An ejection system based on the liquid-electric effect

Abstract

The present invention discloses a catapult system based on the electrohydraulic effect, belonging to the field of catapult technology. The present invention symmetrically mounts electrohydraulic effect generators at the starting end of a catapult rail and on both sides of the rail in its extension direction, pulling and propelling the shuttle of an aircraft within the catapult rail. The electrohydraulic effect generator serves as the catapult power source. Liquid supplied by a liquid supply device, under the action of a high-voltage, high-power pulse current supplied by a high-power pulse power supply, stimulates the electrohydraulic effect, generating a high-speed, vapor-liquid mixed state shock wave with a pressure exceeding hundreds of megapascals. This shock wave is transmitted through the open end of the electrohydraulic effect generator tube into the catapult rail, propelling the shuttle within the catapult rail to pull the aircraft to glide at high speed along the rail in its extension direction, thereby achieving catapult takeoff of the aircraft. Compared to steam catapults, the system has the advantages of reduced size and weight, and high efficiency. Compared to electromagnetic catapults, the system has the advantages of reduced system complexity, low cost, and low requirements for cooling and electromagnetic protection.

Description

Technical Field

[0001] The present invention relates to an ejection system, in particular to an ejection system based on a hydroelectric effect. Background Art

[0002] During the launch phase, high-temperature gas, compressed air, steam, electromagnetic force, and other propulsion systems are typically used to establish the initial velocity of an aircraft or spacecraft. For example, in one of the most typical applications, modern aircraft carrier-based aircraft often use external propulsion to rapidly accelerate and reach takeoff speed within the limited flight deck distance. Depending on the method of generating the propulsion force, there are two main technical approaches for large aircraft: steam catapults and electromagnetic catapults. Steam catapult technology is relatively mature. Its basic principle is to set up a slide rail on the flight deck of the aircraft carrier, and install a cylinder parallel to the slide rail. The shuttle can slide freely in the length direction of the slide rail under the constraint of the slide rail. The lower part of the shuttle is connected to the piston, and the piston is installed in the cylinder. The shuttle hooks the landing gear of the aircraft to ensure that when the shuttle slides along the slide rail, it can drive the aircraft to accelerate along the direction of the slide rail. The nuclear reactor on the aircraft carrier heats water to generate high-temperature and high-pressure steam. The high-temperature and high-pressure steam enters the cylinder to expand and drive the piston and the shuttle connected to the piston to accelerate along the length direction of the slide rail. The shuttle pulls the aircraft through the aircraft landing gear to accelerate the slide until the aircraft reaches the take-off speed and the landing gear separates from the shuttle. Steam catapults have the advantages of simple principles and high technical maturity, but their implementation requires high-temperature and high-pressure steam storage tanks, pipelines, valves and other equipment, which are extremely large in size and weight. According to public information, the complete set of steam catapults on US aircraft carriers has a volume of more than 1,100 cubic meters and a total weight of nearly 500 tons. In addition, there are prominent problems such as difficulty in accurately controlling energy output, energy utilization rate of less than 10%, and continuous operation will cause a decrease in aircraft carrier power. The commonly used technology for electromagnetic catapults is based on the principle of linear motors. Several coils are installed along the length of the lower rail, constraining the shuttle to slide freely along the length of the rail. A strong magnet is installed under the shuttle, which hooks onto the aircraft's landing gear, ensuring that as the shuttle slides along the rail, it accelerates the aircraft along the rail. By controlling the on-off timing and phase sequence of the current in the coils under the rail, a magnetic field with time-varying strength and direction is generated along the length of the rail. This magnetic field interacts with the strong magnet under the shuttle, creating a push-pull effect on the magnet, which in turn drives the shuttle and accelerates the aircraft along the length of the rail until the aircraft reaches takeoff speed and the landing gear separates from the shuttle. The electromagnetic catapult system publicly disclosed by the US military has a volume of approximately 500 cubic meters, weighs approximately 300 tons, and boasts an energy efficiency of 60%.Despite its significant advantages over steam catapults, electromagnetic catapults also present pressing challenges. For one, electromagnetic catapults based on the linear motor principle require precise control of the power supply timing and phase sequence for each coil, requiring an ultra-high-frequency inverter and control system. This makes implementation complex and the system expensive. Similarly, electromagnetic catapults similar to those used in railguns require an interference fit between the shuttle and rail to prevent sparks and erosion caused by the gap between the shuttle and rail, which can easily cause the rail to wear and fail. Regardless of the electromagnetic catapult method, the high current and magnetic induction currents generate high temperatures, affecting the stiffness and lifespan of the permanent magnets, rails, and shuttles. The use of high-power cooling systems undoubtedly increases volume, weight, and energy consumption. Regardless of the electromagnetic catapult method, the high currents lead to strong electromagnetic interference. Because electromagnetic catapults present several issues that require improvement and enhancement, the industry has differing opinions on their large-scale promotion, and methods or measures to replace or enhance them are urgently needed. Summary of the Invention

