Rocket power anchor

Abstract

The invention provides a rocket power anchor. The rocket power anchor comprises a bullet of a spiral structure. The anchoring structure is detachably connected with the warhead, and the anchoring structure can stretch; the second-stage engine is detachably connected with the anchoring structure, a second-stage delay igniter capable of driving the anchoring structure to stretch is arranged at the joint of the second-stage engine and the anchoring structure, and the second-stage engine is filled with a second-stage propelling grain; the first-stage engine is detachably connected with the second-stage engine, a middle partition bin is arranged at the joint of the second-stage engine and the first-stage engine, a first-stage delay igniter is arranged on the middle partition bin, and the first-stage engine is filled with a first-stage propelling grain; the exhaust nozzle can be obliquely arranged at a certain angle, so that the rocket power anchor can rotate during movement; the lifting ring is rotationally connected to the first-stage engine; the total mass of the first-stage propelling grain is smaller than that of the second-stage propelling grain; and a pressure-bearing diaphragm is arranged on the middle partition bin.

Description

Technical Field

[0001] This application belongs to the technical fields of river and lake breach blocking technology, large river closure construction, etc., and specifically relates to a rocket-powered anchor. Background Art

[0002] After a breach occurs in a river embankment, the flow velocity at the breach mouth is usually relatively large. Due to the urgency of time, the materials for blocking the breach are generally locally sourced. These thrown materials are small in volume and light in weight, and are easily washed away by the water flow after being thrown into the breach, making it difficult to quickly take root stably at the breach to complete the task of blocking the breach. Similarly, during the construction of large river closures in large-scale water conservancy projects, problems such as large flow velocities at the closure mouth and difficulty for the thrown materials to quickly take root also occur. In the face of breach problems, common methods such as horizontal closure method, vertical closure method, and combined closure method are often used for closure construction. Although the existing closure construction technologies are relatively mature, they all have disadvantages such as complex construction techniques, long construction time, high cost, and consumption of a large amount of labor. Sometimes, it even delays the construction period and causes serious losses to the operation of later hydropower generation and other aspects. Therefore, it is necessary to develop a new and efficient, convenient, safe and applicable tool for breach plugging and mouth closure to solve the above deficiencies.

[0003] The invention patent with patent number 2017107262155 and publication number CN107587507B discloses a rocket earth anchor, which includes a warhead, a secondary trigger expansion anchor mechanism part, a rocket engine part, and an anti-twist gyro body. The tail of the warhead is fixedly connected to the head of the secondary trigger expansion anchor mechanism part, the tail of the secondary trigger expansion anchor mechanism part is fixedly connected to the head of the rocket engine part, the tail of the rocket engine part is fixedly connected to the head of the anti-twist gyro body, and the tail of the anti-twist gyro body is connected to the underground cable. Double helix cutting wings are locally arranged on the outer surfaces of the warhead shell, the expansion anchor shell, and the rocket engine shell. The technical advantage of the strong rocket thrust of this patent can make the anchor body drill deep into the ground, quickly form a rooting point in the soil body, and then connect the tail cable to the onshore fixed pile. Hanging thrown materials on the cable for sliding throwing can quickly make the thrown materials take root stably at the mouth and not be washed away by the water flow.

[0004] When a rocket anchor works, it often needs to penetrate through multiple media, for example, it needs to move in the air and water respectively, and finally penetrate into the soil. According to actual test verification, the greater the speed of the rocket anchor in the air and water, the greater the resistance, and a large amount of energy will be consumed before penetrating into the soil. The rocket earth anchor of the above patent uses single-stage thrust and cannot reasonably distribute the energy before and after penetrating into the soil, easily leading to excessive energy consumption due to too high speed and too large resistance of the rocket anchor in the air and water, thus making the rocket anchor unable to penetrate into the soil with the maximum thrust and speed, reducing the penetration depth of the rocket anchor and lowering the anchoring force of the rocket anchor. Summary of the Invention

[0005] The purpose of this application is to provide a rocket anchor solution with dual-pulse power, which can achieve two-stage triggering and hierarchical energy release, so as to make full use of energy, increase the penetration depth, and improve the anchoring force.

