Rocket head cover connecting structure

Abstract

The invention relates to the technical field of rocket head cover separation, in particular to a rocket head cover connecting structure which comprises two sets of mounting plates and further comprises a recoil detonation structure connected with the mounting plates, the recoil detonation structure comprises a shell, the shell is connected with two sets of recoil shells, gunpowder layers are arranged in the recoil shells and the shell, the gunpowder layers are connected with fire caps, and the fire caps are connected with the mounting plates. The shell is connected with a detonating mechanism and an impact assembly; the double-control separation structure is connected with the impact assembly, the double-control separation structure comprises an electric control hooking assembly, and an inertia percussion assembly is installed on the electric control hooking assembly. Through the mode that the double-control separation structure and the recoil detonation structure are matched with each other, the half cover separation operation of the rocket head cover is jointly controlled in the two modes of electronic control and inertia control, and during separation, due to reverse thrust of gunpowder gas, the half covers of the rocket head cover can be conveniently and rapidly separated from each other after being separated from a rocket body, and the separation efficiency is improved. The stability and safety when the rocket head cover is separated from the rocket body are improved.

Description

Technical Field

[0001] This invention relates to the field of rocket nose cone separation technology, specifically a rocket nose cone connection structure. Background Technology

[0002] In order to separate the rocket's nose cone from the main body, it is generally composed of two sets of half-containers connected by explosive bolts. Then, the assembled rocket nose cone is installed onto the main body using explosive bolts. When the main body of the rocket reaches an altitude where the atmosphere is relatively thin, the atmospheric drag it experiences is minimal, and the payload no longer needs the protection of the rocket nose cone. In order to save fuel, improve the mass characteristics of the spacecraft, and enhance flight performance, the rocket nose cone needs to be jettisoned to reduce the structural weight.

[0003] When the rocket helmet, which consists of two halves, is separated using traditional methods, it is only detonated by explosive bolts embedded in the halves and relies on an electronic system for activation. This is very simplistic. If the electronic system fails, the rocket helmet will not be able to detach, making the separation control unstable. Furthermore, when the rocket helmet separates into two halves, it is impossible to accelerate the two halves away from each other quickly, increasing the risk of the halves detaching from the rocket body colliding with the rocket body, which is unsafe. Summary of the Invention

[0004] The purpose of this invention is to provide a rocket helmet connection structure to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A rocket helmet connection structure includes two sets of mounting plates, each set of mounting plates having multiple sets of mounting holes, and further includes:

[0007] A recoil detonation structure connected to a mounting plate, the recoil detonation structure including a housing fixedly connected to the mounting plate, two sets of recoil shells fixedly connected to the housing, a sealing membrane fixedly installed at the open end of the recoil shell, a gunpowder layer provided inside both the recoil shell and the housing, a fire cap installed inside the housing connected to the gunpowder layer, a detonating mechanism connected to the housing, and an impact component slidably connected to the housing;

[0008] A dual-control separation structure is fixedly connected to the impact assembly. The dual-control separation structure includes two sets of electrically controlled hook assemblies that are respectively connected to two sets of impact assemblies. The two sets of electrically controlled hook assemblies, which are respectively installed on the two sets of impact assemblies, are movably connected to each other. An inertial firing assembly is installed on the electrically controlled hook assemblies. The inertial firing assembly is used to trigger the impact operation of the electrically controlled hook assemblies.

[0009] As a further improvement of the present invention: the impact assembly includes a first spring fixedly installed inside the housing, the first spring being fixedly connected to a frame that is slidably connected to the housing, the frame being fixedly connected to an impact pin, and the frame being fixedly connected to an electrically controlled hook assembly.

[0010] As a further improvement of the present invention: a second spring is fixedly installed inside the housing, and a one-way limiting block is fixedly connected to the second spring and slidably installed inside the housing. A protruding block is fixedly connected to the frame, and the protruding block and the one-way limiting block are slidably engaged. The protruding block is slidably installed inside the housing.

[0011] As a further improvement of the present invention: the detonating mechanism includes a threaded cover that is threadedly connected to the housing, and a detonating cord is fixedly connected to the threaded cover. One end of the detonating cord is disposed inside the gunpowder layer, and the other end of the detonating cord is disposed outside the housing.