[0003] The present invention aims to provide a launch system that is small in size, light in weight, simple to implement, relatively inexpensive, has a long service life, controllable output energy, high reliability, and is less affected by temperature and magnetic fields. It combines the advantages of electromagnetic catapults and steam catapults while effectively overcoming their shortcomings. To achieve the above-mentioned objectives, the present invention adopts the following technical solutions: a catapult system based on the electrohydraulic effect, comprising a catapult guide rail, an electrohydraulic effect generator, a high-power pulse power supply, a liquid supply device, and a shuttle. The electrohydraulic effect generator is fixedly installed symmetrically at the starting end of the catapult guide rail and on both sides of the extension direction of the catapult guide rail, and the shuttle is embedded in the catapult guide rail and can slide freely along the extension direction of the catapult guide rail; the electrohydraulic effect generator is a tubular object equipped with a liquid level sensor and a generator plug cover, with one open end located on the inner side of the catapult guide rail. The generator plug cover is used to seal the tube body to ensure that liquid can be stored in the tube body. The generator plug cover is located on the inner part of the tube body and is equipped with a pair of discharge electrodes. The discharge electrodes pass through the generator plug cover and are connected to the outer power supply end. The liquid inlet runs through the inner and outer sides of the generator plug cover for replenishing liquid into the electrohydraulic effect generator; the high-power pulse power supply is connected to the power supply end on each electrohydraulic effect generator through a cable; and the liquid supply device is connected to the liquid inlet on each electrohydraulic effect generator through a pipeline.

[0004] Furthermore, the high-power pulse power supply can output high-voltage and high-power pulse current to each electrohydraulic effect generator through the power supply end on the cable and the generator cover according to the set timing.

[0005] Furthermore, the liquid supply device can replenish the working fluid through the pipeline and the liquid replenishing port on the generator cover when the liquid level of the liquid level sensor in the electrohydraulic effect generator is lower than the set value.

[0006] Furthermore, the discharge electrode in the electrohydraulic effect generator produces an electrohydraulic effect with the liquid under the action of high-voltage and high-power pulse current, generating a high-speed jet of a vapor-liquid mixture and forming a pressure of up to hundreds of MPa, which is transmitted to the ejection guide rail through one end of the open tube of the electrohydraulic effect generator.

[0007] Furthermore, a deceleration device is provided at the end of the ejection guide rail, which can absorb the kinetic energy of the shuttle and ensure that the shuttle decelerates and stops at the end of the ejection guide rail.

[0008] Furthermore, the shuttle is designed with a hooking structure that matches the aircraft, which can hook the aircraft landing gear or other towable structures to tow the aircraft to slide.

[0009] Furthermore, the ejection speed can be increased by symmetrically adding electrohydraulic effect generators in pairs along the extension direction of the ejection guide rail.

[0010] A method for using a catapult system based on a hydro-electric effect:

[0011] First, the shuttle is hooked onto the aircraft landing gear or other towable structure, and parked at the starting end of the ejection rail. The liquid supply device injects liquid into each electrohydraulic effect generator through the pipeline and the liquid filling port on the generator cover, and the high-power pulse power supply stores electrical energy.

