High-precision hydraulic lifting oil cylinder for missile launcher

Abstract

The invention discloses a high-precision hydraulic lifting oil cylinder for a missile launcher, and relates to the technical field of hydraulic control, in particular to a high-precision hydraulic lifting oil cylinder device applied to the missile launcher, which is used for realizing precise control of missile launching elevation angle and direction adjustment. The cylinder body is arranged outside the oil cylinder to form a hydraulic oil cavity, the piston rod assembly is arranged in the cylinder body, the sealing system is arranged in the cylinder body, the lower connecting seat is fixedly arranged at the bottom of the cylinder body, and the magnetostrictive displacement sensor is longitudinally arranged in the piston rod. The hydraulic oil inlet and outlet ports are respectively arranged on the side wall of the cylinder body and are respectively communicated with two hydraulic cavities in the cylinder body; the control valve assembly is arranged on the cylinder body and connected with the hydraulic oil channel. The cylinder body is sleeved with the protective cover shell. The long-time fault-free operation of the oil cylinder in the field severe environment can be ensured, and the service life and the stability of equipment are ensured; the missile launcher can stably work in an environment of-40 DEG C to + 70 DEG C so as to meet missile launching task requirements under different geographical and climate conditions; fault parts can be quickly detached and replaced on site, and the maintenance period is greatly shortened.

Description

Technical Field

[0001] The present invention relates to the technical field of hydraulic control, and particularly to a high-precision hydraulic lifting cylinder device applied to a missile launcher, which is used to achieve precise control of the elevation angle and direction adjustment of missile launch. Background Art

[0002] As a key component of the ground launch system, the missile launcher mainly undertakes tasks such as missile carrying, transportation, orientation, and launch. One of its core functions is to quickly and accurately adjust the missile launch angle. The current mainstream elevation adjustment mechanism of the launcher mostly relies on the lifting or rotating power provided by the hydraulic system. As the core executing component of this system, the performance of the hydraulic lifting cylinder directly affects the response speed, aiming accuracy, and reliability of missile launch.

[0003] However, most of the existing hydraulic lifting cylinders are modified based on traditional industrial standard cylinders, and there are the following main problems: Traditional hydraulic cylinders generally adopt an open-loop control method, relying only on pressure or flow control, and cannot achieve high-precision position adjustment. Some models are equipped with simple displacement sensors, but the feedback frequency and resolution are relatively low, unable to meet the strict requirements of missile elevation angle ≤ 0.1° error. In cold, high-temperature, high-humidity, or sandy and dusty environments, conventional hydraulic cylinders are prone to problems such as seal aging, changes in hydraulic oil viscosity, and sensor failure, seriously affecting the battlefield adaptability and reliability of the missile system. Due to the large reaction force during missile launch, the cylinder needs to have high-intensity anti-impact performance. Traditional structural design and material selection often have difficulty in meeting the dual requirements of lightweight and high strength, and the service life is difficult to guarantee. The existing hydraulic systems generally adopt a fixed connection structure, and the whole needs to be disassembled when maintaining and replacing the cylinder, which is not conducive to rapid repair or component replacement under field conditions. Summary of the Invention

[0004] Aiming at the deficiencies of the prior art, the present invention provides a high-precision hydraulic lifting cylinder for a missile launcher, which can ensure the long-term trouble-free operation of the cylinder in harsh field environments, ensure the service life and equipment stability; it can work stably in the environment of -40°C to +70°C to meet the missile launch mission requirements under different geographical and climatic conditions; it can quickly replace faulty components on-site, greatly shortening the maintenance cycle.