[0012] As a further improvement of the present invention: the electrically controlled hook assembly includes a snap-fit ​​frame fixedly connected to the frame body, the snap-fit ​​frame being fixedly connected to a rotation limiting shell, the rotation limiting shell being fixedly connected to a compression coupling, wherein the compression coupling of one set of electrically controlled hook assemblies is movably connected to the snap-fit ​​frame of another set of electrically controlled hook assemblies, the rotation limiting shell having two sets of guide rail grooves, the guide rail grooves being slidably connected to a rotating frame, the two sets of rotating frames being fixedly connected to a set of semi-circular plates, wherein the semi-circular plates of one set of electrically controlled hook assemblies are movably connected to the rotation limiting shell of another set of electrically controlled hook assemblies, the semi-circular plates being fixedly connected to a support plate, the support plate being fixedly connected to a support rod, the support plate being fixedly connected to a third spring, the third spring being fixedly connected to the rotation limiting shell, the third spring being ferromagnetic, the rotation limiting shell being fixedly connected to an electromagnet, and the rotation limiting shell being connected to an inertial firing assembly.

[0013] As a further improvement of the present invention: the inertial firing assembly includes a rectangular sleeve fixedly connected to the rotation limiting shell, a fourth spring fixedly installed inside the rectangular sleeve, a bent arm fixedly connected to the fourth spring and slidably connected to the rectangular sleeve, and a triangular impact head fixedly connected to the bent arm.

[0014] As a further improvement of the present invention: the inertial firing assembly further includes a guide groove opened in a rectangular sleeve, a fifth spring is fixedly installed in the guide groove, a ball is fixedly connected to the fifth spring, the ball is slidably installed in the guide groove, and a groove is opened on the curved arm to be movably connected to the ball.

[0015] Compared with the prior art, the beneficial effects of the present invention are:

[0016] In use, the detonating mechanism is connected to the explosive material inside the explosive bolts installed within the rocket's nose cone. The mounting plates are then installed onto the nose cone using conventional bolts passing through mounting holes. Two sets of mounting plates are installed onto the respective halves of the nose cone. As the two halves align, they form a complete nose cone. The movement of the halves causes the mounting plates to approach each other, bringing the two sets of housings mounted on the mounting plates closer together. The housings, via an impact component, move the electrically controlled hooking components. The two sets of electrically controlled hooking components engage and limit each other. Under normal circumstances, the control center triggers the two sets of electrically controlled hooking components via an electrical signal, causing them to disengage. During this disengagement, the impact component pulls the electrically controlled hooking components and ignites the burner cap. The burner cap ignites the propellant layer, causing it to expand. The propellant gases then break through the sealing membrane, pushing back against the propellant. The recoil shell, on the other hand, ignites the detonation mechanism of the propellant layer. The detonation mechanism detonates each set of explosive bolts. Thus, under the recoil of the propellant gases and the detonation of the explosive bolts, the two sets of rocket nose cone halves detach from the rocket body and separate from each other. If the electronically controlled hook assembly cannot be directly started electrically, the rocket is decelerated and the inertial firing assembly is started by inertia. The inertial firing assembly strikes the electronically controlled hook assembly, causing the electronically controlled hook assembly to separate from each other. Then the impact assembly pulls the electronically controlled hook assembly and strikes the burner cap. The burner cap ignites the propellant layer. The propellant layer is ignited and expands. On the one hand, the propellant gases will break through the sealing membrane to recoil the recoil shell. On the other hand, the propellant layer ignites the detonation mechanism. The detonation mechanism detonates each set of explosive bolts. Thus, under the recoil of the propellant gases and the detonation of the explosive bolts, the two sets of rocket nose cone halves detach from the rocket body and separate from each other. This invention utilizes a dual-control separation structure in conjunction with a recoil detonation structure to achieve simultaneous electronic and inertial control of the separation of the rocket's nose cone half-cover. Furthermore, the recoil from the propellant gases during separation facilitates the rapid separation of the rocket nose cone half-covers from the rocket body, thereby enhancing the stability and safety of the rocket nose cone when it detaches from the rocket body. Attached Figure Description

[0017] Figure 1 This is a three-dimensional structural diagram of the present invention.

[0018] Figure 2 This is a three-dimensional structural schematic diagram from another perspective of the present invention.