[0006] This application adopts the following technical solutions:

[0007] A rocket-powered anchor, comprising,

[0008] A warhead, the warhead being of a spiral structure;

[0009] An anchoring structure, the anchoring structure being detachably connected to the warhead, the anchoring structure comprising a number of deployable anchor claws, and the angle between the deployed anchor claws and the main body of the anchoring structure being 35°-75°;

[0010] A secondary engine, the secondary engine being detachably connected to the anchoring structure, a secondary delay igniter capable of driving the anchoring structure to deploy being provided at the connection between the secondary engine and the anchoring structure, and a secondary propellant charge being filled in the secondary engine;

[0011] A primary engine, the primary engine being detachably connected to the secondary engine, an intermediate compartment being provided at the connection between the secondary engine and the primary engine, a primary delay igniter being provided on the intermediate compartment, and a primary propellant charge being filled in the primary engine;

[0012] Tail nozzles, a number of the tail nozzles being connected to the primary engine, and the tail nozzles being able to be inclined at a certain angle so that the rocket-powered anchor can rotate during movement; and

[0013] A lifting ring, the lifting ring being rotatably connected to the primary engine;

[0014] Wherein, the total mass of the primary propellant charge is less than the total mass of the secondary propellant charge; a pressure-bearing diaphragm is provided on the intermediate compartment, the pressure-bearing diaphragm prevents the gas in the primary engine from entering the secondary engine when the primary engine is working, and when the secondary engine is working, the gas in the secondary engine can break through the pressure-bearing diaphragm and enter the primary engine and be ejected by the tail nozzles.

[0015] Further, the primary propellant charge and the secondary propellant charge are in the form of simultaneous internal and external combustion.

[0016] Further, the anchoring structure comprises a main shaft, a chute is opened on the side wall of the main shaft, a thrust sleeve is slidably arranged outside the main shaft, a thrust piston connected to the thrust sleeve is slidably arranged inside the main shaft, a number of anchor claws are rotatably connected to the side wall of the main shaft, and the anchor claws are connected to the thrust sleeve;

[0017] When the secondary delayed ignition device is in operation, it can drive the thrust piston to move in the main shaft, thereby driving the fluke to extend.

[0018] Furthermore, the thrust piston is provided with a first pin hole, the main shaft is provided with a second pin hole, and the first pin hole and the second pin hole are penetrated with breakable pins.

[0019] Furthermore, a plurality of support rods are arranged in the middle compartment, and the pressure-bearing diaphragm is mounted on the support rods.

[0020] Furthermore, a surface of the pressure-bearing diaphragm close to the support rod is a smooth surface, and a surface away from the support rod is provided with a plurality of grooves.

[0021] Furthermore, the tail nozzle has an inclination angle of 10°-30°.

[0022] Beneficial effects of this application:

[0023] The present application adopts a two-stage engine structure, in which the thrust of the first-stage engine is smaller than that of the second-stage engine, which can realize the two-stage triggering and graded energy release of the engine. When the rocket-powered anchor of the present application works in the air and water, it can continue to cruise in a small thrust form, reduce the movement speed and reduce the movement resistance. When penetration is required close to the ground, it can complete the penetration into the ground in a large thrust form. The present application not only makes full use of energy, but also can penetrate into the ground with the maximum thrust and speed, increase the penetration depth, and thus improve the anchoring force of the rocket anchor. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the structure of the present application when the anchoring structure is not extended;

[0025] Figure 2 It is a schematic diagram of the structure of this application when the anchoring structure is extended;

[0026] Figure 3 for Figure 2 Sectional view in the middle AA direction;

[0027] Figure 4 This is a schematic diagram of the warhead and anchoring structure in this application;

[0028] Figure 5 This is a schematic diagram of the middle compartment structure in this application;

