Machine support locking mechanism and design method thereof

Abstract

The machine support locking mechanism comprises a projectile clamping body and an elastic body, a protruding arc-shaped wedge face is arranged on the surface of the projectile clamping body, the elastic body is fixedly arranged at one end of the projectile clamping body, the elastic body is used for providing elastic force for the projectile clamping body, and the elastic body is fixed to the surface of a fixing block embedded in a launch canister through a bolt. According to the invention, by using a very simple mechanism form, an adjustable elastic locking force and an automatic unlocking mode, both safety and reliability before launching and rapid response during launching are considered, and the miniaturization, low cost and high performance levels of a launching system are improved.

Description

Technical Field

[0001] The present invention relates to the field of launching systems, and in particular to a support locking mechanism and a design method thereof. Background Art

[0002] In many existing weapon launch systems, a machine-carrier locking mechanism is commonly used to secure and secure the projectile to the launch tube. This mechanism is used to position and restrain the projectile before launch and is widely used in launch platforms such as artillery, rockets, and missiles. Traditional machine-carrier locking mechanisms often utilize rigid locking pins, detents, or flange engagement. These mechanisms are not only structurally mature but also relatively simple to manufacture, making them a mainstream solution in the military industry.

[0003] However, the existing machine-support locking mechanism still cannot guarantee both launch safety and quick unlocking requirements in terms of locking reliability under severe vibration and high overload environments. On the one hand, the rigid structure is prone to loosening, wear, or even unlocking under large-scale movement or impact loads, posing a safety hazard of accidental falling of the projectile. On the other hand, to ensure a secure lock, the size and weight of the locking parts must be increased, resulting in an increase in the weight and volume of the entire machine, which is not conducive to mobile deployment. In addition, the complex mechanical transmission and high-precision coordination requirements increase maintenance costs and failure rates.

[0004] Therefore, we propose a machine support locking mechanism and its design method. With a minimalist structure, adjustable elastic locking force and automated unlocking method, it takes into account both safety and reliability before launch and rapid response during launch, thereby improving the miniaturization, low cost and high performance of the launch system. Summary of the Invention

[0005] The purpose of the present invention is to overcome the shortcomings of the existing technology, adapt to actual needs, and provide a machine-support locking mechanism and a design method thereof to solve the problem that the current existing machine-support locking mechanism is still difficult to balance the launch safety and quick unlocking requirements under severe vibration and high overload environments. On the one hand, the rigid structure is prone to loosening, wear and even unlocking under large-scale movement or impact loads, and there is a safety hazard of accidental falling of the projectile; on the other hand, in order to ensure firm locking, the size and weight of the locking part must be increased, resulting in an increase in the weight and volume of the entire machine, which is not conducive to mobile deployment. In addition, the complex mechanical transmission and high-precision matching requirements increase the maintenance cost and failure rate.

[0006] In order to achieve the purpose of the present invention, the technical solution adopted by the present invention is: to design a machine support locking mechanism, including a locking body and an elastic body, the surface of the locking body is provided with a convex arc wedge surface, and an elastic body is fixed at one end thereof, the elastic body is used to provide elastic force for the locking body, and the elastic body is fixed to the surface of the fixed block embedded in the launch tube by bolts.

[0007] Preferably, the elastic body is a leaf spring.

[0008] Preferably, when the projectile and the rocket engine are pushed from the front end of the launch tube to a predetermined position, the outer casing of the projectile contacts the inclined surface of one side of the projectile jammer, causing the elastic body to deform and generate pushing resistance.

[0009] Preferably, after the projectile is pushed into the predetermined position, the locking tip of the locking body enters the limiting groove of the outer casing of the projectile, and the elastic body resets, so that the locking tip of the locking body is fixed in the limiting groove, thereby locking the projectile and the rocket engine in the launch tube at the same time.

[0010] Preferably, the thrust generated by the rocket engine acts on the rear wedge surface of the projectile and continues to increase. When the thrust is greater than the reset force borne by the elastic body, the projectile body disengages from the limit groove, and the projectile and the rocket engine move forward and fly out of the launch tube.

