Rocket power anchor
The rocket anchor with a dual-pulse propulsion structure enables low-thrust endurance in air and water and high-thrust penetration into the soil, solving the problems of high resistance and rapid energy consumption of existing rocket anchors, and improving the stability and anchoring force of the projectile.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- WUHAN LEISHEN SPECIAL EQUIP
- Filing Date
- 2025-05-16
- Publication Date
- 2026-05-26
AI Technical Summary
Existing rocket anchors experience high resistance when moving in air and water, leading to excessive energy consumption and an inability to penetrate the soil with maximum thrust and speed, thus reducing anchoring strength.
It adopts a dual-pulse power structure, which achieves two-stage triggering through the staged energy release of the first and second stage engines. It uses small thrust to reduce drag and large thrust to penetrate the soil. Combined with extendable anchor claws, it can improve the soil penetration depth and anchoring force.
By effectively utilizing energy, the rocket anchor's penetration depth and anchoring force are increased, ensuring that the projected material takes root stably at the breach or closure point, thus solving the problem that projected material is easily washed away by water flow in existing technologies.
Smart Images
Figure CN224281265U_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical fields of river and lake damming technology and major river diversion construction, specifically involving a rocket-powered anchor. Background Technology
[0002] When river embankments breach, the flow velocity at the breach opening is usually high. Due to the time constraints, materials used for sealing the breach are typically sourced locally. These materials are small and lightweight, easily washed away by the current, making it difficult for them to quickly and stably anchor at the breach site and complete the sealing task. Similarly, in large-scale water conservancy projects involving the closure of major rivers, the problem of high flow velocity at the closure point and the difficulty of materials anchoring quickly also arises. Common methods for breach sealing include horizontal blocking, vertical blocking, and hybrid blocking. While existing closure techniques are relatively mature, they all suffer from drawbacks such as complex construction techniques, long construction times, high costs, and high labor consumption. Sometimes, they can even delay the construction schedule, causing serious losses to subsequent hydropower and other operations. Therefore, it is necessary to develop a new, efficient, convenient, safe, and applicable tool for breach sealing and closure to address these shortcomings.
[0003] Utility model patent No. 2017107262155, Publication No. CN107587507B, discloses a rocket-propelled ground-drilling anchor, comprising a warhead, a secondary trigger expansion anchor mechanism, a rocket engine, and an anti-torsion gyroscope. The tail of the warhead is fixedly connected to the head of the secondary trigger expansion anchor mechanism, the tail of the secondary trigger expansion anchor mechanism is fixedly connected to the head of the rocket engine, the tail of the rocket engine is fixedly connected to the head of the anti-torsion gyroscope, and the tail of the anti-torsion gyroscope is connected to an underground anchor cable. Double-helix cutting blades are provided on the outer surfaces of the warhead shell, the expansion anchor shell, and the rocket engine shell. This patent's powerful rocket thrust allows the anchor to drill deep into the ground, quickly forming a foothold in the soil. Combined with the tail anchor cable connected to a fixed pile on the shore, a projectile suspended on the anchor cable can be quickly and stably anchored at the entrance, preventing it from being washed away by water flow.
[0004] Rocket anchors often need to traverse multiple media during operation, such as air and water, before finally penetrating the soil. Actual tests have shown that the greater the speed of the rocket anchor in air and water, the greater its resistance, resulting in significant energy consumption before penetration. The aforementioned patented rocket-driven drilling anchor uses a single-stage thrust, which cannot effectively distribute energy before and after penetration. This easily leads to excessive energy consumption due to excessive speed and resistance in air and water, preventing the rocket anchor from penetrating the soil with maximum thrust and speed, thus reducing its penetration depth and anchoring force. Utility Model Content
[0005] The purpose of this application is to provide a dual-pulse powered rocket anchor scheme that can achieve two-stage triggering and staged energy release, thereby making full use of energy, increasing the penetration depth, and improving the anchoring force.
[0006] The technical solution adopted in this application is as follows:
[0007] A rocket-powered anchor, comprising,
[0008] The warhead has a helical structure.
[0009] An anchoring structure, which is detachably connected to the warhead, the anchoring structure including a plurality of extendable anchor claws;
[0010] A second-stage engine is detachably connected to the anchoring structure. A second-stage delayed ignition device capable of driving the anchoring structure to extend is provided at the connection between the second-stage engine and the anchoring structure. The second-stage engine is filled with a second-stage propellant charge.
