A combined electromagnetic and gas piston cylinder powered ejection device

Abstract

The present invention discloses a combined electromagnetic and gas-powered piston-cylinder catapult system, comprising a gas generator equipped with multiple liquid fuel pressure injection safety valves; an electronic igniter; a water inlet manifold connected between the gas generator and the thrust chamber; a thrust chamber connected to a launch tube via a low-pressure chamber; two launch tubes arranged in parallel, each containing a movable piston connected to a shuttle via a guide connection mechanism; a motor primary fixed between the two launch tubes, with stator core windings mounted on both sides of the motor primary, the stator core windings arranged symmetrically in a linear array with equal spacing within the motor primary; a motor secondary mover fixed below the shuttle and located between the stator core windings on both sides, generating thrust through electromagnetic induction with the stator core windings; and linear guides mounted on both sides and each of the upper ends of the motor primary. This invention reduces the power demand on aircraft carriers.

Description

Technical Field

[0001] The present invention belongs to the technical field of combined power ejection, in particular to an electromagnetic and gas-fired piston cylinder combined power ejection device. Background Art

[0002] Before taking off, the aircraft needs to accelerate and roll on the runway until it reaches a sufficient takeoff speed before it can leave the ground. In order to meet the short-distance takeoff requirements of the aircraft on an aircraft carrier, the aircraft needs to be assisted by catapult takeoff.

[0003] Aircraft currently launched from aircraft carriers worldwide typically utilize steam or electromagnetic catapults. Steam catapults convert high-temperature, high-pressure steam into thrust, launching the aircraft using a slide on a catapult track. Steam catapults are expensive, complex to design, manufacture, and install, and require significant maintenance. They also occupy significant space and consume significant amounts of fresh water. Furthermore, their open-loop control system means that once the launch valve is opened, there is no further control, limiting their continued development.

[0004] The electromagnetic catapult uses a linear motor, utilizing a strong current flowing through a coil to generate a magnetic field that propels the slide forward at high speed. The electromagnetic catapult system has an independent control system that monitors system operation and precisely controls the launch speed, ensuring more stable acceleration during launch. This reduces damage to the carrier's deck and increases reliability. Compared to traditional steam catapults, the electromagnetic catapult offers significant advantages in controllability, robustness, reliability, troubleshooting, military suitability, and manning. Because the electromagnetic catapult's maximum energy exceeds 122MJ, this requires high technical and efficient performance from the AC generator, forced energy storage device, linear synchronous linear motor, and high-power digital cycloconverter. Given my country's current situation, achieving these technical specifications and long-term reliability for the forced energy storage device may not be feasible in the near future. Summary of the Invention

[0005] The purpose of the present invention is to provide an electromagnetic and gas-powered piston-cylinder combined catapult device, that is, an electromagnetic and piston-cylinder gas-powered catapult device, to solve the problems of low efficiency, high maintenance cost and unadjustable power of current steam catapult devices. It can also solve the problem that the electromagnetic catapult system has high technical requirements for forced energy storage devices, thereby reducing the demand for electricity on aircraft carriers.

[0006] The technical solutions for achieving the purpose of the present invention are:

[0007] An electromagnetic and gas-fired piston-cylinder combined powered ejection device, comprising a liquid fuel pressure injection safety valve, a gas generator, a water inlet manifold, a thrust chamber, a low-pressure chamber, a linear guide rail, a motor primary, a stator core winding, a motor secondary, a shuttle, a tractor, and a launch tube;

[0008] The gas generator is provided with a plurality of liquid fuel pressure injection safety valves for injecting liquid propellant into the gas generator;

[0009] The gas generator is provided with an electronic igniter for igniting the liquid propellant to form a launch gas;

[0010] The water inlet manifold is connected between the gas generator and the thrust chamber and is used for injecting water to generate steam to increase the internal pressure;

[0011] The thrust chamber is connected to the launch tube through a low-pressure chamber, and the low-pressure chamber is used for gas expansion to adjust the thrust;

[0012] The two launching tubes are arranged in parallel and side by side. A movable piston is arranged in each launching tube, and the piston is connected to the shuttle through a guide connection mechanism.

[0013] A motor primary is fixed between the two launch tubes, and stator core windings are installed inside both sides of the motor primary. The stator core windings are arranged symmetrically in a linear array with equal spacing inside the motor primary; the motor secondary mover is fixed under the shuttle and located between the stator core windings on both sides, and is used to generate thrust through electromagnetic induction with the stator core windings;

[0014] Linear guides are installed on both sides of the upper end of the motor primary and on each part. The internal linear guides slide with the motor secondary mover. The linear guides on the left and right sides of the upper end support or guide the aircraft or load, and constrain the degrees of freedom of the load or aircraft other than the direction of travel.