[0005] To achieve the above object, the present invention provides the following technical solutions: It includes a cylinder block body 1, a piston rod assembly 2, a piston and sealing system 3, an upper connector 4, a lower connection seat 5, a magnetostrictive displacement sensor 6, a hydraulic oil inlet and outlet interface 7, a control valve assembly 8, and an outer housing 9; The cylinder block body 1 is arranged outside the oil cylinder to form a hydraulic oil cavity, the piston rod assembly 2 is arranged inside the cylinder block body 1, the sealing system 3 is arranged inside the cylinder block body 1, the lower connection seat 5 is fixedly arranged at the bottom of the cylinder block body 1, the magnetostrictive displacement sensor 6 is longitudinally arranged along the inside of the piston rod, and the hydraulic oil inlet and outlet interfaces 7 are respectively arranged on the side wall of the cylinder block body 1 and respectively communicate with two hydraulic cavities inside the cylinder block body; The control valve assembly 8 is arranged on the cylinder block body 1 and is connected to the hydraulic oil passage; The protective housing 9 is sleeved outside the cylinder block body 1.

[0006] A guide sleeve is arranged inside the cylinder block body 1, and the outer surface of the cylinder block body 1 is subjected to phosphating anti-rust treatment.

[0007] The piston rod assembly 2 includes a piston 21 and a piston rod 22. Between the piston 21 and the inner wall of the cylinder block body 1, two independent hydraulic cavities are sealed and separated by a sealing assembly; The piston rod assembly 2 is of a hollow structure, and a magnetostrictive displacement sensor 6 is installed inside, and the outer surface is treated with a hard chromium plating layer to enhance wear resistance and corrosion resistance.

[0008] One end of the piston rod 22 is fixedly connected to the piston 21, and the other end of the piston rod 22 passes through the cylinder block body 1 and is connected to the upper connector 4. The upper connector 4 is arranged at the outer end of the piston rod 22 and is used for hinged connection with the movable bracket of the missile launch rack;

[0009] The lower connection seat 5 is arranged at the lower end of the cylinder block body 1 and is used for connection with the fixed bracket of the missile launch platform through bolts;

[0010] The magnetostrictive displacement sensor 6 is used to detect the telescopic displacement of the piston rod in real time;

[0011] The control valve assembly 8 selects an electro-hydraulic proportional valve or a servo valve. The control valve assembly 8 is connected to the hydraulic oil passage and is used to receive external instructions and adjust the hydraulic flow rate and pressure;

[0012] The protective housing 9 is used to protect against external impacts, dust, and impurities;

[0013] Multiple composite sealing rings are assembled at the end of the piston 21. The sealing rings include a main sealing ring, a guide ring, and a dust ring) to ensure no leakage under high-pressure environments.

[0014] The upper end of the piston rod 22 is hinged and fixed to the upper connector 4 and is connected to the missile launch rack bracket through a pin shaft, allowing a certain range of swing during the lifting process to adapt to the adjustment of the launch angle.

[0015] The lower connecting seat 5 is fixedly connected to the missile launch platform or the vehicle body base. The flange seat is fixed by both high-strength bolts and positioning pins to ensure the firm and reliable installation of the oil cylinder.

[0016] Working principle: When the present invention is in use, the hydraulic pump station provides high-pressure hydraulic oil, which is transported to the hydraulic oil inlet and outlet interfaces of the oil cylinder through the hydraulic pipeline. The control valve assembly (electro-hydraulic proportional valve or servo valve) receives instructions from the missile launch control system, precisely adjusts the flow rate and pressure of the hydraulic oil, and controls the pressure difference between the two hydraulic chambers at both ends of the oil cylinder.

[0017] By controlling the pressure difference between the two chambers, the piston 21 and the piston rod 22 are urged to perform axial linear telescopic motion along the inside of the cylinder body 1, realizing the elevation or depression of the angle of the missile launch rack.

[0018] A multi-channel sealing system (main sealing ring, guide ring, dust-proof ring) provided between the piston and the cylinder body ensures excellent sealing performance even under high-pressure and high-frequency working conditions, avoiding hydraulic oil leakage.

[0019] The piston rod assembly is of a hollow structure, and a magnetostrictive displacement sensor 6 is installed inside. The sensor continuously detects the displacement of the piston rod and outputs position signals to the hydraulic control unit at high frequency and high resolution to realize closed-loop control of the position. The system dynamically adjusts the valve control parameters according to the feedback signal to ensure high-precision positioning of the piston rod movement (control accuracy is better than ±0.1 mm).