[0011] A first-stage engine is detachably connected to a 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. The first-stage engine is filled with a first-stage propellant charge.
[0012] The tail nozzle, a plurality of said tail nozzles, is connected to said first-stage engine, and said tail nozzles are angled at a certain angle so that the rocket's dynamic anchor can rotate during movement; and
[0013] A lifting ring, which is rotatably connected to the first-stage engine;
[0014] The total mass of the first-stage propellant column is less than the total mass of the second-stage propellant column; a pressure-bearing diaphragm is provided on the intermediate compartment, which prevents the gas in the first-stage engine from entering the second-stage engine when the first-stage engine is working, and allows the gas in the second-stage engine to break through the pressure-bearing diaphragm and enter the first-stage engine and be ejected from the tailpipe when the second-stage engine is working.
[0015] Furthermore, the primary and secondary propellant charges are in a form of simultaneous internal and external combustion.
[0016] Furthermore, the anchoring structure includes a main shaft, a groove is formed on the side wall of the main shaft, a thrust sleeve is slidably disposed outside the main shaft, a thrust piston connected to the thrust sleeve is slidably disposed inside the main shaft, and a plurality of anchor claws are rotatably connected to the side wall of the main shaft, the anchor claws being connected to the thrust sleeve.
[0017] When the secondary delayed ignition device is in operation, it can drive the thrust piston to move within the main shaft, thereby driving the anchor claw to extend.
[0018] Furthermore, the thrust piston is provided with a first pin hole, and the main shaft is provided with a second pin hole, with a breakable pin passing through the first pin hole and the second pin hole.
[0019] Furthermore, a number of support rods are provided inside the intermediate compartment, and the pressure-bearing diaphragm is installed on the support rods.
[0020] Furthermore, the side of the pressure-bearing diaphragm that is close to the support rod is smooth, while the side that is away from the support rod has several grooves.
[0021] Furthermore, the angle of the tail nozzle is 10°-30°.
[0022] The beneficial effects of this application are:
[0023] This application employs a two-stage engine structure, where the thrust of the first-stage engine is less than that of the second-stage engine. This enables two-stage triggering and staged energy release. When the rocket's propulsion anchor operates in air and water, it can sustain its flight with low thrust, reducing speed and drag. When it needs to penetrate the ground, it can achieve soil penetration with high thrust. This application not only makes full use of energy but also penetrates the ground with maximum thrust and speed, increasing the penetration depth and thus enhancing the anchoring force of the rocket anchor. Attached Figure Description
[0024] Figure 1 This is a schematic diagram of the structure of this application when the anchoring structure is not extended;
[0025] Figure 2 A schematic diagram of the structure of this application when the anchoring structure is extended;
[0026] Figure 3 for Figure 2 Cross-sectional view along the 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 intermediate compartment structure in this application;
[0029] Figure 6 This is a schematic diagram of the front connector structure in this application;
[0030] Figure 7 This is a schematic diagram of the rear connector structure in this application;
[0031] Image: 100mm warhead;
[0032] 200 Anchoring structure, 201 Main shaft, 2011 Slide groove, 2012 Second pin hole, 202 Thrust piston, 2021 First pin hole, 203 Thrust sleeve, 204 Anchor claw, 205 Connecting rod, 206 Anchoring housing, 2061 Slotting.
[0033] 300 front connector, 301 secondary delay igniter;
[0034] 400 second-stage engine, 401 second-stage propellant charge;
[0035] 500 Intermediate compartment, 501 Primary delayed ignition device, 502 Pressure diaphragm, 5021 Groove, 503 Support rod, 504 Outer pressure ring, 505 Inner pressure ring;
[0036] 600-class engine, 601-class propellant charge;
[0037] 700 Rear connector, 701 Tail nozzle, 702 Sealing plug, 703 Lifting ring. Detailed Implementation
[0038] To make the above-mentioned features and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.
[0039] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.
[0040] Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" or "several" means at least two, such as two, three, etc., unless otherwise explicitly specified.
[0041] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.