[0029] Figure 6 This is a schematic diagram of the front connecting member structure in this application;

[0030] Figure 7 This is a schematic diagram of the rear connecting member structure in this application;

[0031] In the picture: 100 warheads;

[0032] 200 Anchor structure, 201 main shaft, 2011 chute, 2012 second pin hole, 202 thrust piston, 2021 first pin hole, 203 thrust sleeve, 204 anchor claw, 205 connecting rod, 206 anchor housing, 2061 slot;

[0033] 300 Front connector, 301 secondary delay igniter;

[0034] 400 Secondary engine, 401 secondary propellant charge;

[0035] 500 Intermediate compartment, 501 primary delay igniter, 502 pressure-bearing diaphragm, 5021 groove, 503 support rod, 504 external pressure ring, 505 internal pressure ring;

[0036] 600 Primary engine, 601 primary propellant charge;

[0037] 700 Rear connector, 701 nozzle, 702 sealing plug, 703 lifting ring. Detailed implementation mode

[0038] To make the above features and advantages of the present application more obvious and understandable, the following describes the detailed implementation mode of the present application in conjunction with the accompanying drawings. Many specific details are set forth in the following description in order to fully understand the present application. However, the present application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without departing from the connotation of the present application. Therefore, the present application is not limited by the specific embodiments disclosed below.

[0039] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present application.

[0040] In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first", "second" may explicitly or implicitly include at least one of such features. In the description of the present application, the meaning of "plurality", "several" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0041] In this application, unless otherwise clearly defined and limited, terms such as "installation", "connection", "linkage", "fixation", etc. shall be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0042] Referring to Figure 1-7 , this application provides a rocket-powered anchor, including

[0043] a warhead 100, and the warhead 100 is of a spiral structure;

[0044] an anchoring structure 200, the anchoring structure 200 is detachably connected to the warhead, the anchoring structure 200 includes a plurality of deployable anchor claws 204, and the included angle between the anchor claws 204 after deployment and the main body 200 of the anchoring structure is 35° - 75°;

[0045] a secondary engine 400, the secondary engine 400 is detachably connected to the anchoring structure 200, a secondary delay igniter 301 capable of driving the anchoring structure 200 to deploy is arranged at the connection between the secondary engine 400 and the anchoring structure 200, and a secondary propellant charge 401 is filled in the secondary engine 400;

[0046] a primary engine 600, the primary engine 600 is detachably connected to the secondary engine 400, an intermediate compartment 500 is arranged at the connection between the secondary engine 400 and the primary engine 600, a primary delay igniter 501 is arranged on the intermediate compartment 500, and a primary propellant charge 601 is filled in the primary engine 600;

[0047] a tail nozzle 701, a plurality of the tail nozzles 701 are connected to the primary engine 600, and the tail nozzle 701 can adjust the deflection direction so that the rocket-powered anchor can generate rotation during movement; and

[0048] a lifting ring 703, the lifting ring 703 is rotatably connected to the primary engine 600; specifically, the lifting ring 703 can be connected to the primary engine 600 by using existing technical means; through the rotational setting, after the lifting ring 703 is connected to an external cable, it can ensure that the cable is not wound when the rocket-powered anchor rotates.

[0049] Among them, the total mass of the primary propulsion grain 601 is less than the total mass of the secondary propulsion grain 401; a pressure-bearing diaphragm 502 is provided on the intermediate compartment 500, and the pressure-bearing diaphragm 502 prevents the gas in the primary engine 600 from entering the secondary engine 400 when the primary engine 600 is working. When the secondary engine 400 is working, the gas in the secondary engine 400 can break through the pressure-bearing diaphragm 502 and enter the primary engine 600 and be ejected by the tail nozzle 701.