[0011] A method for designing a machine support locking mechanism is also provided, the design steps comprising: S1. Calculation of the cantilever elastic body's elastic force, flexure force, and loading resistance The calculation formula is:

[0012] Where W is the card elastic force P: is the flexural force; μ: friction coefficient; α: The lead-in angle (the α angle is initially set to 55°, which is the spring force during firing. α' is initially set to 25°, which is the resistance during loading); During the design, the initial setting of the card spring force W is 1.5KN and the friction coefficient μ is 0.15; According to the above formula, the deflection force (that is, the working load in the leaf spring) is calculated as: P≈475N; Moreover, when the elastic body remains unchanged, the P value is a constant; In addition, when loading, the angle α' is 25°, and the resistance W' during loading is calculated according to the above formula: W'≈181N; That is: the resistance during loading is about 181N; S2. Calculation of preset dimensions related to the elastic body According to the cantilever triangular leaf spring working mode, the relevant parameters of the preset elastic body (leaf spring) are: Assume that the working deformation (effective elastic deformation) of the elastic body is X The cantilever length at the installation position is L=80mm, Elastomer thickness h=4mm, The cross-sectional width of the cantilever end (force receiving point) is b=14mm. The material suitable for the sheet elastic body is silicon manganese steel 60Si2Mn; Elastic modulus E = 206GPa = 206000MPa; allowable stress (dynamic load) σ = 412MPa Then: The second moment of area is:

[0013] Then: The working deformation (effective elastic deformation) X of the elastic body is:

[0014] Where: K is the shape coefficient = b1 / b2 = 1.2; According to the calculated data, the deformation of the elastic body under the rated flexural force P is about 6.32mm, but the deformation is too long and does not meet the structural design requirements. The data is further rounded. According to the above formula, the relevant data is rounded to: The cantilever length at the installation position is L=80mm, Elastomer thickness h=4.3mm, Cantilever end (force point) cross-sectional width b = 14mm The working deformation of the elastic body (effective elastic deformation) X≈5.09mm; S3. Calculation of elastic body stress verification Maximum allowable stress check: Bending section coefficient Z:

[0015] Maximum allowable stress σ at point A:

[0016] The safety factor reaches 2; S4. Statics simulation verification The designed elastomer structure was simulated again based on the three-dimensional model, and the thickness of the elastomer was finally optimized to 3.3mm. When subjected to a horizontal force of 1.5kN, the elastomer can produce a deformation greater than 5mm, with a value of 5.224mm. At this time, the maximum stress is less than 700Mpa, which is less than the material's yield strength index of 1176Mpa, meeting the design requirements.

[0017] Compared with the prior art, the present invention has the following beneficial effects: 1. The locking body and elastic body (leaf spring) of the present invention are directly fixed to the fixed block embedded in the launch tube by bolts, which reduces the number of parts and is quick to assemble. Compared with traditional mechanisms with multiple pins and pawls, the overall weight and volume of the locking mechanism are reduced, which is conducive to the miniaturization and mobility of the launch platform. At the same time, due to the mature technology of the leaf spring, the processing cost is low, and the subsequent replacement and maintenance are also very convenient.

[0018] 2. When the projectile of the present invention is propelled to the predetermined position, its outer casing contacts the arcuate wedge surface on the projectile retaining element, driving the elastic element to deform and generate pushing resistance, automatically absorbing vibration and impact energy, and effectively preventing the projectile from loosening during transportation or platform movement. During launch, the thrust generated by the rocket engine acts on the rear wedge surface of the projectile. As the thrust continues to increase and exceeds the restoring force generated by the elastic element, the projectile retaining element automatically disengages from the retaining groove, achieving reliable automatic unlocking and rapid launch without the need for additional unlocking or actuating mechanisms.