[0012] Afterwards, the high-power pulse power supply outputs high-voltage and high-power pulse current to the electrohydraulic effect generator installed at the starting end of the ejection rail through the power supply end on the cable and the generator cover. The high-speed jet of gas-liquid mixture generated by the electrohydraulic effect generator acts on the rear end of the shuttle, and the thrust generated causes the shuttle to accelerate and glide on the ejection rail. During the sliding of the shuttle on the ejection rail, the high-power pulse power supply outputs high-voltage and high-power pulse current to the electrohydraulic effect generators located on both sides of the ejection rail in turn and in a timely manner through the power supply end on the cable and the generator cover, ensuring that the high-speed jet of gas-liquid mixture generated by the symmetrical electrohydraulic effect generators on both sides acts just on the rear end of the shuttle, driving the shuttle to drive the aircraft to continuously accelerate along the ejection rail.

[0013] Finally, the shuttle drives the aircraft to reach the designed catapult takeoff speed, the shuttle contacts the deceleration device at the end of the catapult guide rail, the shuttle speed slows down, the aircraft separates from the shuttle and takes off.

[0014] The present invention utilizes a hydraulic-electric effect generator (HEGE) as the launch power source. The HEGEs are symmetrically mounted at the launch rail's starting point and along its extension. They pull and propel the aircraft's shuttle within the launch rail. High-voltage, high-power pulse currents trigger discharges in the liquid gap within the HEGE, causing the liquid to instantly and violently vaporize and plasmatize, generating a high-speed shock wave with a pressure exceeding hundreds of megapascals. This shock wave is then transmitted through the open end of the HEGE tube into the launch rail, propelling the shuttle within the rail to glide the aircraft at high speed along the rail's extension, achieving catapult launch. Compared to traditional steam catapults, the system eliminates the need for high-temperature, high-pressure steam storage tanks, resulting in a smaller size and higher energy efficiency. Compared to electromagnetic catapults, the system eliminates the need for separate cooling designs for the excitation circuit and permanent magnets, eliminating the need for complex excitation circuits and timing control. This results in a low-complexity system, a long service life, ease of use and maintenance, and low cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings described herein are used to provide a further understanding of this specification and constitute a part of this specification. The exemplary embodiments and descriptions of this specification are used to explain this specification and do not constitute an improper limitation of this specification.

[0016] In the picture:

[0017] Figure 1 It is a schematic diagram of the composition of the present invention;

[0018] Figure 2 This is a lower right rear view of the ejection guide rail of the present invention, viewed from the horizontal center plane;

[0019] Figure 3 This is a lower right rear view of the ejection guide rail of the present invention, viewed from a vertical center plane;

[0020] Figure 4 It is a schematic diagram of the water generator plugging cover of the present invention.

[0021] Among them, 1 is the ejection guide rail; 2 is the liquid-electric effect generator; 21 is the generator cover; 211 is the discharge electrode; 212 is the liquid inlet; 213 is the power supply end; 3 is the high-power pulse power supply; 4 is the liquid supply device; 5 is the shuttle. DETAILED DESCRIPTION

[0022] To make the purpose, technical solutions, and advantages of this specification more clear, the technical solutions of this application will be clearly and completely described below in conjunction with the specific embodiments of this application and their corresponding drawings. It is obvious that the embodiments described are only part of the embodiments of this specification, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this document.

[0023] The following combination Figures 1 to 4 , a catapult system based on the hydroelectric effect is described in detail:

[0024] like Figure 1 As shown, it is a ejection system based on the electrohydraulic effect, including an ejection guide rail 1, an electrohydraulic effect generator 2, a high-power pulse power supply 3, a liquid supply device 4, and a shuttle 5. The electrohydraulic effect generator 2 is fixedly installed at the starting end of the ejection guide rail 1 and symmetrically on both sides of the ejection guide rail 1 in the extension direction. The shuttle 5 is embedded in the ejection guide rail 1 and can slide freely along the extension direction of the ejection guide rail 1. The electrohydraulic effect generator 2 is a tubular object equipped with a liquid level sensor and a generator cover 21. One end of the opening is located on the inner side of the ejection guide rail 1. The generator cover 21 is used to In order to seal the tube body and ensure that liquid can be stored in the tube body, the generator cover 21 is located on the inner part of the tube body and is equipped with a pair of discharge electrodes 211. The discharge electrodes 211 pass through the generator cover 21 and are connected to the outer power supply end 213. The liquid replenishing port 212 runs through the inside and outside of the generator cover 21 and is used to replenish liquid into the electrohydraulic effect generator 2; the high-power pulse power supply 3 is connected to the power supply end 213 on each electrohydraulic effect generator 2 through a cable; the liquid supply device 4 is connected to the liquid replenishing port 212 on each electrohydraulic effect generator 2 through a pipeline.

[0025] Furthermore, the high-power pulse power supply 3 can output high-voltage and high-power pulse current to each electrohydraulic effect generator 2 through the power supply terminal 213 on the cable and the generator cover 21 according to the set timing.

[0026] Furthermore, the liquid supply device 4 can replenish the working fluid through the pipeline and the liquid replenishing port 212 on the generator plug cover 21 when the liquid level of the liquid height sensor in the electrohydraulic effect generator 2 is lower than the set value.

[0027] Furthermore, the discharge electrode 211 in the electrohydraulic effect generator 2 generates an electrohydraulic effect with the liquid under the action of high-voltage and high-power pulse current, generating a high-speed jet of a gas-liquid mixture and forming a pressure of up to hundreds of MPa, which is transmitted to the ejection guide rail 1 through the open end of the tube body of the electrohydraulic effect generator 2.

[0028] Furthermore, a deceleration device is provided at the end of the ejection guide rail 1 to absorb the kinetic energy of the shuttle 5 and ensure that the shuttle 5 decelerates and stops at the end of the ejection guide rail 1 .

[0029] Furthermore, the shuttle 5 is designed with a hooking structure that matches the aircraft, which can hook the aircraft landing gear or other towable structures to tow the aircraft to slide.

[0030] Furthermore, the ejection speed can be increased by symmetrically adding the electrohydraulic effect generators 2 in pairs along the extension direction of the ejection guide rail 1 .

[0031] A method for using a catapult system based on a hydro-electric effect:

[0032] First, the shuttle 5 is hooked onto the landing gear of the aircraft or other towable structure, and the shuttle 5 is parked at the starting end of the ejection guide rail 1. The liquid supply device 4 injects liquid into each electrohydraulic effect generator 2 through the pipeline and the liquid filling port 212 on the generator cover 21, and the high-power pulse power supply 3 stores electrical energy.

[0033] Afterwards, the high-power pulse power supply 3 outputs high-voltage and high-power pulse current to the electrohydraulic effect generator 2 installed at the starting end of the ejection guide rail 1 through the power supply end 213 on the cable and the generator cover 21. The high-speed jet of gas-liquid mixture generated by the electrohydraulic effect generator 2 acts on the rear end of the shuttle 5, and the thrust generated causes the shuttle 5 to accelerate and glide on the ejection guide rail 1; during the sliding of the shuttle 5 on the ejection guide rail 1, the high-power pulse power supply 3 outputs high-voltage and high-power pulse current to the electrohydraulic effect generator 2 located on both sides of the ejection guide rail 1 in turn and in a timely manner through the power supply end 213 on the cable and the generator cover 21, ensuring that the high-speed jet of gas-liquid mixture generated by the electrohydraulic effect generator 2 symmetrically on both sides acts just on the rear end of the shuttle 5, driving the shuttle 5 to drive the aircraft to continuously accelerate along the ejection guide rail 1.

[0034] Finally, the shuttle 5 drives the aircraft to reach the designed catapult takeoff speed, the shuttle 5 contacts the deceleration device at the end of the catapult guide rail 1, the shuttle 5 slows down, and the aircraft separates from the shuttle 5 and takes off.