[0019] Figure 3 This is a three-dimensional structural diagram of the electronically controlled hook assembly and the inertial firing assembly of the present invention.

[0020] Figure 4 This is a three-dimensional structural diagram of the interaction between the electronically controlled hook assembly and the inertial firing assembly of the present invention.

[0021] Figure 5 This is a schematic diagram of the inertial firing assembly of the present invention.

[0022] Figure 6 This is a schematic diagram of the structure in which the shell, recoil shell, sealing membrane, gunpowder layer, percussion cap, first spring, frame, firing pin, and one-way limiting block of the present invention cooperate with each other.

[0023] Figure 7 This is a schematic diagram of the structure of the housing, first spring, frame, striker, second spring, one-way limiting block, and protrusion block of the present invention in cooperation with each other.

[0024] Figure 8 This is a schematic diagram of the internal structure of the two sets of electrically controlled hook-and-loop components of the present invention.

[0025] In the diagram: 1. Mounting plate; 2. Mounting hole; 3. Recoil detonation structure; 4. Shell; 5. Recoil shell; 6. Sealing membrane; 7. Powder layer; 8. Perfumery; 9. Detonating mechanism; 10. Impact assembly; 11. Dual-control separation structure; 12. Electrically controlled hook assembly; 13. Inertial firing assembly; 14. First spring; 15. Frame; 16. Firing pin; 17. Second spring; 18. One-way limiting block; 19. Protruding block; 2 0. Threaded cap; 21. Detonating cord; 22. Clip-on bracket; 23. Rotation limit shell; 24. Extrusion joint; 25. Guide rail groove; 26. Rotary frame; 27. Semicircular plate; 28. Support plate; 29. ​​Support rod; 30. Third spring; 31. Electromagnet; 32. Rectangular sleeve; 33. Fourth spring; 34. Bent arm; 35. Triangular impact head; 36. Guide groove; 37. Fifth spring; 38. Sphere; 39. Groove. Detailed Implementation

[0026] The technical solution of the present invention will be further described in detail below with reference to specific embodiments.

[0027] Example 1, see Figures 1 to 8 As shown, a rocket helmet connection structure includes two sets of mounting plates 1, each set of mounting plates 1 having multiple sets of mounting holes 2, and also includes:

[0028] A recoil detonation structure 3 is connected to the mounting plate 1. Only one recoil detonation structure 3 is installed on a set of mounting plates 1. The recoil detonation structure 3 includes a housing 4 fixedly connected to the mounting plate 1. Two sets of recoil shells 5 are fixedly connected to the housing 4. A sealing membrane 6 is fixedly installed at the open end of the recoil shell 5. A gunpowder layer 7 is provided inside both the recoil shell 5 and the housing 4. The gunpowder layer 7 is connected to a percussion cap 8 installed inside the housing 4. The housing 4 is connected to a detonation mechanism 9. An impact component 10 is slidably connected to the housing 4.

[0029] A dual-control separation structure 11 is fixedly connected to the impact assembly 10. The dual-control separation structure 11 includes two sets of electrically controlled hooking assemblies 12. Each set of electrically controlled hooking assemblies 12 is connected to one set of impact assemblies 10. The two sets of electrically controlled hooking assemblies 12, which are respectively installed on the two sets of impact assemblies 10, are movably connected to each other. An inertial firing assembly 13 is installed on the electrically controlled hooking assembly 12. The inertial firing assembly 13 is used to perform impact triggering operation on the electrically controlled hooking assembly 12.

