Bidirectional linkage locking hypersonic folding rudder wing structure

Abstract

The invention relates to the technical field of aircrafts, and discloses a two-way linkage locking hypersonic folding rudder wing structure which is composed of a movable rudder, a fixed rudder, an unfolding driving mechanism, a two-way linkage locking mechanism and a rear cover assembly. When a missile is ejected out of a launching barrel, the movable rudder rotates under the action of an unfolding driving mechanism, when the movable rudder rotates to the position where the movable rudder cannot abut against the locking pin, a locking spring I in the movable rudder pushes the locking pin into a chordwise locking pin hole of the fixed rudder, the locking pins on the two sides collide with guide rods at the same time, then the guide rods on the two sides extrude a bent sheet at the same time, and the bent sheet is unfolded. The bent sheet deforms, the pull rod is released, and the locking spring II in the fixed rudder pushes the locking block into the spanwise locking groove of the movable rudder; locking between the movable rudder and the fixed rudder is achieved in the chordwise direction and the spanwise direction, and the problem that when a hypersonic missile folding rudder wing structure is locked only in the chordwise direction, strength and rigidity are insufficient is solved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft, and in particular relates to a hypersonic folding rudder wing structure with bidirectional linkage locking. Background Art

[0002] Compared with box-type missiles, canister-type missiles can be launched by catapult. The cold launch method causes less damage to the internal structure of the launch tube. The launch tube can be put back into use after a simple repair, and it does not need to have complex and high-precision internal guide rails like the launch box. It has lower costs and better sealing. Canister-type missiles are now favored by various countries. Due to the structural characteristics of the launch tube, the rudder wings of canister-type missiles generally use folding rudder wings. Missiles with a Mach number greater than 5.0 are called hypersonic missiles. The folding rudder wings of hypersonic missiles are subject to large loads and severe aerodynamic heating. Aerodynamic heating will cause the folding rudder wing structure to heat up rapidly, with temperatures as high as thousands of degrees Celsius. Even though the folding rudder wings are generally protected by thermal insulation coatings, excessive temperatures will still greatly reduce the strength and rigidity of the folding rudder wing structure, thereby affecting the reliability of the missile.

[0003] The reduction of the strength and stiffness of the folding rudder wing structure under the action of large loads and aerodynamic heating means that only chord locking cannot provide sufficient strength and stiffness for the folding rudder wing structure. Due to the setting of the internal deployment drive mechanism and locking mechanism, the folding rudder wing is often provided with exposed parts such as operation windows and locking screws on the rudder surface, and the exposed parts are easily damaged under the combined action of force and heat, which leads to the failure of the locking mechanism inside the folding rudder wing. As a key component for providing aerodynamic control for missiles, once the folding rudder wing fails, the missile cannot complete the combat mission according to the preset instructions. Therefore, it is extremely important to design a folding rudder wing structure with high strength and stiffness, which is provided with exposed parts only at the trailing edge position where the influence of aerodynamic heating is the smallest. Summary of the invention

[0004] In view of the above situation, in order to solve the problem of insufficient strength and rigidity of the folding rudder wing structure of a hypersonic missile when only the chord-wise locking is used, the purpose of the present invention is to provide a hypersonic folding rudder wing structure with bidirectional linkage locking, so as to realize the locking of the folding rudder wing in both the span direction and the chord-wise direction, improve the force transmission path in the folding rudder wing, effectively improve the rigidity of the folding rudder wing as a whole and the strength of the connection after unfolding, and at the same time, only the exposed parts are provided at the trailing edge position where the influence of aerodynamic heating is the smallest, so as to effectively ensure the reliability of missile flight.

[0005] To achieve the above-mentioned purpose, the technical solution adopted by the present invention is: to provide a hypersonic folding rudder wing structure with bidirectional linkage locking, the structure of the folding rudder wing includes: a dynamic rudder, a fixed rudder, a deployment drive mechanism, a bidirectional linkage locking mechanism and a rear cover assembly; wherein the dynamic rudder and the fixed rudder are respectively connected to the deployment drive mechanism; the bidirectional linkage locking mechanism is divided into a chord-wise locking mechanism and a span-wise locking mechanism.