[0019] 3. The locking force provided by the arc-shaped wedge surface and the leaf spring of the present invention can be flexibly adjusted by the wedge surface angle and the spring stiffness, which can not only meet the anti-loosening requirements under different vibration intensities, but also match the thrust characteristics of the rocket engine, eliminating the hidden dangers of rigid locking pins being easily worn and locked. At the same time, due to the small number of parts and flexible material selection, it can be quickly customized for launch systems of different calibers and different thrust levels. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall structure of the present invention; Figure 2 It is a front view structural schematic diagram of the present invention; Figure 3 It is a side structural schematic diagram of the present invention; Figure 4 Schematic diagram of the design method flow of the present invention; Figure 5 This is a schematic diagram of the angle of the wedge surface of the bullet-entrapment body of the present invention; Figure 6 It is a schematic diagram of the elastic body mechanical model in the manual of the present invention; Figure 7 is a schematic diagram of stress simulation of the present invention; Figure 8 It is a deformation simulation schematic diagram of the present invention; In the figure: 1. card body; 2. elastic body. DETAILED DESCRIPTION

[0021] The present invention will be further described below with reference to the accompanying drawings and embodiments: Example 1: A machine support locking mechanism and its design method, see Figures 1 to 8, including a projectile-locking body 1 and an elastic body 2. The surface of the projectile-locking body 1 is provided with a convex arc-shaped wedge surface, and an elastic body 2 is fixed at one end thereof. The elastic body 2 is used to provide elastic force for the projectile-locking body 1. The elastic body 2 is fixed to the surface of the fixed block embedded in the launch tube by bolts.

[0022] Specifically, the elastic body 2 is a leaf spring.

[0023] Furthermore, when the projectile and the rocket engine are pushed from the front end of the launch tube to the predetermined position, the outer casing of the projectile contacts the inclined surface of one side of the projectile 1, causing the elastic body 2 to deform and generate pushing resistance. The inclined surface of the outer casing of the projectile contacts the protruding arc-shaped wedge surface on the projectile 1. As the pushing force continues to act, the projectile 1 is controllably deformed around the leaf spring fixed on the fixed block, and the elastic body 2 is compressed and generates an outward reverse force. This reverse force is the pushing resistance, which not only ensures the smoothness of the insertion process, but also absorbs energy and prevents loosening under sudden vibration or impact conditions.

[0024] It is worth noting that after the projectile is pushed into the predetermined position, the locking tip of the locking body 1 enters the limiting groove of the outer casing of the projectile, and the elastic body 2 resets, so that the locking tip of the locking body 1 is fixed in the limiting groove, thereby locking the projectile and the rocket engine in the launch tube at the same time. When the projectile is pushed to the predetermined position, the tip of the locking body 1 slides into the preset limiting groove on the outer casing of the projectile. As the thrust stops increasing, the plate spring resets and pulls the locking body 1, so that the tip is firmly locked in the limiting groove. At this time, the projectile and the rocket engine are locked in the launch tube at the same time, ensuring that they will not accidentally fall off during transportation, turning or any vibration environment before launch.

[0025] It is worth noting that the thrust generated by the rocket engine acts on the rear wedge surface of the projectile and continues to increase. When the thrust is greater than the reset force borne by the elastic body 2, the projectile body 1 disengages from the limit groove, and the projectile and the rocket engine move forward and fly out of the launch tube. After the launch command is issued, the rocket engine starts to ignite and generate forward thrust. This thrust acts on the projectile body 1 through the rear wedge surface of the projectile. As the thrust continues to increase, when it exceeds the reset force that the leaf spring can provide, the projectile body 1 undergoes elastic deformation again, and the tip disengages from the limit groove. The projectile and the rocket engine immediately disengage from the locking mechanism and quickly fly out of the launch tube without any additional mechanical unlocking action, completing the launch.