[0020] A protective cover 9 is externally provided to effectively resist the invasion of external pollutants such as sand, mud, and rainwater, protect the hydraulic cylinder body and the sensor system, and extend the service life of the equipment. The cylinder body is subjected to phosphating rust prevention treatment, and the surface of the piston rod is plated with a hard chromium layer to enhance the overall corrosion resistance, wear resistance, and environmental adaptability of the oil cylinder.

[0021] The upper end of the piston rod is hinged to the support arm of the missile launch rack through the upper connecting head 4, and the lower connecting seat 5 is fixed to the launch platform base through flange bolts and positioning pins. The hinged structure allows the oil cylinder to swing within a certain range to adapt to the attitude change of the launch rack during the lifting and lowering process, and at the same time facilitates quick replacement and maintenance.

[0022] The present invention realizes high-precision and real-time displacement detection through the built-in magnetostrictive displacement sensor, and combines with an electro-hydraulic proportional valve or a servo valve to form a closed-loop control system. The position control accuracy is better than ±0.1 mm, which can meet the strict requirements of the missile launch angle error ≤ 0.1°, greatly improving the missile launch hit rate and the system response speed. The whole system can operate normally in the extreme environment from -40°C to +70°C, meeting the combat requirements in various complex environments such as cold regions, plateaus, high temperatures, and sandstorms.

[0023] In the present invention, the outer housing and the sealing system are jointly protected, with excellent dust-proof, anti-corrosion, and waterproof performance, significantly extending the service life. The cylinder block and the piston rod are made of high-strength alloy steel, combined with advanced surface treatment processes (phosphating, hard chromium plating), and the overall anti-impact, anti-wear, and anti-corrosion performance is excellent. The multi-channel composite sealing structure at the piston end effectively improves the sealing reliability and the durability of the oil cylinder, and the designed service life exceeds 100,000 full-stroke action cycles. The oil cylinder adopts a modular design, and the upper connecting head and the lower connecting seat can be quickly disassembled and assembled. The piston rod assembly and the sealing system are convenient for on-site replacement, shortening the field maintenance time and improving the combat continuity. It has the ability of self-detection and fault tolerance. When the hydraulic system or the sensor is abnormal, it can operate through the redundant circuit or the emergency mode to ensure that the missile launch mission is not interrupted. The control valve assembly has a fast response and has overpressure protection and anti-shock protection functions to ensure the stable and safe operation of the system. Brief Description of the Drawings

[0024] The drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation to the present invention.

[0025] Figure 1 is a schematic structural diagram of the present invention;

[0026] In the figure: cylinder block body 1, piston rod assembly 2, piston and sealing system 3, upper connecting head 4, lower connecting seat 5, magnetostrictive displacement sensor 6, hydraulic oil inlet and outlet interface 7, control valve assembly 8, outer housing 9, piston 21, piston rod 22. Detailed Embodiments

[0027] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0028] Please refer to Figure 1 , the following technical solutions are adopted in this detailed embodiment:

[0029] It includes a cylinder block body 1, a piston rod assembly 2, a piston and sealing system 3, an upper connector 4, a lower connection seat 5, a magnetostrictive displacement sensor 6, hydraulic oil inlet and outlet interfaces 7, a control valve assembly 8, and an outer housing 9; the cylinder block body 1 is arranged outside the oil cylinder to form a hydraulic oil chamber, the piston rod assembly 2 is arranged inside the cylinder block body 1, the sealing system 3 is arranged inside the cylinder block body 1, the lower connection seat 5 is fixedly arranged at the bottom of the cylinder block body 1, the magnetostrictive displacement sensor 6 is longitudinally arranged along the inside of the piston rod, and the hydraulic oil inlet and outlet interfaces 7 are respectively arranged on the side wall of the cylinder block body 1 and are respectively communicated with two hydraulic chambers inside the cylinder block body; the control valve assembly 8 is arranged on the cylinder block body 1 and is connected to the hydraulic oil passage; the protective housing 9 is sleeved outside the cylinder block body 1.