[0015] Compared with the prior art, the present invention has the following significant advantages:

[0016] A combined electromagnetic and gas-powered catapult scheme, designed for steam or electromagnetic catapults, has been proposed. This scheme, a combined electromagnetic and gas-powered piston-cylinder catapult, significantly reduces the energy storage pressure on the electromagnetic catapult's energy storage elements, as well as the corresponding heat dissipation pressure caused by the large amount of energy dissipated. It also reduces the power loss and fresh water consumption of steam catapults on aircraft carriers. This system can control speed and acceleration throughout the entire catapult launch process, enabling rapid and continuous launches. It offers advantages such as high efficiency, high thrust density, minimal thrust fluctuation, and enhanced safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the overall structure of the present invention

[0018] Figure 2This is a schematic diagram of the dynamic magnet permanent magnet synchronous linear motor in the present invention

[0019] Figure 3 This is a schematic diagram of a single launch tube for a gas-fired ejection in the present invention.

[0020] Figure 4 Schematic diagram of the linear guide rail of the catapult in the present invention

[0021] Figure 5 This is a schematic diagram of the gas generator arrangement in the present invention.

[0022] Figure 6 This is a schematic diagram of the tractor of the catapult in the present invention

[0023] Figure 7 It is a flow chart of the ejection method in the present invention

[0024] In the figure: liquid fuel pressure injection safety valve 1, gas generator 2, water inlet manifold 3, thrust chamber 4, low-pressure chamber 5, linear guide 6, motor primary (stator track) 7, stator core winding 8, motor secondary (T-type mover) 9, shuttle 10, tractor 11, launch tube 12, guide connecting groove 13, power output arm 14. DETAILED DESCRIPTION

[0025] In order to help those skilled in the art better understand the technical solutions in this application, the technical solutions in the embodiments of this application are clearly and completely described below. Obviously, the described embodiments are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of this application.

[0026] like Figure 1-Figure 7 As shown, the present invention provides an electromagnetic and gas piston cylinder combined power ejection device, including a liquid fuel pressure injection safety valve 1, a gas generator 2, a water inlet manifold 3, a thrust chamber 4, a low-pressure chamber 5, a linear guide 6, a motor primary (stator track) 7, a stator core winding 8, a motor secondary mover (T-type mover) 9, a shuttle 10, a tractor 11, a launch tube 12, a guide connecting groove 13, and a power output arm 14.

[0027] Three liquid fuel pressure injection safety valves (1) are arranged in three equal parts around the circumference of each gas generator (2), increasing or decreasing the liquid propellant flow rate according to launch requirements. Each gas generator (2) has a 4:1 mass flow rate adjustment capability to meet launch requirements under different operating conditions. Multiple gas generators (2) are evenly distributed at the rear of the water inlet manifold (3).

[0028] There are multiple gas generators 2 arranged beside an electronic igniter for igniting a liquid propellant to form high-pressure and high-temperature emission gas. The water inlet manifold 3 is located at the front side of the gas generator and injects fresh water into it to cool the gas generated by high-pressure combustion and form steam to increase the internal pressure, pushing the piston forward.

[0029] The thrust chamber 4 and the low-pressure chamber 5 are arranged in sequence in front of the water inlet manifold 3 for the expansion of high-pressure gas and related thrust adjustment.

[0030] The launch tube 12 is located in front of the low-pressure chamber 5 and is arranged in parallel on both sides of the moving-magnet permanent magnet synchronous linear motor. A movable piston is arranged in each launch tube 12. The launch tube 12 is provided with a guiding connection groove 13. The piston is connected to the shuttle 10 through a power output arm 14. The power output arm 14 is in sliding fit with the guiding connection groove 13. A sealing steel belt is arranged in the guiding connection groove 13 for dynamically sealing the launch tube 12. The piston transmits the generated thrust to the shuttle 10 through the power output arm 14 to push the load or the aircraft forward.

[0031] The permanent magnet synchronous linear motor consists of a motor primary 7, a stator core winding 8, and a motor secondary (T-shaped mover) 9. The motor primary 7 is of a "U" shape and is fixed between the two launch tubes 12. The stator core winding 8 is installed inside the bilateral sides of the motor primary 7, and the stator core windings 8 are symmetrically arranged in a linear equidistant array on both sides inside it. The motor secondary mover 9 and the slide-type shuttle 10 are made in the form of slides and are embedded in the stator of the linear motor. The motor secondary mover 9 is a permanent magnet, and a magnetic steel is installed on it for electromagnetic induction with the stator core winding 8 to generate thrust. Linear guide rails 6 are installed on the upper left and right sides and each part of the stator track 7. The internal linear guide rails 6 are in sliding fit with the motor secondary mover 9. The linear guide rails 6 on the upper left and right sides play a role in supporting or guiding the aircraft or the load and restrict the degrees of freedom other than the shooting direction of the load or the aircraft. A tractor 11 is fixedly connected to the shuttle 10. The tractor 11 is a connecting device between the ejection device and the aircraft landing gear for pulling and accelerating during takeoff. The motor system of the electromagnetic ejection and the piston in the launch tube are combined through the power output arm 14 and are connected to the aircraft through the tractor 11 to drive the aircraft forward.