[0030] In use, the detonating mechanism 9 is connected to the explosive in the explosive bolts installed inside the rocket nose cone. The mounting plate 1 is then installed onto the rocket nose cone using conventional bolts passing through the mounting holes 2. Two sets of mounting plates 1 are respectively installed onto the half-covers of the rocket nose cone. Subsequently, the two sets of rocket nose cone half-covers are joined together to form a complete rocket nose cone. The half-covers of the rocket nose cone cause the mounting plates 1 to approach each other, and the two sets of housings 4, respectively installed on the two sets of mounting plates 1, approach each other. The housings 4, through the impact component 10, drive the electrically controlled hooking component 12 to move. The two sets of electrically controlled hooking components 12 engage and limit each other. Under normal circumstances, the control center activates the two sets of electrically controlled hooking components 12 via an electrical signal trigger, causing the two sets of electrically controlled hooking components 12 to disengage. During the disengagement process, the impact component 10 pulls the electrically controlled hooking component 12 and ignites the burner cap 8. The burner cap 8 ignites the gunpowder layer 7, which expands upon ignition. On one hand, the gunpowder gases will break through the sealing membrane 6, thus pushing back... The recoil shell 5, on the other hand, ignites the propellant layer 7 and the detonation mechanism 9. The detonation mechanism 9 detonates each set of explosive bolts. Thus, under the recoil of the propellant gases and the detonation of the explosive bolts, the half-covers of the two sets of rocket nose cones detach from the rocket body, and the half-covers of the two sets of rocket nose cones separate from each other. If the electronically controlled hook assembly 12 cannot be directly started electrically, the rocket is decelerated, and the inertial firing assembly 13 is started by inertia. The inertial firing assembly 13 strikes the electronically controlled hook assembly 12, thereby triggering the electronically controlled hook assembly 12. 2. After separation, the impact component 10 pulls the electronically controlled hook component 12, and the impact component 10 ignites the burner cap 8. The burner cap 8 ignites the gunpowder layer 7, which expands upon ignition. On one hand, the gunpowder gas breaks through the sealing membrane 6 to push back the recoil shell 5. On the other hand, the gunpowder layer 7 ignites the detonation mechanism 9, which detonates each set of explosive bolts. Thus, under the recoil of the gunpowder gas and the detonation of the explosive bolts, the two sets of rocket nose cone halves separate from the rocket body, and the two sets of rocket nose cone halves separate from each other. This invention uses a dual-control separation structure 11 and a recoil detonation structure 3 in combination to achieve both electronic and inertial control of the rocket nose cone halves separation operation. During separation, the recoil of the gunpowder gas facilitates the rapid separation of the rocket nose cone halves after they detach from the rocket body, thereby improving the stability and safety of the rocket nose cone when it detaches from the rocket body.

[0031] In one embodiment, the impact assembly 10 includes a first spring 14 fixedly installed inside the housing 4. The first spring 14 is fixedly connected to a frame 15 slidably connected to the housing 4. The frame 15 is fixedly connected to a firing pin 16. The frame 15 is fixedly connected to an electrically controlled hook assembly 12. When the two sets of electrically controlled hook assemblies 12 are in a mutually limiting state, the first spring 14 is in a stretched state. As the two sets of electrically controlled hook assemblies 12 disengage, the frame 15 is stretched and moved by the first spring 14, causing the moving frame 15 to drive the firing pin 16 to strike the percussion cap 8, thereby igniting the internal charge of the percussion cap 8.

[0032] In one embodiment, a second spring 17 is fixedly installed inside the housing 4. The second spring 17 is fixedly connected to a one-way limiting block 18 that is slidably installed inside the housing 4. A protruding block 19 is fixedly connected to the frame 15. The protruding block 19 is slidably engaged with the one-way limiting block 18 and is slidably installed inside the housing 4. During the process of the first spring 14 pulling the frame 15, the protruding block 19 moves with the frame 15 and slides relative to the one-way limiting block 18. As the protruding block 19 slides away from the one-way limiting block 18, the second spring 17 pushes out the front end of the one-way limiting block 18. Then, gunpowder gas is generated, and the frame 15 is pushed by the expanding gunpowder gas. At this time, because the one-way limiting block 18 blocks the movement of the protruding block 19, the protruding block 19 is limited, preventing the frame 15 from resetting and causing the electronically controlled hook assembly 12 to reconnect. At the same time, it is beneficial for the gunpowder gas to be ejected directionally from the opening end of the recoil shell 5, increasing the thrust when the half-shells of the rocket nose cone move away from each other, so as to increase the speed when the half-shells of the rocket nose cone move away from each other.

[0033] In one embodiment, the detonating mechanism 9 includes a threaded cap 20 threadedly connected to the housing 4. A detonating cord 21 is fixedly connected to the threaded cap 20. The detonating cord 21 is connected to an explosive device inside an explosive bolt installed within the rocket pylon. One end of the detonating cord 21 is located inside the gunpowder layer 7, and the other end is located outside the housing 4. As the detonating cord 21 is ignited by the exploding gunpowder layer 7, it detonates the explosive device inside the explosive bolt, thus disconnecting the rocket pylon from the rocket body and simultaneously disconnecting the half-covers of the two sets of rocket pylons. The detonating cord 21 achieves a linkage detonation effect.