[0006] The dynamic rudder is provided with an upper hole and a lower hole along the chord direction, the upper hole is used to install the chord-wise locking mechanism, and the lower hole is used to install the deployment driving mechanism; the upper hole and the lower hole are each composed of a blind hole and a through hole, and their axes are respectively collinear; the dynamic rudder is provided with a locking groove along the span direction.

[0007] The fixed rudder is provided with two chord-wise through holes along the chord-wise direction, and the fixed rudder is provided with a groove along the span-wise direction; a step through hole is provided directly below the groove, and the upper through hole of the step through hole provides installation space and guiding function for the locking spring II, and the pull rod moves up and down through the lower through hole of the step through hole; both ends of the upper chord-wise through hole are tapered pin holes, and the lower chord-wise through hole is used to install the deployment drive mechanism, and the remaining space in the fixed rudder is used to install the span-wise locking mechanism.

[0008] The deployment drive mechanism comprises a cylindrical pin, a torsion bar, a front shaft and a rear shaft; the front shaft and the rear shaft are provided with square through holes at the axial position, which are used to limit the two ends of the torsion bar, play a role in force transmission, and also play a guiding role when assembling the rear shaft; the front shaft and the torsion bar are rigidly connected by a cylindrical pin, and the chordal freedom of the torsion bar is constrained by the cylindrical pin fixed on the torsion bar and the front shaft; the deployment drive mechanism and the dynamic rudder and the fixed rudder are fixed and force transmitted through the waist-shaped holes of the dynamic rudder and the fixed rudder and the waist-shaped features of the rear ends of the front shaft and the rear shaft; specifically, the dynamic rudder is fixed through the rear The waist-shaped hole at the rear end of the rotating shaft is connected to the unfolding drive mechanism, and the fixed rudder is connected to the unfolding drive mechanism through the waist-shaped hole at the rear end of the front rotating shaft; the front rotating shaft and the rear rotating shaft are provided with chamfers at the shape mutation points along the axial direction, so as to facilitate the front rotating shaft and the rear rotating shaft to be assembled in place; the rear ends of the front rotating shaft and the rear rotating shaft are both provided with two grooves, so as to facilitate the assembly of the front rotating shaft and the rear rotating shaft using tooling; two threaded holes are provided on the rear end surface of the rear rotating shaft, so as to facilitate pulling out the rear rotating shaft during disassembly; the front rotating shaft is connected to the torsion bar through a cylindrical pin, so as to facilitate applying force to the rear end of the torsion bar during disassembly, so as to pull out the torsion bar and the front rotating shaft together.

[0009] The bidirectional linkage locking mechanism is divided into a chord-wise locking mechanism and a span-wise locking mechanism. The span-wise locking mechanism is actuated by the action of the chord-wise locking mechanism. The chord-wise locking mechanism is composed of a locking pin, a locking spring I and a drilling gasket. One end of the locking pin is conical and the other end is a cylindrical structure with a threaded through hole on the axis. The drilling gasket is a circular ring gasket. The span-wise locking mechanism is composed of a bent sheet, a guide rod, a locking block, a pull rod and a locking spring II. Among them, the guide rod is a cylindrical rod in the middle, and the outer surfaces at both ends are used for guiding. Concave blocks are provided on both sides along the chord direction to facilitate the use of a long rod-shaped tooling to disassemble the front locking pin and locking block. Spring I; in the unfolded state, the pull rod leaves the limiting area of ​​the bending sheet; the guide rod is provided with two grooves for installing the bending sheet, and the bending sheet is dipped in glue and inserted into the grooves to achieve the fixing function; the bending sheet is a bent metal elastic sheet, and the two bending sheets are symmetrically arranged on both sides of the pull rod; the bending direction of the bending sheet is the direction away from the pull rod; in the folded state, the bending sheet can clamp the frustum feature of the pull rod; in the assembled or unfolded state, when subjected to the chordal external force during installation or the locking pin, the middle position of the bending sheet is deformed away from the pull rod, which does not affect the installation of the pull rod and the release when unfolded.