[0030] A guide sleeve is arranged inside the cylinder block body 1, and the outer surface of the cylinder block body 1 is subjected to phosphating anti-rust treatment. The piston rod assembly 2 includes a piston 21 and a piston rod 22. Between the piston 21 and the inner wall of the cylinder block body 1, two independent hydraulic chambers are sealed and separated by a sealing assembly; the piston rod assembly 2 is of a hollow structure, and a magnetostrictive displacement sensor 6 is installed inside, and the outer surface is treated with a hard chromium plating layer to enhance wear resistance and corrosion resistance.

[0031] One end of the piston rod 22 is fixedly connected to the piston 21, and the other end of the piston rod 22 passes through the cylinder block body 1 and is connected to the upper connector 4. The upper connector 4 is arranged at the outer end of the piston rod 22 and is used for hinged connection with the movable support of the missile launcher; the lower connection seat 5 is arranged at the lower end of the cylinder block body and is used for connection with the fixed support of the missile launch platform through bolts; the magnetostrictive displacement sensor 6 is used for real-time detection of the telescopic displacement of the piston rod; the control valve assembly 8 selects an electro-hydraulic proportional valve or a servo valve. The control valve assembly 8 is connected to the hydraulic oil passage and is used for receiving external commands and adjusting the hydraulic flow rate and pressure; the protective housing 9 is used for protecting against external impacts, dust, and impurities; multiple composite sealing rings are assembled at the end of the piston 21. The sealing ring includes a main sealing ring, a guide ring, and a dust ring to ensure no leakage under high-pressure environments. The upper end of the piston rod 22 is hinged and fixed to the upper connector 4 and is connected to the missile launcher support through a pin shaft, allowing a certain range of swing during the lifting process to adapt to the adjustment of the launch angle. The lower connection seat 5 is fixedly connected to the missile launch platform or the vehicle body base, and the flange seat is fixed by both high-strength bolts and positioning pins to ensure the firm and reliable installation of the oil cylinder.

[0032] The present invention realizes high-precision and real-time displacement detection through an internally installed magnetostrictive displacement sensor, and forms a closed-loop control system in combination with an electro-hydraulic proportional valve or a servo valve. The position control accuracy is better than ±0.1 mm, which can meet the stringent requirements of the missile launch angle error ≤ 0.1°, and greatly improve the missile launch hit rate and the system response speed. The entire system can operate normally in the extreme environment of -40°C to +70°C, meeting the combat requirements in various complex environments such as cold regions, plateaus, high temperatures, and sandstorms.

[0033] In the present invention, the outer cover and the sealing system are jointly protected, with excellent dust, corrosion, and water resistance, significantly extending the service life. The cylinder body and the piston rod are made of high-strength alloy steel, combined with advanced surface treatment processes (phosphating, hard chromium plating), and the overall impact resistance, wear resistance, and corrosion resistance are excellent. The multi-channel composite sealing structure at the piston end effectively improves the sealing reliability and the durability of the oil cylinder, and the designed service life exceeds 100,000 full-stroke action cycles. The oil cylinder adopts a modular design, and the upper connection head and the lower connection seat can be quickly disassembled and assembled. The piston rod assembly and the sealing system are convenient for on-site replacement, shortening the field maintenance time and improving the combat continuity. It has self-detection and fault tolerance capabilities. When the hydraulic system or the sensor is abnormal, it can operate through redundant circuits or emergency modes to ensure that the missile launch mission is not interrupted. The control valve assembly has a rapid response and has overpressure protection and anti-shock protection functions to ensure the stable and safe operation of the system.