[0034] In one embodiment, the electrically controlled hook assembly 12 includes a snap-fit ​​bracket 22 fixedly connected to the frame 15. The snap-fit ​​bracket 22 is fixedly connected to a rotation limiting shell 23, and the rotation limiting shell 23 is fixedly connected to a compression connector 24. One set of compression connectors 24 of the electrically controlled hook assembly 12 is movably connected to the snap-fit ​​bracket 22 of another set of electrically controlled hook assemblies 12. The rotation limiting shell 23 has two sets of guide rail grooves 25, and the guide rail grooves 25 are slidably connected to a rotating frame 26. Both sets of rotating frames 26 are fixedly connected to a set of semi-circular plates 27. One set of electrically controlled hook assemblies... The semicircular plate 27 of 12 is movably connected to the rotation limiting shell 23 of another set of electrically controlled hooking components 12. The semicircular plate 27 is fixedly connected to a support plate 28, and the support plate 28 is fixedly connected to a support rod 29. The support plate 28 is fixedly connected to a third spring 30. The third spring 30 is fixedly connected to the rotation limiting shell 23. The third spring 30 is ferromagnetic. The third spring 30 can be grooved with ferromagnetic material, or iron powder can be melted into or mixed into the third spring 30. The rotation limiting shell 23 is fixedly connected to an electromagnet 31. The rotation limiting shell 23 is connected to the inertial firing component 13. During the approach of the two sets of electrically controlled hook assemblies 12, the compression connector 24 of one set of electrically controlled hook assemblies 12 inserts into the snap-fit ​​bracket 22 of the other set of electrically controlled hook assemblies 12. During this process, the compression connector 24 compresses the semi-circular plate 27, causing the semi-circular plate 27 to drive the rotating frame 26 to rotate. The semi-circular plate 27 drives the support plate 28 to rotate, and the support plate 28 compresses the third spring 30. Then, as both sets of compression connectors 24 are inserted into the snap-fit ​​bracket 22, the third spring 30 pushes the support plate 28 to rotate, so that the semi-circular plate 27 rotates back to its original position. At this time, both sets of semi-circular plates 27 are simultaneously positioned in the two sets of rotation limit shells 23 to complete the mutual connection between the two sets of electrically controlled hook assemblies 12. After the electric hook assembly 12 is mutually limited, the electromagnet 31 magnetically attracts the third spring 30, the third spring 30 pulls the support plate 28, or the inertial firing assembly 13 strikes the support rod 29, the support rod 29 drives the support plate 28 to rotate, so that the support plate 28 drives the semi-circular plate 27 to rotate, the semi-circular plate 27 drives the rotating frame 26 to rotate, the rotating frame 26 slides relative to the guide rail groove 25, so that the semi-circular plate 27 is only within a set of rotating limiting shells 23. Then, under the pull of the first spring 14 on the frame 15, the snap-fit ​​frame 22 drives the rotating limiting shells 23 to move, so that the rotating limiting shells 23 move away from each other, so as to realize the mutual separation of the two sets of electric hook assemblies 12.

[0035] In one embodiment, the inertial firing assembly 13 includes a rectangular sleeve 32 fixedly connected to the rotation limiting shell 23. A fourth spring 33 is fixedly installed inside the rectangular sleeve 32. The fourth spring 33 is fixedly connected to a bent arm 34 slidably connected to the rectangular sleeve 32. A triangular impact head 35 is fixedly connected to the bent arm 34. As the rocket body decelerates according to a predetermined program, under the action of inertia, the bent arm 34 moves and compresses the fourth spring 33. The bent arm 34 drives the triangular impact head 35 to squeeze the support rod 29, causing the support rod 29 to drive the support plate 28 to rotate, so that the inertial firing assembly 13 impacts the electrically controlled hook assembly 12, and then the two sets of triggered electrically controlled hook assemblies 12 separate from each other.

