 7 to Figure 10 From the four groups of bar graphs, it can be found that the reinforcement layout scheme of the present invention not only outperforms the upright orthogonal reinforcement scheme in stiffness, strength and buckling resistance under static conditions while using less material and being lighter in weight, but also can still maintain its performance advantages under thermal-mechanical coupling conditions, especially in terms of displacement level and stress level. The advantages of the reinforcement layout scheme of the present invention are particularly significant.

[0031] Embodiment 2:

[0032] A rib layout structure applied to a thrust vector control wing includes a main-level rib layout and a secondary-level rib layout. The main-level rib layout includes a first rib, a second rib, a third rib, a seventh rib and a twelfth rib, as well as a sixteenth rib, a seventeenth rib, an eighteenth rib, a nineteenth rib, a twentieth rib, a twenty-first rib and a twenty-second rib, wherein the twentieth rib is a central longitudinal rib. The secondary-level rib layout includes an eighth rib, a ninth rib, a tenth rib, an eleventh rib, a fourth rib, a fifth rib, a sixth rib, a thirteenth rib, a fourteenth rib and a fifteenth rib.

[0033] The overall reinforcement structure layout is symmetrical, and the position of each rib is determined by the interconnection relationship between key nodes P1 to P9. Figure 1 The PO point shown in is the coordinate origin.

[0034] Place the coordinate origin PO at the connection position between the actuator support or other types of actuating structures and the control wing bottom plate; when the specific transmission connection position is unclear, the coordinate origin PO can be placed at the center of gravity of the control wing bottom plate. The distance between P0 and P1 is L.

[0035] The coordinates of nodes P1 to P9 are: P1 = (0, -L), P2 = (0, L),

[0036] Among the main-level ribs, the first rib, the second rib, and the third rib are curved ribs. The first rib passes through P3, P9, and the symmetric node of P9, and the three points are fitted by a spline curve, and extended to the control wing shell, thereby determining the position of the rib; the second rib passes through the origin P0, P7, P8, and the symmetric nodes of P7 and P8, and the five points are fitted by a spline curve, and extended to the control wing shell, thereby determining the position of the rib; the third rib passes through P1, P4, P5, P8, and the corresponding symmetric nodes, and the seven points are fitted by a spline curve, thereby determining the position of the rib.

[0037] In the main-level ribs, three points P6, P8, and P9 are fitted by spline curves, and the fitting line is extended to the control wing shell and intersects at points B1 and B2. Connect B1 and P8 to determine the position of the twelfth rib, and the seventh rib is symmetrical to it; connect P8 and P9 to determine the position of the eighteenth rib, and the twenty-second rib is symmetrical to it; connect P9 and B2 to determine the position of the nineteenth rib, and the twenty-first rib is symmetrical to it; connect P8 and P2 to determine the position of the sixteenth rib, and the seventeenth rib is symmetrical to it; the twentieth rib passes through P1, P0, P2, and P3, and is located at the symmetric center line of the entire rib layout. At this point, the layout positions of all main-level ribs are determined.

[0038] In the sub-level ribs, three points P7, P5, and P6 are fitted by spline curves, and the fitting line is extended to the control wing shell and intersects at point B3. Connect P7 and P5 to determine the position of the fifteenth rib, and the fourth rib is symmetrical with it; connect P5 and P6 to determine the position of the fourteenth rib, and the fifth rib is symmetrical with it; connect P6 and B3 to determine the position of the thirteenth rib, and the sixth rib is symmetrical with it; the positions of the eighth rib, the ninth rib, the tenth rib, and the eleventh rib are determined in combination with the shape of the actual control wing shell. Draw a vertical line from point P4 to the control wing shell to determine the position of the tenth rib, and the ninth rib is symmetrical with it; draw a vertical line from point P5 to the control wing shell to determine the position of the eleventh rib, and the eighth rib is symmetrical with it. At this point, the layout positions of all sub-level ribs are determined.

