Three-way linkage locking folding rudder wing structure

Abstract

The invention relates to the technical field of aircrafts, and discloses a three-way linkage locking folding rudder wing structure which comprises a movable rudder, a fixed rudder, an unfolding driving mechanism and a three-way linkage locking mechanism. The movable rudder and the fixed rudder are connected through an unfolding driving mechanism, after external constraint is removed, the movable rudder rotates under the action of the unfolding driving mechanism, and when the movable rudder rotates to the position where the movable rudder cannot abut against the locking pin, a locking spring in the fixed rudder pushes the locking pin into a chordwise locking pin hole of the movable rudder, and the fixed rudder is unfolded. When the elastic potential energy of the locking spring is reduced to be consistent with the elastic potential energy of the special-shaped spring, the special-shaped spring also starts to release the elastic potential energy, and the locking block is pushed into a spanwise locking groove of the movable rudder; locking between the movable rudder and the fixed rudder is achieved in three directions, and the strength of the joint is greatly improved; the problem that when the folding rudder wing of the hypersonic missile is only locked in the chordwise direction, the strength of the connecting position is insufficient is solved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft, and in particular relates to a three-way linked locking folding rudder wing structure. Background Art

[0002] As a key component for providing aerodynamic control torque for missiles, folding rudder wings can realize the attitude adjustment of missiles during flight. Their folding characteristics can effectively improve the loading density of missiles, and are the mainstream trend of the development of hypersonic missile rudder wings. Due to the high flight speed of hypersonic missiles, the load on the folding rudder wings is very large, and only chord-wise locking cannot provide sufficient strength for the folding rudder wings. At present, the chord-wise locking mechanism generally uses the rotating mating surface between the dynamic rudder and the fixed rudder to resist the locking pin, while the span-wise locking mechanism generally limits the locking pin before deployment by locking nut limiting and circular rotating surface limiting. However, these two typical solutions are limited in application. Therefore, it is necessary to design a folding rudder wing mechanism with fewer restrictions and both span-wise and chord-wise locking capabilities.

[0003] The patent application with the publication number CN117053635A discloses a high-load hypersonic folding rudder that is adaptable to thermal deformation. The folding rudder adopts a multi-pin locking structure composed of four spanwise locking pins, which can withstand a large value of normal aerodynamic loads. However, this type of folding rudder will cause the locking nut and some of the cut-off locking pins to fly out of the rudder surface, becoming redundant during the missile launch process, reducing the reliability of the launch process.

[0004] The patent with authorization announcement number CN114426094B discloses a foldable air rudder for hypersonic aircraft, which can be locked in multiple directions of radial and axial directions at the same time, significantly improving the strength of the air rudder connection. This type of foldable air rudder realizes the constraint of the spanwise locking pin and the locking spring in the folded state through the circular rotating surface matched between the dynamic rudder and the fixed rudder; the circular rotating surface causes the cross-sectional area near the rudder axis to be too large, increasing the aerodynamic resistance; this structural scheme has a large area of ​​exposed operating window on the rudder surface, which is not suitable for all hypersonic aircraft; this structural scheme is too complicated, resulting in high cost; it should be noted that the radial direction is the spanwise direction described in this patent, and the axial direction is the chordwise direction described in this patent. Summary of the invention

[0005] In view of the above situation, in order to solve the problem that only chord-wise locking cannot provide sufficient strength for the folding rudder wing of a hypersonic missile, the purpose of the present invention is to provide a folding rudder wing structure with three-way linkage locking to achieve locking in multiple directions of the folding rudder wing in the span direction and the chord direction, improve the force transmission path in the folding rudder wing, improve the overall stiffness of the folding rudder wing and the strength of the connection after unfolding, and at the same time achieve no excess material in the unfolding process of the folding rudder wing, effectively ensuring the reliability of missile launch.

[0006] To achieve the above-mentioned purpose, the technical solution adopted by the present invention is: to provide a three-way linked locking folding rudder wing structure, whose structure includes: a dynamic rudder, a fixed rudder, a deployment drive mechanism and a three-way linked locking mechanism; the dynamic rudder and the fixed rudder are both provided with threaded through holes on both sides of the symmetrical rudder surface for connecting the deployment drive mechanism.

[0007] The dynamic rudder is provided with a through hole and a pair of coaxial and opposite conical locking pin holes along the chord direction, and a locking groove along the span direction; the through hole cooperates with the lower through hole of the fixed rudder to install the deployment drive mechanism; the front section aperture of the through hole is slightly smaller than the rear section aperture to facilitate the installation and disassembly of the front rotating shaft.