[0050] Specifically, the rocket-powered anchor of the present application is placed in the air in a certain manner, and the console gives an ignition signal to the igniter of the primary engine 600 of the rocket-powered anchor. High-temperature gas is generated in the igniter, which ignites the primary propulsion grain 601 in the primary engine 600. When the gas in the primary engine 600 reaches a certain pressure, it is ejected by the tail nozzle 701, and the primary engine 600 starts to work normally, generating thrust to push the rocket-powered anchor to move until the primary engine 600 finishes working. When the primary engine 600 is working, the primary delay igniter 501 between the primary engine 600 and the secondary engine 400 is ignited. When the primary engine 600 finishes working, the primary delay igniter 501 ignites the secondary propulsion grain 401 in the secondary engine 400, and the secondary engine 400 starts to work. The gas in the secondary engine 400 breaks through the pressure-bearing diaphragm 502 provided in the intermediate compartment 500, and the gas flows out through the combustion chamber and nozzle of the primary engine 600 until the secondary engine 400 finishes working. When the secondary engine 400 is working, the secondary delay igniter 301 of the anchoring mechanism is ignited. After the secondary engine 400 finishes working, the ignited secondary delay igniter 301 generates high-pressure gas to drive the anchoring mechanism to extend. When the rocket-powered anchor receives a pulling force and withdraws towards the ground, the extended anchoring mechanism can increase the soil-facing area and improve the anchoring force.

[0051] Among them, the pressure-bearing diaphragm 502 provided in the intermediate compartment 500 is required to be able to bear positive pressure and open in the reverse direction, that is, it can bear positive pressure during the working time of the primary engine 600 to ensure that the gas working in the primary engine 600 will not flow into the secondary engine 400. When the secondary engine 400 is working, the generated gas acts on the pressure-bearing diaphragm 502 in the reverse direction and can break through the pressure-bearing diaphragm 502, and the gas then flows out through the combustion chamber and nozzle of the primary engine 600. By setting the pressure-bearing diaphragm 502, it can be ensured that the primary engine 600 and the secondary engine 400 work at different times, avoiding the ignition of the secondary engine 400 when the primary engine 600 is working.

[0052] In this application, the included angle between the anchor claw 204 and the main body 200 of the anchoring structure after the anchor claw 204 extends is 35°-75°. It can be understood that the included angle between the anchor claw 204 and the main body 200 of the anchor should be an acute angle and should be appropriate. An included angle that is too large or too small can easily result in too small a contact area between the anchor claw 204 and the soil, thus resulting in insufficient anchoring force.

[0053] As a preferred embodiment, both the primary propulsion grain 601 and the secondary propulsion grain 401 can adopt high burning rate modified black carbon (GHT) propellants. The basic properties of the propellants are shown in Table 1:

[0054] Table 1 Basic performance parameters of GHT propellant

[0055]

[0056] As a preferred embodiment, the charging parameters of the primary engine 600 and the secondary engine 400 are shown in Table 2, and among them, the interior ballistic parameters of the primary engine 600 and the secondary engine 400 are shown in Table 3:

[0057] Table 2 Charging parameters

[0058]

[0059] Table 3 Main result parameters of the calculated interior ballistics of the two-stage engine

[0060]

[0061]

[0062] This application adopts a two-stage engine structure, in which the thrust of the primary engine 600 is less than that of the secondary engine 400, and it can realize two-stage triggering and staged energy release of the engine. When the rocket-powered anchor of this application works in air and water, it can have a small thrust form for endurance, reduce the movement speed and the movement resistance. When it needs to penetrate the ground, it can complete the entry into the soil in a large thrust form. This application not only makes full use of the energy, but also can penetrate the soil with the maximum thrust and speed, improve the penetration depth, and thus improve the anchoring force of the rocket-powered anchor.

[0063] It can be understood that the primary propulsion grain 601 and the secondary propulsion grain 401 burn simultaneously inside and outside.