[0010] The chord-wise length of the bent sheet and the guide rod after assembly is 3-5 mm longer than the length of the circular through hole on the upper side of the fixed rudder, and the lengths of the guide rods on both sides protruding from the circular through hole on the upper side of the fixed rudder are the same, so as to ensure that the locking pins on both sides can hit the guide rods on both sides at the same time, thereby causing deformation of the bent sheet.

[0011] The upper end of the pull rod is a threaded section for achieving connection with the locking block, and a frustum is provided at the lower end of the pull rod; the conical surface of the frustum serves as a guide to press the frustum under the bent thin sheet during installation, and the frustum of the pull rod is clamped by the bent thin sheet when the folding rudder wing is assembled; when the folding rudder wing is in a folded state, the pull rod and the locking block are pulled by two symmetrical bent thin sheets so that the upper end surface of the locking block does not exceed the upper end surface of the fixed rudder.

[0012] An annular stop is provided at the threaded end of the pull rod, which controls the span length of the locking block and the pull rod after assembly from a design perspective; the locking block is a square pin with rounded edges, and is provided with a through hole and a threaded hole inside. The through hole provides installation space and guiding function for the locking spring II, and the threaded hole is used to install the pull rod.

[0013] The rear cover assembly includes a rear cover and rear cover screws. The rear cover limits the deployment drive mechanism and the chordal locking mechanism and serves as an operation window during installation and disassembly.

[0014] When the missile is ejected from the launch tube, the dynamic rudder rotates under the action of the deployment drive mechanism. When the dynamic rudder rotates to the position where it cannot resist the locking pin, the locking spring I in the dynamic rudder pushes the locking pin into the chord-wise locking pin hole of the fixed rudder. The locking pins on both sides hit the guide rod at the same time, and then the guide rods on both sides squeeze the bending sheet at the same time, causing the bending sheet to deform and release the pull rod. The locking spring II in the fixed rudder pushes the locking block into the span-wise locking groove of the dynamic rudder. The locking between the dynamic rudder and the fixed rudder is achieved in both the chord-wise and span-wise directions.

[0015] The invention relates to a method for assembling a folding rudder wing, comprising the following steps: Step 1: Dip the bent sheet in glue and insert it into the groove of the guide rod, and install the whole piece into the chord-up side hole of the fixed rudder; Step 2: Install locking spring II into the fixed rudder; Step 3: Assemble the tie rod on the locking block through threaded connection, install the whole into the fixed rudder, apply force to both ends of the exposed guide rod, and apply pressure to the locking block so that the truncated cone feature of the tie rod is stuck by the bent sheet; Step 4: Install the drilling gasket, locking spring I and locking pin into the dynamic rudder in sequence; Step 5: Assemble the movable rudder and the fixed rudder into the folded state, so as to use the front rotating mating surface of the fixed rudder to hold the locking pin; Step 6: Connect the front end of the torsion bar and the front shaft through a cylindrical pin, and insert it into the shaft holes of the dynamic rudder and the fixed rudder. Use a tool to clamp the two grooves at the rear end of the front shaft to adjust the angle and assemble the front shaft in place. Step 7: Install the rear shaft along the torsion bar into the shaft holes of the dynamic rudder and the fixed rudder, use a tool to clamp the two grooves at the rear end of the rear shaft to adjust the angle, and assemble the rear shaft in place; Step 8: Install the rear locking pin and locking spring I in sequence; Step 9: Use the rear cover screws to assemble the rear cover on the dynamic rudder.