[0008] The fixed rudder is provided with upper and lower through holes and two operating windows along the chord direction, and a groove along the span direction; the upper through hole and the operating window are used for installing and disassembling the sliding block, the locking spring and the locking pin, and the aperture of the lower through hole is slightly smaller in the front section than in the rear section, so as to facilitate the installation and disassembly of the front rotating shaft; the side of the operating window in contact with the locking pin, the locking spring and the sliding block is a circular arc surface, which is used in conjunction with aviation high and low temperature grease during assembly to disassemble the locking pin, the locking spring and the sliding block.

[0009] The moving rudder and the fixed rudder are both provided with threaded through holes on both sides of the symmetrical rudder surface for installing the front shaft screw and the rear shaft screw. The moving rudder is fixed to the unfolding drive mechanism through the front shaft screw; the fixed rudder is fixed to the unfolding drive mechanism through the rear shaft screw.

[0010] The unfolding drive mechanism comprises a front rotating shaft screw, a rear rotating shaft screw, a cylindrical pin, a torsion bar, a front rotating shaft and a rear rotating shaft; the dynamic rudder and the fixed rudder are connected through the unfolding drive mechanism; the front rotating shaft is fixed to the dynamic rudder through the front rotating shaft screw; the rear rotating shaft is fixed to the fixed rudder through the rear rotating shaft screw; 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 chord-wise degree of freedom of the torsion bar is constrained by the cylindrical pin fixed on the torsion bar and the front rotating shaft; when the dynamic rudder is rotated and folded around the front rotating shaft and the rear rotating shaft, the torsion bar stores torsional elastic potential energy, which serves as the unfolding drive when the constraints of the folded rudder wings are removed.

[0011] The three-way linkage locking mechanism comprises an operating cover plate, a cover plate screw, a locking block, a special-shaped spring, a fixing screw, a sliding block, a locking spring and a locking pin; in a folded state, the locking spring presses the locking pin against the rotating surface of the moving rudder, and the locking spring presses the sliding block against the special-shaped spring; the locking block is constrained inside the fixed rudder by the special-shaped spring; the operating cover plate is mounted on the rudder surface through the cover plate screw; the special-shaped spring is mounted in the groove of the fixed rudder through the fixing screw; the locking block and the locking pin are both mounted in the fixed rudder; after removing the external constraints, the driving mechanism is deployed to make the moving rudder start to rotate, when the moving rudder rotates to a position where it cannot resist the locking pin, the locking spring in the fixed rudder pushes the locking pin into the chord-wise locking pin hole of the moving rudder, when the elastic potential energy of the locking spring drops to the same as the elastic potential energy of the special-shaped spring, the special-shaped spring also starts to release the elastic potential energy, and pushes the locking block into the span-wise locking groove of the moving rudder, thereby realizing locking in three directions of one span direction and two chord directions, and realizing reliable locking of the folded rudder wing.

[0012] The middle part of the locking block is provided with a structure composed of a curved surface and an inclined surface, which plays a guiding and restraining role when compressing the special-shaped spring; during the transportation of the missile, if the elastic element is deformed under vibration, it can automatically adjust the locking block to zero.

[0013] When the special-shaped spring is stressed, elastic deformation will occur in both the spanwise and chordwise directions. When the folding rudder wing is unfolded, the elastic recovery of the special-shaped spring in the spanwise direction pushes the locking block into the spanwise locking groove of the dynamic rudder.

[0014] The through holes for installing the front shaft screw, the rear shaft screw and the cover screw are all arranged perpendicular to the center plane of the rudder.

[0015] The deployment drive mechanism comprises two rotating shafts, a front rotating shaft and a rear rotating shaft. During the rotation of the dynamic rudder, the front rotating shaft rotates together with the dynamic rudder, and the rear rotating shaft remains stationary together with the fixed rudder; the rear section of the front rotating shaft serves as the rotating shaft of the fixed rudder, and the rear section of the rear rotating shaft serves as the rotating shaft of the dynamic rudder.

[0016] The unfolding drive mechanism has a torsion bar and an elastic element, and the three-way linkage locking mechanism has three elastic elements: a special-shaped spring and two locking springs.

[0017] The outer diameter of the front shaft is slightly smaller than the outer diameter of the rear shaft to ensure the efficiency of assembling and disassembling the front shaft.

[0018] The tails of the front shaft and the rear shaft are both provided with two grooves to facilitate the installation of the front shaft screw and the rear shaft screw; the rear end surface of the rear shaft is provided with two threaded holes to facilitate pulling out the rear shaft during disassembly.