[0036] Example 2, based on Example 1, see [link / reference] Figures 1-5 The inertial firing assembly 13 further includes a guide groove 36 formed within a rectangular sleeve 32. A fifth spring 37 is fixedly installed within the guide groove 36, and a ball 38 is fixedly connected to the fifth spring 37. The ball 38 is slidably installed within the guide groove 36, and a groove 39 is formed on the curved arm 34 that is movably connected to the ball 38. Because the fifth spring 37 presses the ball 38 into the groove 39, the curved arm 34 is prevented from moving accidentally due to vibration, thus preventing the inertial firing assembly 13 from being accidentally triggered.

[0037] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention.

Claims

1. A rocket nose cone connection structure, comprising two sets of mounting plates, each set of mounting plates having multiple sets of mounting holes, characterized in that... Also includes: A recoil detonation structure connected to a mounting plate, the recoil detonation structure including a housing fixedly connected to the mounting plate, two sets of recoil shells fixedly connected to the housing, a sealing membrane fixedly installed at the open end of the recoil shell, a gunpowder layer provided inside both the recoil shell and the housing, a fire cap installed inside the housing connected to the gunpowder layer, a detonating mechanism connected to the housing, and an impact component slidably connected to the housing; A dual-control separation structure is fixedly connected to the impact assembly. The dual-control separation structure includes two sets of electrically controlled hook assemblies that are respectively connected to two sets of impact assemblies. The two sets of electrically controlled hook assemblies, which are respectively installed on the two sets of impact assemblies, are movably connected to each other. An inertial firing assembly is installed on the electrically controlled hook assemblies. The inertial firing assembly is used to trigger the impact operation of the electrically controlled hook assemblies.

2. The rocket nose cone connection structure according to claim 1, characterized in that, The impact assembly includes a first spring fixedly installed inside the housing, the first spring being fixedly connected to a frame that is slidably connected to the housing, the frame being fixedly connected to an impact pin, and the frame being fixedly connected to an electrically controlled hook assembly.

3. The rocket nose cone connection structure according to claim 1, characterized in that, A second spring is fixedly installed inside the housing. The second spring is fixedly connected to a one-way limiting block that is slidably installed inside the housing. A protruding block is fixedly connected to the frame. The protruding block and the one-way limiting block are slidably engaged. The protruding block is slidably installed inside the housing.

4. The rocket nose cone connection structure according to claim 1, characterized in that, The detonation mechanism includes a threaded cap that is threadedly connected to the housing. A detonating cord is fixedly connected to the threaded cap. One end of the detonating cord is located inside the gunpowder layer, and the other end of the detonating cord is located outside the housing.

5. The rocket nose cone connection structure according to claim 2, characterized in that, The electrically controlled hook assembly includes a snap-fit ​​frame fixedly connected to the frame body. The snap-fit ​​frame is fixedly connected to a rotation limiting shell, and the rotation limiting shell is fixedly connected to a compression coupling. The compression coupling of one set of electrically controlled hook assemblies is movably connected to the snap-fit ​​frame of another set of electrically controlled hook assemblies. Two sets of guide rail grooves are provided inside the rotation limiting shell. A rotating frame is slidably connected to the guide rail grooves. A set of semi-circular plates is fixedly connected to both sets of rotating frames. The semi-circular plates of one set of electrically controlled hook assemblies are movably connected to the rotation limiting shell of another set of electrically controlled hook assemblies. A support plate is fixedly connected to the semi-circular plate. A support rod is fixedly connected to the support plate. A third spring is fixedly connected to the support plate. The third spring is ferromagnetic. An electromagnet is fixedly connected to the rotation limiting shell. The rotation limiting shell is connected to an inertial firing assembly.

6. The rocket nose cone connection structure according to claim 5, characterized in that, The inertial firing assembly includes a rectangular sleeve fixedly connected to a rotation limiting shell, a fourth spring fixedly installed inside the rectangular sleeve, a curved arm fixedly connected to the fourth spring and slidably connected to the rectangular sleeve, and a triangular impact head fixedly connected to the curved arm.

7. The rocket nose cone connection structure according to claim 6, characterized in that, The inertial firing assembly also includes a guide groove formed within a rectangular sleeve, a fifth spring fixedly installed within the guide groove, a ball fixedly connected to the fifth spring, the ball being slidably installed within the guide groove, and a groove on the curved arm that is movably connected to the ball.

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