[0032] The electromagnetic and gas-powered piston-cylinder combined catapult system of the present invention operates as follows: Before an aircraft takes off, the aircraft carrier's own power supply stores enough energy for the electric motor to launch the aircraft through a forced energy storage device. The power regulation subsystem and the regulation control subsystem control the permanent magnet synchronous linear motor to launch the aircraft within a specified time. Simultaneously, a gas generator uses an electronic igniter to electrically ignite the liquid propellant, causing combustion and pressure generation. Simultaneously, a water inlet manifold 3 begins spraying water directly in front of the gas generator to cool the gas and generate steam, which boosts the pressure and accelerates the piston and linear motor rotor. When the pressure in the launch tube changes, the servo valve replenishes or reduces the amount of liquid propellant and water spray to ensure the required pressure for launch. A water brake cylinder (not shown in the present invention) is located in front of the launch tube 12. After the aircraft is launched, the water brake cylinder acts on the pistons of the dual launch tubes, decelerating the permanent magnet synchronous linear motor rotor and piston to zero. After this, the reverse electromagnetic force of the linear motor returns the rotor and piston to their original position, ready for the next launch.

[0033] The above description contains the preferred embodiments of the present invention. This is to illustrate the technical features of the present invention in detail and is not intended to limit the invention to the specific forms described in the embodiments. Other modifications and variations based on the main content of the present invention without departing from the principles of the present invention are also protected by this patent. The main content of the present invention is defined by the claims, not by the detailed description of the embodiments.

Claims

1. An electromagnetic and gas piston cylinder combined power ejection device, characterized in that: It includes liquid fuel pressure injection safety valve, gas generator, water inlet manifold, thrust chamber, low-pressure chamber, linear guide rail, motor primary, stator core winding, motor secondary, shuttle, tractor, and launch tube; The gas generator is provided with a plurality of liquid fuel pressure injection safety valves for injecting liquid propellant into the gas generator; The gas generator is provided with an electronic igniter for igniting the liquid propellant to form a launch gas; The water inlet manifold is connected between the gas generator and the thrust chamber and is used for injecting water to generate steam to increase the internal pressure; The thrust chamber is connected to the launch tube through a low-pressure chamber, and the low-pressure chamber is used for gas expansion to adjust the thrust; The two launching tubes are arranged in parallel and side by side. A movable piston is arranged in each launching tube, and the piston is connected to the shuttle through a guide connection mechanism. A motor primary is fixed between the two launch tubes, and stator core windings are installed inside both sides of the motor primary. The stator core windings are arranged symmetrically in a linear array with equal spacing inside the motor primary; the motor secondary mover is fixed under the shuttle and located between the stator core windings on both sides, and is used to generate thrust through electromagnetic induction with the stator core windings; Linear guides are installed on both sides of the upper end of the motor primary and on each part. The internal linear guides slide with the motor secondary mover. The linear guides on the left and right sides of the upper end support or guide the aircraft or load, and constrain the degrees of freedom of the load or aircraft other than the direction of projection; The guide connection mechanism includes a power output arm and a guide connection groove; a guide connection groove is provided on the launch tube, the piston is connected to the shuttle through the power output arm, the power output arm and the guide connection groove are slidably matched, and a sealing steel belt is provided in the guide connection groove for dynamically sealing the launch tube. The piston transmits the thrust generated to the shuttle through the power output arm.

2. The electromagnetic and gas piston cylinder combined powered ejection device according to claim 1, characterized in that: The liquid fuel pressure injection safety valves are evenly distributed on the circumference of the gas generator.

3. The electromagnetic and gas piston cylinder combined powered ejection device according to claim 1, characterized in that: The gas generators are evenly distributed at the tail end of the water inlet manifold.

4. The electromagnetic and gas piston cylinder combined powered ejection device according to claim 1, characterized in that: The secondary rotor of the motor is a permanent magnet.

5. The electromagnetic and gas piston cylinder combined powered ejection device according to claim 1, characterized in that: A water brake cylinder is arranged in front of the launch tube.

6. The electromagnetic and gas piston cylinder combined powered ejection device according to claim 1, characterized in that: A tractor is fixed on the shuttle, which serves as a connecting device between the catapult device and the aircraft landing gear, and is used to pull and accelerate takeoff.

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