[0034] The above are only the preferred embodiments of the present invention, and do not impose any form of limitation on the present invention. Although the present invention has been disclosed as above with the preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some changes or modifications to the equivalent embodiments with equivalent changes within the scope of the technical solution of the present invention. However, as long as it does not depart from the content of the technical solution of the present invention, any simple modification, equivalent change, and modification made to the above embodiments based on the technical essence of the present invention still fall within the scope of the technical solution of the present invention.

Claims

1. A high-precision hydraulic lifting cylinder for a missile launcher, characterized in that It includes a cylinder block body (1), a piston rod assembly (2), a piston and sealing system (3), an upper connector (4), a lower connection seat (5), a magnetostrictive displacement sensor (6), a hydraulic oil inlet and outlet interface (7), a control valve assembly (8), and an outer housing (9); the cylinder block body (1) is arranged outside the oil cylinder to form a hydraulic oil chamber, the piston rod assembly (2) is arranged inside the cylinder block body (1), the sealing system (3) is arranged inside the cylinder block body (1), the lower connection seat (5) is fixedly arranged at the bottom of the cylinder block body (1), the magnetostrictive displacement sensor (6) is longitudinally arranged along the inside of the piston rod, and the hydraulic oil inlet and outlet interfaces (7) are respectively arranged on the side wall of the cylinder block body (1) and are respectively communicated with two hydraulic chambers inside the cylinder block body; the control valve assembly (8) is arranged on the cylinder block body (1) and is connected to the hydraulic oil passage; the protective housing (9) is sleeved outside the cylinder block body (1).

2. The high-precision hydraulic lifting oil cylinder for a missile launcher according to claim 1, wherein: A guide sleeve is arranged inside the cylinder block body (1), and the outer surface of the cylinder block body (1) is treated with phosphating for rust prevention.

3. The high-precision hydraulic lifting oil cylinder for a missile launcher according to claim 1, wherein: The piston rod assembly (2) includes a piston (21) and a piston rod (22). Between the piston (21) and the inner wall of the cylinder block body (1), two independent hydraulic chambers are sealed and separated by a sealing component; the piston rod assembly (2) is of a hollow structure, with a magnetostrictive displacement sensor (6) installed inside, and the outer surface is treated with a hard chromium plating.

4. A high-precision hydraulic lifting cylinder for a missile launcher according to claim 1, characterized in that: One end of the piston rod (22) is fixedly connected to the piston (21), and the other end of the piston rod (22) passes through the cylinder block body (1) and is connected to the connection seat of the upper connector (4). The upper connector (4) is arranged at the outer end of the piston rod (22) and is used for hinged connection with the movable bracket of the missile launcher.

5. A high-precision hydraulic lifting cylinder for a missile launcher according to claim 1, characterized in that: The lower connection seat (5) is arranged at the lower end of the cylinder block body and is used for connection with the fixed bracket of the missile launch platform through bolts.

6. A high-precision hydraulic lifting cylinder for a missile launcher according to claim 1, characterized in that: The magnetostrictive displacement sensor (6) is used for real-time detection of the telescopic displacement of the piston rod.

7. A high-precision hydraulic lifting oil cylinder for a missile launcher according to claim 1, characterized in that: The control valve assembly (8) selects an electro-hydraulic proportional valve or a servo valve, and the control valve assembly (8) is connected to the hydraulic oil passage.

8. A high-precision hydraulic lifting cylinder for a missile launcher according to claim 1, characterized in that: Multiple composite sealing rings are assembled at the end of the piston (21).

9. The high-precision hydraulic lifting oil cylinder for a missile launcher according to claim 1, wherein: The upper end of the piston rod (22) is hinged and fixed to the upper connector (4) and is connected to the missile launcher bracket through a pin shaft, allowing it to swing within a certain range during the lifting process to adapt to the adjustment of the launch angle.

10. A high-precision hydraulic lifting oil cylinder for a missile launcher according to claim 1, characterized in that: The lower connection seat (5) is fixedly connected to the missile launch platform or the vehicle body base, and the flange seat is fixed by both high-strength bolts and positioning pins.

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