[0064] Refer to Figure 3 and 4, It can be understood that the anchoring structure 200 includes an anchoring housing 206, which is detachably connected to the warhead 100, specifically by bolt connection. The anchoring housing 206 is provided with a number of slots 2061 that enable the anchor claws 204 to extend. The anchoring structure 200 includes a main shaft 201. A chute 2011 is formed on the side wall of the main shaft 201, and at least one chute 2011 is provided. A thrust sleeve 203 is slidably arranged outside the main shaft 201, and a thrust piston 202 connected to the thrust sleeve 203 is slidably arranged inside the main shaft 201. A number of anchor claws 204 are rotatably connected to the side wall of the main shaft 201, and the anchor claws 204 are connected to the thrust sleeve 203. Specifically, a connecting rod 205 is rotatably connected between the anchor claws 204 and the thrust sleeve 203;

[0065] When the secondary delay igniter 301 works, it can drive the thrust piston 202 to move inside the main shaft 201, thereby driving the anchor claws 204 to extend.

[0066] Specifically, the secondary delay igniter 301 is arranged at the end of the main shaft 201. When the secondary delay igniter 301 is ignited, high-pressure gas will be generated. The high-pressure gas can impact the thrust piston 202 to move inside the main shaft 201, thereby driving the thrust sleeve 203 to move outside the main shaft 201. The thrust sleeve 203 pushes the anchor claws 204 to extend from the slots 2061 of the anchoring housing 206 and into the soil through the connecting rod 205. When the rocket-powered anchor is subjected to an external tensile force, the anchor claws 204 can further extend and insert into the soil, thereby increasing the anchoring force.

[0067] Refer to Figure 3 and 4 , It can be understood that a first pin hole 2021 is provided on the thrust piston 202, and a second pin hole 2012 is provided on the main shaft 201. A breakable pin is inserted through the first pin hole 2021 and the second pin hole 2012.

[0068] Specifically, by setting the foldable pin, the anchoring structure 200 is in a locked state initially, preventing the anchor claws 204 from extending due to factors such as vibration. When the high-pressure gas generated by the ignition of the secondary delay igniter 301 has a large enough thrust to break the pin, the anchoring structure 200 is unlocked, enabling the anchor claws 204 to extend.

[0069] Refer to Figure 5 , It can be understood that a number of support rods 503 are arranged inside the intermediate compartment 500, and the pressure-bearing diaphragm 502 is installed on the support rods 503.

[0070] Specifically, several of the support rods 503 are arranged inside the intermediate compartment 500 to support the pressure-bearing diaphragm 502, preventing the gas in the primary engine 600 from breaking through the pressure-bearing diaphragm 502. At the same time, sufficient space is left between the support rods 503 to allow the gas in the secondary engine 400 to enter the primary engine 600 through the intermediate compartment 500. The pressure-bearing diaphragm 502 has an annular structure and is installed on the support rods 503 through an outer pressure ring 504 and an inner pressure ring 505, with one side of the support member facing the direction of the secondary engine 400. The primary delay igniter 501 is arranged in the middle of the support rod 503.

[0071] Referring to Figure 5 , it can be understood that the side of the pressure-bearing diaphragm 502 close to the support rod 503 is a smooth surface, and several grooves 5021 are arranged on the side facing away from the support rod 503.

[0072] Specifically, by arranging grooves 5021 on one side of the pressure-bearing diaphragm 502, the pressure-bearing diaphragm 502 can be smoothly broken through when it is impacted by the gas generated by the secondary engine 400.

[0073] Referring to Figure 7 , it can be understood that the inclined direction of the tail nozzle 701 is 10° - 30°.

[0074] Specifically, several tail nozzles 701 are distributed in a circular structure on the rear connecting member 700. Several tail nozzles 701 are inclined at a certain angle along the same direction around the circumference, so that a rotational moment rotating along the axial direction is decomposed from the thrust of the tail nozzle 701. A sealing plug 702 is arranged in the tail nozzle 701, and when the gas pressure in the primary engine 600 reaches a certain level, it can break through the sealing plug 702 and be ejected from the tail nozzle 701.

[0075] It should be noted that the igniter of the primary engine 600 is arranged inside the primary engine 600, and its lead wire can extend out through the sealing plug 702 on one of the tail nozzles 701. A through hole can be arranged on this sealing plug 702 to allow the lead wire to extend out.