[0026] A design method for a machine support locking mechanism is also provided, the design steps comprising: S1. Calculation of the cantilever elastic body's elastic force, flexure force, and loading resistance The calculation formula is:

[0027] Where W is the card elastic force P: is the flexural force; μ: friction coefficient; α: The lead-in angle (the α angle is initially set to 55°, which is the spring force during firing. α' is initially set to 25°, which is the resistance during loading); During the design, the initial setting of the card spring force W is 1.5KN and the friction coefficient μ is 0.15; According to the above formula, the deflection force (that is, the working load in the leaf spring) is calculated as: P≈475N; Moreover, when the elastic body 2 remains unchanged, the P value is a constant; In addition, when loading, the angle α' is 25°, and the resistance W' during loading is calculated according to the above formula: W'≈181N; That is: the resistance during loading is about 181N; S2, calculation of preset dimensions related to elastic body 2 According to the cantilever triangular leaf spring working mode, the relevant parameters of elastic body 2 (leaf spring) are preset as follows: Assume that the working deformation (effective elastic deformation) of elastic body 2 is X The cantilever length at the installation position is L=80mm, The thickness of elastic body 2 is h=4mm, The cross-sectional width of the cantilever end (force receiving point) is b=14mm. The material suitable for the sheet elastic body 2 is silicon manganese steel 60Si2Mn; Elastic modulus E = 206GPa = 206000MPa; allowable stress (dynamic load) σ = 412MPa Then: The second moment of area is:

[0028] Then: The working deformation (effective elastic deformation) X of the elastic body 2 is:

[0029] Where: K is the shape coefficient = b1 / b2 = 1.2; According to the calculated data, the deformation of elastic body 2 under the rated flexural force P is about 6.32mm, but the deformation is too long and does not meet the structural design requirements. The data is further rounded. According to the above formula, the relevant data is rounded to: The cantilever length at the installation position is L=80mm, The thickness of elastic body 2 is h=4.3mm, Cantilever end (force point) cross-sectional width b = 14mm Working deformation of elastic body 2 (effective elastic deformation) X≈5.09mm; S3. Calculation of stress check of elastic body 2 Maximum allowable stress check: Bending section coefficient Z:

[0030] Maximum allowable stress σ at point A:

[0031] The safety factor reaches 2; S4. Statics simulation verification The designed elastomer 2 structure was simulated again based on the three-dimensional model. Finally, when the thickness of elastomer 2 was optimized to 3.3mm, when subjected to a horizontal force of 1.5kN, elastomer 2 could produce a deformation greater than 5mm, with a value of 5.224mm. At this time, the maximum stress was less than 700Mpa, which is less than the material's yield strength index of 1176Mpa, meeting the design requirements.

[0032] During use, the inclined surface of the outer shell of the projectile contacts the convex arc wedge surface on the projectile body 1. As the pushing force continues to act, the projectile body 1 deforms controllably around the leaf spring fixed on the fixed block, and the elastic body 2 is compressed and generates an outward reverse force. This reverse force is the pushing resistance, which not only ensures the smoothness of the insertion process, but also absorbs energy and prevents loosening under sudden vibration or impact conditions. When the projectile is pushed to the predetermined position, the tip of the projectile body 1 slides into the preset limit groove on the outer shell of the projectile. As the thrust stops increasing, the leaf spring resets and pulls the projectile body 1, so that the tip is firmly locked. The projectile and the rocket engine are locked in the launch tube at the same time to ensure that they will not fall off accidentally during transportation, turning or any vibration environment before launch. After the launch command is issued, the rocket engine starts to ignite and generates forward thrust. This thrust acts on the projectile body 1 through the rear wedge surface of the projectile. As the thrust continues to increase, when it exceeds the reset force provided by the leaf spring, the projectile body 1 undergoes elastic deformation again, and the tip disengages from the limit groove. The projectile and the rocket engine immediately disengage from the locking mechanism and quickly fly out of the launch tube without any additional mechanical unlocking action, completing the launch.

[0033] In addition, the components designed in the present invention are all universal standard parts or components known to those skilled in the art. Their structures and principles can be known to those skilled in the art through technical manuals or conventional experimental methods. They can be fully implemented by those skilled in the art. Needless to say, the content protected by the present invention does not involve improvements to internal structures and methods.