[0019] The locking block has a rectangular cross-section, the front end of the locking pin has a conical cross-section, and the locking pin is a group of identical parts assembled in reverse at both ends of the upper through hole of the fixed rudder, thereby increasing the bearing area, improving the force transmission path in the folding rudder wing, and improving the strength of the connection.

[0020] The sliding block and the locking pin are provided with dovetail grooves on the end faces visible from the operation window, and the sliding block and the locking pin can be disassembled by using a special tool under the action of impulse.

[0021] An assembly method of a three-way linked locking folding rudder wing structure comprises the following steps: Step 1: Use the fixing screw to install the special-shaped spring into the groove of the fixed rudder; Step 2: Use a cylindrical pin to connect the front end of the torsion bar and the front shaft into one piece, and insert it into the shaft holes of the dynamic rudder and the fixed rudder. By turning the torsion bar or using a special tool to clamp the two grooves at the rear end of the front shaft, turn the pin hole on the front shaft to align with the front shaft screw hole on the dynamic rudder, and screw in the front shaft screw; Step 3: Install the rear shaft along the torsion bar into the shaft holes of the dynamic rudder and the fixed rudder, use a special tool to clamp the two grooves at the rear end of the rear shaft, rotate the pin hole on the rear shaft to align with the rear shaft screw hole on the fixed rudder, and screw in the rear shaft screw; Step 4: Rotate the dynamic rudder to the folded state and keep it; Step 5: The locking block and the sliding block are pressed into the fixed rudder. Only after passing the inspection can the next step of assembly be carried out; Step 6: Install the locking pin into the fixed rudder, use the moving rudder to hold the locking pin, and press in the locking spring; Step 7: Install the operating cover onto the fixed rudder using the cover screws.

[0022] A disassembly method of a three-way linked locking folding rudder wing structure comprises the following steps: Step 1: Remove the constraints from the folded rudder wings and unfold them automatically; Step 2: Remove the operating cover and cover screws; Step 3: Take out the locking spring and use a special tool to take out the locking pin; Step 4: Push the sliding block to move the locking block out of the spanwise locking groove of the dynamic rudder; Step 5: Rotate the dynamic rudder to the folded state and keep it; Step 6: Remove the sliding block, locking block, fixing screw and special-shaped spring in sequence; Step 7: Remove the front and rear pivot screws; Step 8: Use the threaded hole on the rear end face of the rear shaft to pull out the rear shaft, clamp the rear end of the torsion bar, and pull out the front shaft.

[0023] The beneficial effects of the present invention are as follows: the problem that only chord-wise locking cannot provide sufficient strength for the folding rudder wing of a hypersonic missile is effectively solved; locking of the folding rudder wing in multiple directions, both in the span direction and the chord-wise direction, is achieved, the force transmission path in the folding rudder wing is improved, the overall rigidity of the folding rudder wing is effectively improved, the strength of the connection after unfolding is greatly improved, and during the unfolding process of the folding rudder wing, no redundant material is generated, thereby effectively ensuring the reliability of missile launch. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a typical schematic diagram of the spanwise locking mechanism of a locking nut; Figure 2 This is a typical schematic diagram of a circular rotating surface span-wise locking mechanism; Figure 3 is a schematic diagram of the folding rudder wing of the present invention in the unfolded state; Figure 4 It is a schematic diagram of the folding rudder wing structure in the unfolded state of the present invention; Figure 5 is a schematic diagram of the folding rudder wing of the present invention in a folded state; Figure 6 It is a schematic diagram of the folding rudder wing structure in the folded state of the present invention; Figure 7 It is a schematic diagram of the internal parts of the folding rudder wing of the present invention in the unfolded state; Figure 8 It is a schematic diagram of the special-shaped spring in different states; In the figure, 1, dynamic rudder; 2, fixed rudder; 3, front shaft screw; 4, rear shaft screw; 5, operating cover; 6, cover screw; 7, locking block; 8, special-shaped spring; 9, fixing screw; 10, sliding block; 11, locking spring; 12, locking pin; 13, cylindrical pin; 14, torsion bar; 15, front shaft; 16, rear shaft. DETAILED DESCRIPTION

[0025] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0026] The present invention provides a folding rudder wing structure with three-way linkage locking to solve the problem that only chord-wise locking cannot provide sufficient strength for the folding rudder wing of a hypersonic missile, and solves the problem that a traditional span-wise locking mechanism will produce redundant materials and the locking mechanism is too complicated and bloated.