[0035] The present invention utilizes a hydraulic-electric effect generator (HEGE) as the launch power source. The HEGEs are symmetrically mounted at the launch rail's starting point and along its extension. They pull and propel the aircraft's shuttle within the launch rail. High-voltage, high-power pulse currents trigger discharges in the liquid gap within the HEGE, causing the liquid to instantly and violently vaporize and plasmatize, generating a high-speed shock wave with a pressure exceeding hundreds of megapascals. This shock wave is then transmitted through the open end of the HEGE tube into the launch rail, propelling the shuttle within the rail to glide the aircraft at high speed along the rail's extension, achieving catapult launch. Compared to traditional steam catapults, the system eliminates the need for high-temperature, high-pressure steam storage tanks, resulting in a smaller size and higher energy efficiency. Compared to electromagnetic catapults, the system eliminates the need for separate cooling designs for the excitation circuit and permanent magnets, eliminating the need for complex excitation circuits and timing control. This results in a low-complexity system, a long service life, ease of use and maintenance, and low cost.

[0036] The above description is merely a preferred embodiment of this specification and is not intended to limit this specification. Those skilled in the art will readily appreciate that this specification is susceptible to various modifications and variations. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this specification shall be within the scope of protection of this specification.

Claims

1. A catapult system based on the electrohydraulic effect, characterized by: The device comprises an ejection rail, an electrohydraulic effect generator, a high-power pulse power supply, a liquid supply device, and a shuttle. The electrohydraulic effect generator is fixedly mounted symmetrically at the starting end of the ejection rail and on both sides of the ejection rail in the extension direction. The shuttle is embedded in the ejection rail and can slide freely along the extension direction of the ejection rail. The high-power pulse power supply and the liquid supply device respectively provide the electrohydraulic effect generator with high-voltage and high-power pulse current and working liquid. The electrohydraulic effect generator utilizes the liquid input from the liquid supply device to stimulate the electrohydraulic effect under the action of the high-voltage and high-power pulse current input from the high-power pulse power supply, thereby generating a high-speed jet of a vapor-liquid mixture and forming a pressure of hundreds of MPa or more, which is transmitted to the ejection guide rail through the open end of the electrohydraulic effect generator tube; The electrohydraulic effect generator is a tubular object equipped with a liquid level sensor and a generator cover. One open end is located on the inner side of the ejection guide rail. The generator cover is used to seal the tube body to ensure that liquid can be stored in the tube body. The generator cover is located on the inner side of the tube body and is equipped with a pair of discharge electrodes. The discharge electrodes pass through the generator cover and are connected to the outer power supply end. The fluid replenishment port runs through the inside and outside of the generator cover and is used to replenish liquid into the electrohydraulic effect generator. The high-power pulse power supply is connected to the power supply end on each electrohydraulic effect generator through a cable, and the liquid supply device is connected to the fluid replenishment port on each electrohydraulic effect generator through a pipeline.

2. The ejection system based on the electrohydraulic effect according to claim 1, characterized in that: The high-power pulse power supply can output high-voltage and high-power pulse current to each electrohydraulic effect generator through the power supply end on the cable and the generator cover according to the set timing.

3. The ejection system based on the electrohydraulic effect according to claim 1, characterized in that: The liquid supply device can replenish the working medium liquid through the pipeline and the liquid replenishing port on the generator plug cover when the sensitive liquid level of the liquid level sensor in the liquid-electric effect generator is lower than the set value.

4. The ejection system based on the electrohydraulic effect according to claim 1, characterized in that: The end of the ejection guide rail is provided with a deceleration device, which can absorb the kinetic energy of the shuttle and ensure that the shuttle decelerates and stops at the end of the ejection guide rail.

5. The ejection system based on the electrohydraulic effect according to claim 1, characterized in that: The shuttle is designed with a hooking structure that matches the aircraft, which can hook the aircraft landing gear or other towable structures to tow the aircraft to slide.

6. The ejection system based on the electrohydraulic effect according to claim 1, characterized in that: The ejection speed, ejection capability and ejection smoothness can be increased by adding hydraulic-electric effect generators in pairs symmetrically along the extension direction of the ejection guide rail.

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