[0016] The invention relates to a method for disassembling a folding rudder wing, comprising the following steps: Step 1: Remove the constraints from the folded rudder wings and unfold them automatically; Step 2: Remove the back cover screws and back cover; Step 3: Remove the rear locking spring I and locking pin; Step 4: Use the two threaded holes on the rear end face of the rear shaft to pull out the rear shaft; Step 5: Use pliers to hold the rear end of the torsion bar and pull out the front shaft; Step 6: Use a long rod-shaped tool to press the front locking pin into the inside of the dynamic rudder and lift the dynamic rudder upward; Step 7: Remove the remaining parts.

[0017] The beneficial effects of the present invention are as follows: the problem of insufficient strength and rigidity of the folding rudder wing structure of a hypersonic missile when only the chord-wise locking is used is effectively solved; locking of the folding rudder wing in both the spanwise and chordwise directions is achieved, the force transmission path in the folding rudder wing is improved, the rigidity of the entire folding rudder wing and the strength of the connection after unfolding are effectively improved, and at the same time, exposed parts are only provided at the trailing edge position where the influence of aerodynamic heating is minimal, thereby effectively ensuring the reliability of missile flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of the folding rudder wing structure in the unfolded state; Figure 2 is a schematic diagram of the folding rudder wing structure in a folded state; Figure 3 This is a comparison of the folded state (left) and unfolded state (right) of the spanwise locking mechanism; Figure 4 It is a schematic diagram of the bending sheet and the guide rod under the state of no force; Figure 5 It is a simulation schematic diagram of the bending sheet and the guide rod under stress; Figure 6 It is a schematic diagram of the pull rod structure; Figure 7 1. It is a schematic diagram of the locking block structure; Figure 8 It is a schematic diagram of each cross section of the rotating shaft hole in the unfolded state; Fig. 9 is a schematic diagram of the unfolding drive mechanism in the unfolded state; Fig.10 This is a schematic diagram of using the fixed rudder to resist the locking pin in the folded state; Fig.11 It is a schematic diagram of the present invention using a long rod-shaped tool to dismantle the front locking pin and the locking block; In the figure, 1. dynamic rudder; 2. fixed rudder; 3. locking pin; 4. locking spring I; 5. drilling gasket; 6. cylindrical pin; 7. torsion bar; 8. front rotating shaft; 9. rear rotating shaft; 10. bending sheet; 11. guide rod; 12. locking block; 13. pull rod; 14. locking spring II; 15. rear cover; 16. rear cover screw. DETAILED DESCRIPTION

[0019] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0020] The present invention provides a hypersonic folding rudder wing structure with bidirectional linkage locking to solve the problem that sufficient strength and rigidity cannot be provided for the folding rudder wing structure of a hypersonic missile when only chord-wise locking is used, and exposed parts are provided only at the trailing edge position where the influence of aerodynamic heating is minimal to reduce the damage of aerodynamic heating to the internal structure of the folding rudder wing.

[0021] It should be noted that the front mentioned in the present invention refers to the end close to the leading edge of the folding rudder wing, and the opposite is the rear; the end close to the slight chord of the folding rudder wing is the top, and the opposite is the bottom.

[0022] like Figure 1 , 2 As shown, the present invention provides a hypersonic folding rudder wing structure with bidirectional linkage locking, which, through an unfolding drive mechanism and a bidirectional linkage locking mechanism, unfolds and locks the folding rudder wing after the missile is ejected from the launch tube; there are two sets of front and rear rotating mating surfaces between the dynamic rudder 1 and the fixed rudder 2, which are respectively connected by the front rotating shaft 8 and the rear rotating shaft 9. The dynamic rudder in this embodiment adopts a radial grid wing surface structure; a torsion bar is selected to provide the dynamic rudder with an unfolding driving force, and the torsion bar stores torsional elastic potential energy when it is in a folded state. When the missile is ejected from the launch tube, the elastic recovery of the torsion bar causes the dynamic rudder to rotate around the unfolding drive mechanism; the selected springs are all cylindrical helical compression springs, which have mature manufacturing technology, low cost and good reliability.