[0027] 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.

[0028] like Figure 1The figure shows a typical locking mechanism for a locking nut. Its working principle is to cut off the locking nail on the locking nut through the rotating rudder, so that the locking pin under the locking nut is freed and popped out under the action of the spring. Figure 2 The figure shows a typical schematic diagram of a circular rotating surface span-wise locking mechanism. Its working principle is that when the folding rudder wing has not been rotated to the unfolded state, the circular rotating surface on the fixed rudder is used to constrain the locking pin inside the moving rudder until it rotates to the unfolded position. Under the action of the spring, the locking pin is bounced into the corresponding locking pin hole.

[0029] like Figure 3 , 4 As shown, the present invention provides a folding rudder wing structure with three-way linkage locking, which consists of four parts: a moving rudder 1, a fixed rudder 2, an unfolding drive mechanism, and a three-way linkage locking mechanism; the fixed rudder 2 is inserted into the rudder wing cabin body and connected to the steering gear to achieve attitude adjustment of the missile during flight; through the unfolding drive mechanism and the three-way linkage locking mechanism, the folding rudder wing is unfolded and locked after the missile is ejected from the launch tube; there are two sets of front and rear rotating matching surfaces between the moving rudder 1 and the fixed rudder 2, which are respectively connected by a front rotating shaft 15 and a rear rotating shaft 16.

[0030] like Figure 4 As shown, the sizes of the special-shaped spring 8, the locking spring 11 and the torsion bar 14 need to be accurately calculated according to the moment of inertia and the deployment time of the dynamic rudder 1; the function of the special-shaped spring 8 and the locking spring 11 is to provide power for the locking block 7 and the locking pin 12. When the folding rudder wing is folded, the special-shaped spring 8 and the locking spring 11 are both in a compressed state; the outer contour of the locking block 7 is used as a guide to provide a span-wise force on the special-shaped spring 8 during installation; the outer diameter of the sliding block 10 is used as a guide to provide a chord-wise force on the special-shaped spring 8 during installation.

[0031] like Figures 3 to 7 As shown, the dynamic rudder 1 uses the torsion bar 14 as the deployment drive, and the dynamic rudder 1 is connected to the torsion bar 14 through the front shaft screw 3 and the front shaft 15; the fixed rudder 2 is connected to the torsion bar 14 through the rear shaft screw 4 and the rear shaft 16; when the dynamic rudder 1 rotates, the rear end of the torsion bar 14 and the rear shaft 16 remain stationary with the fixed rudder 2, and the front end of the torsion bar 14 and the front shaft 15 rotate with the dynamic rudder 1, resulting in the torsion bar 14 forming a torsional elastic deformation within the elastic range.

[0032] like Figure 3 , 7 As shown, the front shaft screw 3 and the rear shaft screw 4 are composed of a threaded section, a cylindrical section and a slotted groove. The section with a larger diameter is a threaded section, which cooperates with the front shaft threaded holes and the rear shaft threaded holes on both sides of the rudder surface; the section with a smaller diameter is a smooth cylindrical section, which cooperates with the pin holes on the front shaft 15 and the rear shaft 16.

[0033] like Figure 4 As shown, the function of the locking block 7 and the locking pin 12 is to enter the span-wise locking groove and the chord-wise locking pin hole corresponding to the dynamic rudder 1 from the fixed rudder 2 after the folding rudder wing is unfolded, so as to realize the reliable locking of the folding rudder wing; in order to facilitate the disassembly of the folding rudder wing, the structure composed of the curved surface and the inclined surface in the middle position of the locking block 7 can use the sliding block 10 to compress the special-shaped spring 8 and retract the locking block 7 into the fixed rudder 2; a dovetail groove is provided at the tail of the locking pin 12 for easy disassembly; the aperture diameter of the front rotating shaft hole of the dynamic rudder 1 is consistent with the aperture diameter of the front section of the rotating shaft hole of the fixed rudder 2, and the aperture diameter is smaller; the aperture diameter of the rear rotating shaft hole of the dynamic rudder 1 is consistent with the aperture diameter of the rear section of the rotating shaft hole of the fixed rudder 2, and the aperture diameter is larger; it is convenient for the installation and disassembly of the front rotating shaft 15.