[0042] Reference Figure 1-7 This application provides a rocket propulsion anchor, including,
[0043] The warhead 100 has a helical structure;
[0044] An anchoring structure 200 is detachably connected to the projectile, and the anchoring structure 200 includes a plurality of extendable anchor claws 204.
[0045] A second-stage engine 400 is detachably connected to the anchoring structure 200. A second-stage delayed ignition device 301 capable of driving the anchoring structure 200 to extend is provided at the connection between the second-stage engine 400 and the anchoring structure 200. The second-stage engine 400 is filled with a second-stage propellant charge 401.
[0046] A first-stage engine 600 is detachably connected to a second-stage engine 400. An intermediate compartment 500 is provided at the connection between the second-stage engine 400 and the first-stage engine 600. A first-stage delayed ignition device 501 is provided on the intermediate compartment 500. The first-stage engine 600 is filled with a first-stage propellant charge 601.
[0047] A tailpipe 701, a plurality of tailpipes 701 are connected to the first-stage engine 600, and the tailpipes 701 are capable of adjusting their deflection direction so that the rocket's dynamic anchor can rotate during movement; and
[0048] A lifting ring 703 is rotatably connected to the first-stage engine 600. Specifically, the lifting ring 703 can be connected to the first-stage engine 600 using existing technology. By rotating the lifting ring 703, after connecting to the external cable, the cable can be prevented from getting tangled when the rocket's power anchor rotates.
[0049] The total mass of the first-stage propellant column 601 is less than the total mass of the second-stage propellant column 401. A pressure-bearing diaphragm 502 is provided on the intermediate compartment 500. When the first-stage engine 600 is working, the pressure-bearing diaphragm 502 prevents the gas inside the first-stage engine 600 from entering the second-stage engine 400. When the second-stage engine 400 is working, the gas inside the second-stage engine 400 can break through the pressure-bearing diaphragm 502 and enter the first-stage engine 600 and be ejected from the tail nozzle 701.
[0050] Specifically, the rocket propulsion anchor of this application is placed in the air in a certain manner. The control console sends an ignition signal to the ignition device of the first-stage engine 600 of the rocket propulsion anchor. High-temperature gas is generated in the ignition device, which ignites the first-stage propellant grain 601 in the first-stage engine 600. When the gas in the first-stage engine 600 reaches a certain pressure, it is ejected from the tail nozzle 701, and the first-stage engine 600 begins normal operation, generating thrust to move the rocket propulsion anchor until the first-stage engine 600 has finished working. When the first-stage engine 600 is working, it ignites the first-stage delay ignition device 501 between the first-stage engine 600 and the second-stage engine 400. After the first-stage engine 600 has finished working, the first-stage delay ignition device 501 ignites the second-stage propellant grain 401 in the second-stage engine 400, and the second-stage engine 400 begins working. The gas in the second-stage engine 400 breaks through the pressure-bearing diaphragm 502 set in the intermediate compartment 500, and the gas is ejected through the combustion chamber and nozzle of the first-stage engine 600 until the second-stage engine 400 has finished working. When the second-stage engine 400 operates, it ignites the second-stage delay igniter 301 of the anchoring mechanism. After the second-stage engine 400 completes operation, the ignited second-stage delay igniter 301 generates high-pressure gas, which drives the anchoring mechanism to extend. When the rocket's powered anchor receives a pull-out force and retracts towards the ground, the extended anchoring mechanism increases the surface area exposed to the ground, thereby enhancing the anchoring force.
[0051] The pressure-bearing diaphragm 502 installed within the intermediate compartment 500 is required to withstand pressure in the forward direction and open in the reverse direction. Specifically, it must withstand forward pressure during the operation of the first-stage engine 600 to prevent the combustion gases from entering the second-stage engine 400. When the second-stage engine 400 operates, the generated combustion gases act in the reverse direction on the pressure-bearing diaphragm 502, potentially rupturing it and allowing the gases to flow out through the combustion chamber and nozzle of the first-stage engine 600. By installing the pressure-bearing diaphragm 502, the first-stage engine 600 and the second-stage engine 400 can operate in a time-sharing manner, preventing the first-stage engine 600 from igniting the second-stage engine 400 during operation.
[0052] In a preferred embodiment, both the primary propellant grain 601 and the secondary propellant grain 401 can use high-burning-rate modified carbon black (GHT) propellant. The basic properties of the propellant are shown in Table 1.