[0076] It can be understood that a detachable connection method, such as a threaded connection, can be adopted between the tail nozzle 701 and the rear connecting member 700. The tail nozzle 701 can adopt a two-section structure, one section is a threaded connection section, and the other section is a nozzle section. The nozzle section forms an angle of 10° - 30° with the threaded connection section. Thus, the tail nozzles with different angles can be rotated for installation as needed to achieve different rotational speeds. It should be noted that those skilled in the art can adjust the threaded connection section to make all the tail nozzles 701 inclined along the same direction around the circumference.

[0077] It can be understood that a threaded connection can be adopted between the anchoring structure 200 and the secondary engine 400, a threaded connection can be adopted between the secondary engine 400 and the intermediate bin 500, a threaded connection can be adopted between the intermediate bin 500 and the primary engine 600, and a threaded connection can be adopted between the primary engine 600 and the rear connecting member 700.

Claims

1. A rocket-powered anchor, characterized in that, include, A warhead, wherein the warhead is a spiral structure; An anchoring structure, the anchoring structure is detachably connected to the warhead, the anchoring structure comprises a plurality of extendable anchor claws, and the angle between the anchor claws and the anchoring structure body after extension is 35°-75°; A secondary engine, wherein the secondary engine is detachably connected to the anchor structure, a secondary delayed ignition device capable of driving the anchor structure to extend is provided at the connection between the secondary engine and the anchor structure, and the secondary engine is filled with a secondary propellant charge; a first-stage engine, wherein the first-stage engine is detachably connected to the second-stage engine, an intermediate compartment is provided at the connection between the second-stage engine and the first-stage engine, a first-stage delayed ignition device is provided on the intermediate compartment, and the first-stage engine is filled with a first-stage propellant; Tail nozzles, a plurality of said tail nozzles are connected to said first stage engine, and said tail nozzles can be tilted at a certain angle so that the rocket powered anchor can rotate when in motion; as well as a lifting ring rotatably connected to the first stage engine; Among them, the total mass of the first-stage propellant charge is less than the total mass of the second-stage propellant charge; a pressure-bearing diaphragm is arranged on the middle partition, and the pressure-bearing diaphragm prevents the combustion gas in the first-stage engine from entering the second-stage engine when the first-stage engine is working; when the second-stage engine is working, the combustion gas in the second-stage engine can break through the pressure-bearing diaphragm, enter the first-stage engine, and be ejected from the tail nozzle.

2. The rocket-powered anchor according to claim 1, characterized in that, The first-stage propellant charge and the second-stage propellant charge are in a form of internal and external simultaneous combustion.

3. A rocket-powered anchor according to claim 1 or 2, characterized in that, The anchoring structure comprises a main shaft, a sliding groove is provided on the side wall of the main shaft, a thrust sleeve is slidably provided on the outside of the main shaft, a thrust piston connected to the thrust sleeve is slidably provided on the inside of the main shaft, a plurality of anchor claws are rotatably connected to the side wall of the main shaft, and the anchor claws are connected to the thrust sleeve; When the secondary delayed ignition device is in operation, it can drive the thrust piston to move in the main shaft, thereby driving the fluke to extend.

4. The rocket-powered anchor according to claim 3, characterized in that, The thrust piston is provided with a first pin hole, the main shaft is provided with a second pin hole, and the first pin hole and the second pin hole are penetrated with breakable pins.

5. A rocket-powered anchor according to claim 1, characterized in that, A plurality of support rods are arranged in the middle compartment, and the pressure-bearing diaphragm is installed on the support rods.

6. The rocket-powered anchor according to claim 5, characterized in that, The side of the pressure-bearing diaphragm close to the support rod is a smooth surface, and the side away from the support rod is provided with a plurality of grooves.

7. A rocket-powered anchor according to claim 1, characterized in that, The tail nozzle has an inclined angle of 10°-30°.

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