[0034] like Figure 4 As shown, the front shaft 15 and the rear shaft 16 are both hollow structures; the front shaft 15 has only a square groove at the front end to realize the limiting function, and the rear end is a circular hole to reduce the weight; the interior of the rear shaft 16 is a square groove as a whole, and when the rear shaft 16 is assembled, the square groove and the rear end of the torsion bar 14 play a guiding role; further, the rear end of the rear shaft 16 is provided with a groove and a process threaded hole to facilitate the assembly and disassembly of the rear shaft 16.

[0035] The basic principles, main features and beneficial effects of the present invention are shown and described above; technicians in this industry should understand that the present invention is not limited to the above embodiments, and the above embodiments and descriptions only describe the principles of the present invention. The present invention may have various changes and improvements without departing from the spirit and scope of the present invention, and these changes and improvements all fall within the scope of the present invention to be protected. The scope of protection claimed by the present invention is defined by the attached claims and their equivalents.

Claims

1. A three-way linked locking folding rudder wing structure, characterized in that: It includes a moving rudder, a fixed rudder, an unfolding drive mechanism and a three-way linkage locking mechanism; the moving rudder and the fixed rudder are connected through the unfolding drive mechanism; The moving rudder is provided with a through hole and a pair of coaxial and opposite conical locking pin holes along the chord direction, and a locking groove along the span direction; the through hole cooperates with the lower through hole of the fixed rudder to install the deployment drive mechanism; the front diameter of the through hole is slightly smaller than the rear diameter; The fixed rudder is provided with two through holes, one on the upper side and two operating windows, along the chord direction, and a groove along the span direction; the through hole and the operating window on the upper side are used for installing and removing the sliding block, the locking spring and the locking pin, and the through hole on the lower side has a diameter of the front section slightly smaller than the rear section; The movable rudder and the fixed rudder are both provided with threaded through holes on both sides of the symmetrical rudder surfaces; The deployment drive mechanism comprises a front shaft screw, a rear shaft screw, a cylindrical pin, a torsion bar, a front shaft and a rear shaft; the front shaft screw is installed in a threaded through hole of a dynamic rudder, and the front shaft is fixed to the dynamic rudder through the front shaft screw; the rear shaft screw is installed in a threaded through hole of a fixed rudder, and the rear shaft is fixed to the fixed rudder through the rear shaft screw; the square hole of the front shaft limits the front end of the torsion bar, and the square hole of the rear shaft limits the rear end of the torsion bar; the chordal freedom of the torsion bar is constrained by a cylindrical pin fixed to the torsion bar and the front shaft; The three-way linkage locking mechanism comprises an operating cover plate, a cover plate screw, a locking block, a special-shaped spring, a fixing screw, a sliding block, a locking spring and a locking pin; in a folded state, the locking spring presses the locking pin against the rotating surface of the moving rudder, and the locking spring presses the sliding block against the special-shaped spring; the locking block is constrained inside the fixed rudder by the special-shaped spring; the operating cover plate is mounted on the rudder surface through the cover plate screw; the special-shaped spring is mounted in the groove of the fixed rudder through the fixing screw; the locking block and the locking pin are both mounted in the fixed rudder; When the external constraints are removed, the driving mechanism is deployed to cause the moving rudder to start rotating. When the moving rudder rotates to the point where it cannot resist the locking pin, the locking spring in the fixed rudder pushes the locking pin into the chord-wise locking pin hole of the moving rudder. When the elastic potential energy of the locking spring drops to the same level as that of the special-shaped spring, the special-shaped spring also begins to release its elastic potential energy, pushing the locking block into the span-wise locking groove of the moving rudder, thereby achieving locking in three directions: one span-wise direction and two chord-wise directions.

2. A three-way linkage locking folding rudder wing structure according to claim 1, characterized in that: A structure composed of a curved surface and an inclined surface is provided at the middle position of the locking block.

3. A three-way linkage locking folding rudder wing structure according to claim 1, characterized in that: When the special-shaped spring is stressed, elastic deformation will occur in both the spanwise and chordwise directions. When the folding rudder wing is unfolded, the elastic recovery of the special-shaped spring in the spanwise direction pushes the locking block into the spanwise locking groove of the dynamic rudder.

4. A three-way linkage locking folding rudder wing structure according to claim 1, characterized in that: The deployment drive mechanism comprises two rotating shafts, a front rotating shaft and a rear rotating shaft. During the rotation of the dynamic rudder, the front rotating shaft rotates together with the dynamic rudder, and the rear rotating shaft remains stationary together with the fixed rudder; the rear section of the front rotating shaft serves as the rotating shaft of the fixed rudder, and the rear section of the rear rotating shaft serves as the rotating shaft of the dynamic rudder.

Images