[0053] Table 1 Basic performance parameters of GHT propellant
[0054]
[0055]
[0056] As a preferred embodiment, the propellant parameters of the first-stage engine 600 and the second-stage engine 400 are shown in Table 2, and the internal ballistic parameters of the first-stage engine 600 and the second-stage engine 400 are shown in Table 3.
[0057] Table 2. Parameters for Explosive Loading
[0058]
[0059] Table 3. Main parameters of the calculated internal ballistics for the two-stage engine.
[0060]
[0061] This application employs a two-stage engine structure, where the thrust of the first-stage engine (600) is less than that of the second-stage engine (400), enabling two-stage triggering and staged energy release. When the rocket-powered anchor of this application operates in air and water, it can sustain its flight with a low thrust, reducing speed and drag. When it needs to penetrate the ground, it can complete the penetration with a high thrust. This application not only makes full use of energy but also penetrates the ground with maximum thrust and speed, increasing the penetration depth and thus improving the anchoring force of the rocket-powered anchor.
[0062] It is understood that the primary propellant charge 601 and the secondary propellant charge 401 are in the form of simultaneous internal and external combustion.
[0063] Reference Figure 3 and 4 It is understood that the anchoring structure 200 includes an anchoring housing 206, which is detachably connected to the projectile 100, specifically by bolts. The anchoring housing 206 has several slots 2061 that allow the anchor claws 204 to extend. The anchoring structure 200 includes a main shaft 201, with at least one sliding groove 2011 on its side wall. A thrust sleeve 203 is slidably disposed outside the main shaft 201, and a thrust piston 202 connected to the thrust sleeve 203 is slidably disposed inside the main shaft 201. Several 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.
[0064] When the secondary delayed ignition device 301 is working, it can drive the thrust piston 202 to move within the main shaft 201, thereby driving the anchor claw 204 to extend.
[0065] Specifically, the secondary delay ignition device 301 is located at the end of the main shaft 201. When the secondary delay ignition device 301 is ignited, it generates high-pressure gas. This high-pressure gas impacts the thrust piston 202, causing it to move within the main shaft 201 and thus driving the thrust sleeve 203 to move outside the main shaft 201. The thrust sleeve 203, through the connecting rod 205, pushes the anchor claw 204 out of the slot 2061 of the anchoring housing 206, thereby extending it into the soil. When the rocket-powered anchor is subjected to external tension, the anchor claw 204 can further extend and insert into the soil, thereby increasing the anchoring force.
[0066] Reference Figure 3 and 4 It is understood that the thrust piston 202 is provided with a first pin hole 2021, and the main shaft 201 is provided with a second pin hole 2012. A breakable pin is inserted through the first pin hole 2021 and the second pin hole 2012.
[0067] Specifically, by setting the foldable pin, the anchoring structure 200 is initially locked, preventing the anchor claw 204 from extending due to vibration or other factors. When the secondary delay igniter 301 is ignited, the high-pressure gas generated has a sufficiently large thrust to break the pin, thereby unlocking the anchoring structure 200 and allowing the anchor claw 204 to extend.
[0068] Reference Figure 5 It is understood that a number of support rods 503 are provided inside the intermediate compartment 500, and the pressure-bearing diaphragm 502 is installed on the support rods 503.
[0069] Specifically, several support rods 503 are disposed within the intermediate compartment 500 to support the pressure-bearing diaphragm 502, preventing the combustion gases in the first-stage engine 600 from breaking through the pressure-bearing diaphragm 502. Simultaneously, sufficient space is provided between the support rods 503 to allow the combustion gases in the second-stage engine 400 to enter the first-stage engine 600 through the intermediate compartment 500. The pressure-bearing diaphragm 502 has a circular structure and is mounted on the support rods 503 via an outer pressure ring 504 and an inner pressure ring 505, with one side of the support facing the second-stage engine 400. The first-stage delayed ignition device 501 is disposed in the middle of the support rod 503.
[0070] Reference Figure 5It is understood that the side of the pressure-bearing diaphragm 502 that is close to the support rod 503 is smooth, and the side that is away from the support rod 503 is provided with a number of grooves 5021.
[0071] Specifically, by providing a groove 5021 on one side of the pressure-bearing diaphragm 502, the pressure-bearing diaphragm 502 can be easily broken through when subjected to the gas impact generated by the secondary engine 400.