Claims

1. A ribbed layout structure applied to a thrust vector control wing, characterized in that: The invention comprises a main-level rib layout and a secondary-level rib layout; the main-level rib layout comprises a first rib (1), a second rib (2), a third rib (3), a seventh rib (7) and a twelfth rib (12), as well as a sixteenth rib (16), a seventeenth rib (17), an eighteenth rib (18), a nineteenth rib (19), a twentieth rib (20), a twenty-first rib (21) and a twenty-second rib (22), wherein the twentieth rib (20) is a central longitudinal rib; the secondary-level rib layout comprises an eighth rib (8), a ninth rib (9), a tenth rib (10), an eleventh rib (11), a fourth rib (4), a fifth rib (5), a sixth rib (6), a thirteenth rib (13), a fourteenth rib (14) and a fifteenth rib (15); The overall reinforcement layout structure is bilaterally symmetrical about the central axis, and the position of each rib is determined by the mutual connection relationship of key nodes P1 to P9; point PO is the origin of the coordinates; the coordinate origin PO is placed at the connection position between the actuating structure and the control wing bottom plate; The distance between P0 and P1 is L, and the coordinates of nodes P1 to P9 are: P1=(0,-L),P2=(0,L), Among the main-level ribs, the first rib (1), the second rib (2), and the third rib (3) are curved ribs; wherein the first rib (1) passes through P3, P9 and the symmetric node of P9, and the three points are fitted by a spline curve, and the rib is extended to the control wing shell, thereby determining the position of the rib; the second rib (2) passes through the origin P0, P7, P8 and the symmetric node of P7 and P8, and the five points are fitted by a spline curve, and the rib is extended to the control wing shell, thereby determining the position of the rib; the third rib (3) passes through P1, P4, P5, P8 and the corresponding symmetric node, and the seven points are fitted by a spline curve, thereby determining the position of the rib; In the main-level ribs, three points P6, P8 and P9 are fitted by a spline curve, and the fitting line is extended to the control wing shell and intersects at points B1 and B2; B1 and P8 are connected to determine the position of the twelfth rib (12), and the seventh rib (7) is symmetrical to it; P8 and P9 are connected to determine the position of the eighteenth rib (18), and the twenty-second rib (22) is symmetrical to it; P9 and B2 are connected to determine the position of the nineteenth rib (19), and the twenty-first rib (21) is symmetrical to it; P8 and P2 are connected to determine the position of the sixteenth rib (16), and the seventeenth rib (17) is symmetrical to it; the twentieth rib (20) passes through P1, P0, P2 and P3 and is located at the symmetrical center line of the entire rib layout; In the secondary ribs, three points P7, P5 and P6 are fitted by a spline curve, and the fitting line is extended to the control wing shell and intersects at point B3; P7 and P5 are connected to determine the position of the fifteenth rib (15), and the fourth rib (4) is symmetrical with the rib; P5 and P6 are connected to determine the position of the fourteenth rib (14), and the fifth rib (5) is symmetrical with the rib; P6 and B3 are connected to determine the position of the thirteenth rib (13), and the sixth rib (6) is symmetrical with the rib; the eighth rib (8), the ninth rib (9), the tenth rib (10) and the eleventh rib (11) are connected to the control wing shell; a vertical line is drawn from point P4 to the control wing shell to determine the position of the tenth rib (10), and the ninth rib (9) is symmetrical with the rib; a vertical line is drawn from point P5 to the control wing shell to determine the position of the eleventh rib (11), and the eighth rib (8) is symmetrical with the rib.

2. A ribbed layout structure for a thrust vector control wing according to claim 1, characterized in that: The coordinate origin PO is placed at the center of gravity of the control wing bottom plate.

3. The ribbed layout structure for a thrust vector control wing according to claim 1, characterized in that: The eighth rib (8), the ninth rib (9), the tenth rib (10), and the eleventh rib (11) are parallel to each other.

4. The ribbed layout structure for a thrust vector control wing according to claim 1, characterized in that: The secondary level rib height is selected within a range from one quarter to one third of the primary level rib height.

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