Claims

1. A machine support locking mechanism, comprising a locking body (1) and an elastic body (2), characterized in that: The surface of the projectile-locking body (1) is provided with a convex arc-shaped wedge surface, and an elastic body (2) is fixedly provided at one end thereof. The elastic body (2) is used to provide elastic force for the projectile-locking body (1). The elastic body (2) is fixed to the surface of a fixed block embedded in the launch tube by bolts.

2. The machine support locking mechanism according to claim 1, wherein: The elastic body (2) is a leaf spring.

3. The machine support locking mechanism according to claim 1, wherein: When the projectile and the rocket engine are pushed from the front end of the launch tube to a predetermined position, the projectile outer casing contacts the inclined surface of one side of the projectile jammer (1), causing the elastic body (2) to deform and generate pushing resistance.

4. The machine support locking mechanism according to claim 3, wherein: After the projectile is pushed into a predetermined position, the projectile tip of the projectile-locking body (1) enters the limiting groove of the projectile outer casing, and the elastic body (2) is reset, so that the projectile tip of the projectile-locking body (1) is fixed in the limiting groove, thereby locking the projectile and the rocket engine in the launch tube at the same time.

5. The machine support locking mechanism according to claim 4, characterized in that: The thrust generated by the rocket engine acts on the rear face of the projectile and continues to increase. When the thrust is greater than the reset force carried by the elastic body (2), the projectile body (1) is released from the limiting groove, and the projectile and the rocket engine move forward and fly out of the launch tube.

6. A method for designing a machine support locking mechanism according to any one of claims 1 to 5, characterized in that: The design steps include: S1. Calculation of the cantilever elastic body's elastic force, flexure force, and loading resistance The calculation formula is: Where W is the card elastic force P: is the flexural force; μ: friction coefficient; α: The lead-in angle (the α angle is initially set to 55°, which is the spring force during firing. α' is initially set to 25°, which is the resistance during loading); During the design, the initial setting of the card spring force W is 1.5KN and the friction coefficient μ is 0.15; According to the above formula, the deflection force (that is, the working load in the leaf spring) is calculated as: P≈475N; Moreover, when the elastic body (2) remains unchanged, the value of P is a constant; In addition, when loading, the angle α' is 25°, and the resistance W' during loading is calculated according to the above formula: W'≈181N; That is: the resistance during loading is about 181N; S2. Calculation of relevant preset dimensions of elastic body (2) According to the cantilever triangular leaf spring working mode, the relevant parameters of the preset elastic body (2) (leaf spring) are: Assume that the working deformation (effective elastic deformation) of the elastic body (2) is X The cantilever length at the installation position is L=80mm, The thickness of the elastic body (2) is h = 4 mm, The cross-sectional width of the cantilever end (force receiving point) is b=14mm. The material suitable for the sheet elastic body (2) is silicon manganese steel 60Si2Mn; Elastic modulus E = 206GPa = 206000MPa; allowable stress (dynamic load) σ = 412MPa Then: The second moment of area is: Then: The working deformation (effective elastic deformation) X of the elastic body (2) is: Where: K is the shape coefficient = b1 / b2 = 1.2; According to the calculated data, the deformation of the elastic body (2) under the rated flexural force P is about 6.32 mm, but the deformation is too long and does not meet the structural design requirements. The data is further rounded. According to the above formula, the relevant data is rounded to: The cantilever length at the installation position is L=80mm, The thickness of the elastic body (2) is h = 4.3 mm, Cantilever end (force point) cross-sectional width b = 14mm The working deformation (effective elastic deformation) of the elastic body (2) is X≈5.09 mm; S3. Calculation of stress check of elastic body (2) Maximum allowable stress check: Bending section coefficient Z: Maximum allowable stress σ at point A: The safety factor reaches 2; S4. Statics simulation verification The designed elastic body (2) structure is simulated again based on the three-dimensional model. When the thickness of the elastic body (2) is finally optimized to 3.3 mm, the elastic body (2) can produce a deformation greater than 5 mm when subjected to a horizontal force of 1.5 kN, and the value is 5.224 mm. At this time, the maximum stress is less than 700 MPa, which is less than the yield strength index of the material of 1176 MPa, meeting the design and use requirements.

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