[0023] like Figure 1 As shown, one end of the locking pin 3 is conical and the other end is a cylindrical structure, and a threaded through hole is provided on the axis, which is convenient for pulling out the rear locking pin 3 from the rear cover using tooling; the drilled gasket 5 is a circular gasket, which provides a force application plane for the locking spring I4, and its inner hole is convenient for disassembly using tooling.

[0024] like Figure 2 As shown, the chord-wise length of the bent sheet 10 and the guide rod 11 after assembly is 3-5 mm longer than the length of the circular through hole on the upper side of the fixed rudder 2, and the lengths of the guide rods 11 on both sides protruding from the circular through holes on the upper side of the fixed rudder 2 are the same, to ensure that the locking pins 3 on both sides can hit the guide rods 11 on both sides at the same time, thereby causing the bent sheet 10 to deform.

[0025] like Figure 3 , 4 As shown in Figure 5, the middle of the guide rod 11 is a cylindrical rod to reduce the weight of the guide rod 11. The outer surfaces at both ends are used for guiding. Concave blocks are provided on both sides along the chord direction to facilitate the removal of the locking pin 3 and the locking spring Ⅰ4 in front by using a long rod-shaped tooling; when in the unfolded state, the pull rod 13 leaves the limiting area of ​​the curved sheet 10. The guide rod 11 is provided with two grooves for installing the curved sheet 10. The curved sheet 10 is dipped in glue and inserted into the grooves to achieve the function of fixing. It can also be designed as a screw fixing form. The curved sheet 10 is a metal elastic curved sheet with a small curvature, which is symmetrically installed on both sides of the pull rod 13. When the folding rudder wing is assembled, the curved sheet 10 clamps the truncated cone feature of the pull rod 13.

[0026] like Figure 3 , 4As shown in Figure 5, when both ends of the guide rod 11 are subjected to the chord-wise force during installation or the locking pin 3, the middle position of the bending sheet 10 is deformed away from the pull rod 13. During the deformation process, the pull rod 13 is released, and the locking spring II 14 in the fixed rudder 2 pushes the locking block 12 into the span-wise locking groove of the dynamic rudder 1. During assembly, a small amount of glue is applied to both ends of the guide rod 11 for fixing. The amount of glue applied should ensure that the connection between the guide rod 11 and the fixed rudder 2 is reliable under an overload of 10g when the missile leaves the tube, and also ensure that the movement of the guide rod 11 under the impact of the locking pin 3 is not affected.

[0027] It should be noted that the guide rod 11 and the upper through hole of the fixed rudder 2 can also be fixed by setting a fixing screw with a breaking function starting from the upper end surface of the fixed rudder 2, and breaking the fixing screw by the impact of the locking pin 3 on the guide rod 11, thereby achieving the above function.

[0028] like Figure 6 As shown, the upper end of the tie rod 13 is a threaded section for connection with the locking block 12, and a truncated cone is provided at the lower end, and the conical surface of the truncated cone serves as a guide to press the truncated cone feature under the curved sheet 10 during installation. When the folding rudder wing is in the folded state, the tie rod 13 and the locking block 12 are pulled by two symmetrical curved sheets 10, so that the upper end surface of the locking block 12 does not exceed the upper end surface of the fixed rudder 2. Furthermore, an annular stop can be provided at the threaded end of the tie rod 13 to control the span length of the locking block 12 and the tie rod 13 after assembly from the design point of view.

[0029] like Figure 7 As shown, the locking block 12 is a square pin with rounded sides, and is provided with a through hole and a threaded hole. The through hole provides installation space and a guiding function for the locking spring II 14, and the threaded hole is used to install the pull rod 13.