[0072] Reference Figure 7 It is understood that the angle of the tail nozzle 701 is 10°-30°.
[0073] Specifically, a plurality of tail nozzles 701 are arranged in a circular structure on the rear connector 700. The plurality of tail nozzles 701 are obliquely positioned at a certain angle in the same direction around the circumference, so that the thrust of the tail nozzles 701 is decomposed into a rotational torque that rotates axially. A sealing plug 702 is provided in the tail nozzle 701. When the internal combustion gas of the first-stage engine 600 reaches a certain pressure, it can break through the sealing plug 702 and be ejected from the tail nozzle 701.
[0074] It should be noted that the ignition device of the first-stage engine 600 is located inside the first-stage engine 600, and its lead wire can extend through the sealing plug 702 on one of the tail nozzles 701. The sealing plug 702 can be provided with a through hole to allow the lead wire to extend.
[0075] It is understood that the tail nozzle 701 and the rear connector 700 can be detachably connected, for example, by a threaded connection. The tail nozzle 701 can have a two-section structure, one section being a threaded connection section and the other being a nozzle section, wherein the nozzle section forms an angle of 10°-30° with the threaded connection section. This allows for different rotation speeds by rotating the tail nozzles at different angles as needed. It should be noted that those skilled in the art can adjust the threaded connection section to ensure that all tail nozzles 701 are angled in the same direction around the circumference.
[0076] It is understood that the anchoring structure 200 and the secondary engine 400 can be connected by threads, the secondary engine 400 and the intermediate compartment 500 can be connected by threads, the intermediate compartment 500 and the primary engine 600 can be connected by threads, and the primary engine 600 and the rear connector 700 can be connected by threads.
Claims
1. A rocket-powered anchor, characterized in that, include, The warhead has a helical structure. An anchoring structure, which is detachably connected to the warhead, the anchoring structure including a plurality of extendable anchor claws; A second-stage engine is detachably connected to the anchoring structure. A second-stage delayed ignition device capable of driving the anchoring structure to extend is provided at the connection between the second-stage engine and the anchoring structure. The second-stage engine is filled with a second-stage propellant charge. A first-stage engine is detachably connected to a 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. The first-stage engine is filled with a first-stage propellant charge. The tail nozzles are connected to the first-stage engine, and the tail nozzles can be tilted at a certain angle so that the rocket's power anchor can rotate when it is in motion. as well as A lifting ring, which is rotatably connected to the first-stage engine; The total mass of the first-stage propellant column is less than the total mass of the second-stage propellant column; a pressure-bearing diaphragm is provided on the intermediate compartment, which prevents the gas in the first-stage engine from entering the second-stage engine when the first-stage engine is working, and allows the gas in the second-stage engine to break through the pressure-bearing diaphragm and enter the first-stage engine and be ejected from the tailpipe when the second-stage engine is working.
2. The rocket dynamic anchor according to claim 1, characterized in that, The primary and secondary propellant charges are in a form of simultaneous internal and external combustion.
3. A rocket-powered anchor according to claim 1 or 2, characterized in that, The anchoring structure includes a main shaft with a groove on its side wall, a thrust sleeve slidably disposed outside the main shaft, a thrust piston slidably disposed inside the main shaft and connected to the thrust sleeve, and a plurality of anchor claws rotatably connected to the side wall of the main shaft, the anchor claws being connected to the thrust sleeve. When the secondary delayed ignition device is in operation, it can drive the thrust piston to move within the main shaft, thereby driving the anchor claw to extend.
4. A rocket dynamic anchor according to claim 3, characterized in that, The thrust piston is provided with a first pin hole, and the main shaft is provided with a second pin hole. A breakable pin passes through the first pin hole and the second pin hole.
5. A rocket-powered anchor according to claim 1, characterized in that, The intermediate compartment is provided with several support rods, and the pressure-bearing diaphragm is installed on the support rods.
6. A rocket powered anchor according to claim 5, characterized in that, The side of the pressure-bearing diaphragm that is close to the support rod is smooth, while the side that is away from the support rod has several grooves.
7. A rocket powered anchor according to claim 1, characterized in that, The tail nozzle is tilted at an angle of 10°-30°.