[0030] like Figure 8 As shown, the lower side hole of the moving rudder 1 and the lower side hole of the fixed rudder 2 together form a shaft hole for assembling the unfolding drive mechanism. If the moving rudder 1 and the fixed rudder 2 are regarded as one body, the shaft hole can be composed of four parts. From the leading edge to the trailing edge, they are the first part, the second part, the third part and the fourth part. The first part and the third part are circular holes, which serve as the rotating holes of the moving rudder 1 and the fixed rudder 2 respectively. The second part is a waist-shaped hole with the same diameter as the third part, and its parallel surface is tangent to the circular hole of the first part; the fourth part is a waist-shaped hole, and its parallel surface is tangent to the circular hole of the third part. Except for the first part which is a blind hole, the rest are through holes, and chamfers are provided at the transition positions of each part to make it more in line with the processing requirements. The function of the parallel plane is to provide a connection interface between the unfolding drive mechanism and the moving rudder 1 and the fixed rudder 2 for realizing force transmission.

[0031] like Figure 1 , 2As shown in , 9, the front rotating shaft 8 and the rear rotating shaft 9 are provided with square through holes at the axial position, which are used to limit the two ends of the torsion bar 7, play a role in force transmission, and also play a guiding role when assembling the rear rotating shaft 9; the front rotating shaft 8 and the rear rotating shaft 9 are both provided with waist-shaped features at the rear end, which are respectively connected with the waist-shaped holes of the dynamic rudder 1 and the fixed rudder 2 to achieve fixation and force transmission; the front rotating shaft 8 and the rear rotating shaft 9 are provided with chamfers at the shape mutation points along the axial direction, which is convenient for the front rotating shaft 8 and the rear rotating shaft 9 to be assembled in place; the rear ends of the front rotating shaft 8 and the rear rotating shaft 9 are both provided with two grooves, so as to facilitate the assembly of the front rotating shaft 8 and the rear rotating shaft 9 by using tooling; two threaded holes are provided on the rear end surface of the rear rotating shaft 9, which is convenient for pulling out the rear rotating shaft 9 during disassembly; the front rotating shaft 8 and the torsion bar 7 are connected by a cylindrical pin 6, which is convenient for applying force to the rear end of the torsion bar 7 during disassembly, so as to pull out the torsion bar 7 and the front rotating shaft 8 together.

[0032] like Fig.10 As shown, in the folded state, the front locking pin 3 is limited in the upper blind hole of the dynamic rudder 1 by using the fixed rudder 2.

[0033] like Fig.11 As shown, a method for disassembling the front locking pin 3 and the locking spring I 4 using a rod-shaped tooling is provided after removing the rear cover assembly, the rear chordal locking mechanism and the deployment drive mechanism.

Claims

1. A hypersonic folding rudder wing structure with two-way linkage locking, the folding rudder wing consists of five parts: a moving rudder, a fixed rudder, an unfolding drive mechanism, a two-way linkage locking mechanism and a rear cover assembly, wherein the moving rudder and the fixed rudder are connected by the unfolding drive mechanism; characterized in that: The dynamic rudder is provided with an upper hole and a lower hole along the chord direction, the upper hole is used to install the chord-wise locking mechanism, and the lower hole is used to install the deployment drive mechanism; the upper hole and the lower hole are each composed of a blind hole and a through hole, and their axes are respectively collinear; the dynamic rudder is provided with a locking groove along the span direction; The fixed rudder is provided with two chord-wise through holes along the chord-wise direction, and the fixed rudder is provided with a groove along the span-wise direction; a step through hole is provided directly below the groove, and the upper through hole of the step through hole provides installation space and guide function for the locking spring II, and the pull rod moves up and down through the lower through hole of the step through hole; both ends of the upper chord-wise through hole are tapered pin holes, and the lower chord-wise through hole is used to install the deployment drive mechanism, and the remaining space in the fixed rudder is used to install the span-wise locking mechanism; The movable rudder is connected to the unfolding drive mechanism through the waist-shaped hole at the rear end of the rear shaft, and the fixed rudder is connected to the unfolding drive mechanism through the waist-shaped hole at the rear end of the front shaft; The deployment drive mechanism comprises a cylindrical pin, a torsion bar, a front rotating shaft and a rear rotating shaft; the square hole of the front rotating shaft limits the front end of the torsion bar, and the square hole of the rear rotating shaft limits the rear end of the torsion bar; the front rotating shaft and the torsion bar are rigidly connected by a cylindrical pin, and the chordal freedom of the torsion bar is constrained by the cylindrical pin fixed on the torsion bar and the front rotating shaft; the front rotating shaft and the rear rotating shaft are provided with chamfers at the sudden changes in shape along the axial direction, and the rear ends of the front rotating shaft and the rear rotating shaft are both provided with two grooves; and two threaded holes are provided on the rear end surface of the rear rotating shaft; The bidirectional linkage locking mechanism is divided into a chord-wise locking mechanism and a span-wise locking mechanism. The span-wise locking mechanism is activated by the action of the chord-wise locking mechanism. The chord-wise locking mechanism comprises a locking pin, a locking spring I and a drilling gasket. One end of the locking pin is conical and the other end is cylindrical, with a threaded through hole provided on the axis. The drilling gasket is a circular ring gasket. The span-wise locking mechanism comprises a curved sheet, a guide rod, a locking block, a pull rod and a locking spring II; wherein the middle of the guide rod is a cylindrical rod, the outer surfaces at both ends are used for guiding, and concave blocks are provided on both sides along the chord direction; the guide rod is provided with two grooves for installing the curved sheet, the curved sheet is a curved metal elastic sheet, and the two curved sheets are symmetrically arranged on both sides of the pull rod; The rear cover assembly includes a rear cover and rear cover screws. The rear cover limits the deployment drive mechanism and the chordal locking mechanism and serves as an operation window during installation and disassembly. When the missile is ejected from the launch tube, the dynamic rudder rotates under the action of the deployment drive mechanism. When the dynamic rudder rotates to the position where it cannot resist the locking pin, the locking spring I in the dynamic rudder pushes the locking pin into the chord-wise locking pin hole of the fixed rudder. The locking pins on both sides hit the guide rod at the same time, and then the guide rods on both sides squeeze the bending sheet at the same time, causing the bending sheet to deform and release the pull rod. The locking spring II in the fixed rudder pushes the locking block into the span-wise locking groove of the dynamic rudder. The locking between the dynamic rudder and the fixed rudder is achieved in both the chord-wise and span-wise directions.

2. A bidirectionally linked and locked hypersonic folding rudder wing structure according to claim 1, characterized in that: The upper end of the pull rod is a threaded section, and the lower end is provided with a frustum. The conical surface of the frustum serves as a guide to press the frustum feature under the bent thin sheet during installation. When the folding rudder wing is assembled, the frustum of the pull rod is clamped by the bent thin sheet. When the folding rudder wing is in a folded state, the pull rod and the locking block are pulled by two symmetrical bent thin sheets.

3. A bidirectionally linked locking hypersonic folding rudder wing structure according to claim 1, characterized in that: The bending direction of the bending sheet is the direction away from the pull rod; when in the folded state, the bending sheet can clamp the truncated cone feature of the pull rod; In the assembled or unfolded state, when subjected to the chordal external force during installation or by the locking pin, the middle portion of the bending sheet is deformed away from the pull rod.

4. A bidirectionally linked and locked hypersonic folding rudder wing structure according to claim 1, characterized in that: The bidirectional linkage locking mechanism enables the span-wise locking mechanism to be actuated through the action of the chord-wise locking mechanism.

5. The hypersonic folding rudder wing structure with bidirectional linkage locking according to claim 1, characterized in that: The locking block is a square pin with rounded sides, and is provided with a through hole and a threaded hole. The through hole provides installation space and a guiding function for the locking spring II, and the threaded hole is used to install the pull rod.

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