Aircraft pneumatic ejection system and control method

Abstract

The invention discloses an aircraft pneumatic catapulting system and a control method, the aircraft pneumatic catapulting system comprises a catapulting machine, a power mechanism, a reset mechanism, a brake mechanism, a launch control system and a catapulting mechanism, the catapulting mechanism comprises a launch platform, an air cylinder, a dragging vehicle, a movable piston and a traction device; the power mechanism comprises a carbon dioxide liquid storage tank, a filling machine, a phase change device, a first electromagnetic valve, an energy storage tank, a second electromagnetic valve and a servo control valve which are sequentially connected through a high-pressure pipeline. Supercritical carbon dioxide in the storage tank is heated to generate phase change expansion, generated high-pressure gas enters the ejection mechanism to drive the ejection mechanism to eject an aircraft, and the aircraft ejection device has the technical capabilities of being wide in energy controllable range, accurate and controllable in ejection force, high in maneuverability, capable of taking off in a short distance and capable of rapidly and continuously ejecting medium and large aircrafts.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft ejection technology, in particular to an aircraft pneumatic ejection system and control method. BACKGROUND

[0002] The aircraft pneumatic ejection technology has developed so far, and is currently more applied to small aircraft, and is rarely applied to medium and large aircraft. The technical bottlenecks affecting the application range are as follows: the energy output of the pneumatic ejection device is limited by the storage amount of compressed air, and cannot provide sufficient take-off power for medium and large aircraft; and the ejection frequency and efficiency are limited after each ejection, and the aircraft cannot be ejected continuously. In view of the above technical bottleneck problems restricting the development and application of the aircraft pneumatic ejection technology, the prior art has no effective solution. SUMMARY

[0003] In order to solve the defects existing in the prior art, the present application provides an aircraft pneumatic ejection system and control method based on the principle of carbon dioxide phase change expansion work, which solves the problems of insufficient energy storage of the aircraft pneumatic ejection device and long energy storage time in the prior art.

[0004] The technical scheme of the present application: an aircraft pneumatic ejection system, comprising: An ejection mechanism, the ejection mechanism comprising a launch platform, a cylinder, a tow car, a moving piston, a traction device, the cylinder being located inside the launch platform, the moving piston being located in the cylinder, the surface of the launch platform being provided with a guide rail, the tow car moving along the launch platform through the guide rail, the moving piston being connected with the tow car through the traction device and providing power for the tow car; A power mechanism, the power mechanism comprising a carbon dioxide storage tank, a filling machine, a phase change device, a first electromagnetic valve, an energy storage tank, a second electromagnetic valve, and a servo control valve connected in sequence through a high-pressure pipeline, the end of the high-pressure pipeline being connected with the cylinder; A reset mechanism, the reset mechanism comprising a reset car and a driving device, under the driving of the driving device, the reset car reciprocates along the guide rail and pushes the tow car to return from the tail end of the launch platform to the starting end of the launch platform; A brake mechanism, the brake mechanism being used for braking the tow car; A control system, the control system collecting state parameters of each component of the aircraft pneumatic ejection system as a criterion for work, and executing a control program.

[0005] In one embodiment, the traction device includes a first fixed pulley, a second fixed pulley, and a traction rope. The first fixed pulley is installed at the starting end of the launch platform, the second fixed pulley is installed at the tail end of the launch platform, and the traction rope passes around the surfaces of the first and second fixed pulleys, connecting the moving piston to the tow vehicle.

[0006] In one embodiment, the cylinder is provided with an air inlet and an air outlet. The high-pressure pipeline of the power mechanism is connected to the air inlet to provide power to the cylinder. The air outlet is provided with a high-pressure pipeline and a third solenoid valve. A buffer spring is provided inside the cylinder.

[0007] In one embodiment, the towing vehicle is equipped with a towing interface and a locking and releasing mechanism. The towing vehicle supports and propels the aircraft to accelerate along the guide rail of the launch platform through the towing interface, and the towing vehicle locks and releases the aircraft through the locking and releasing mechanism.

[0008] In one embodiment, the driving device includes a drive motor and a reducer, wherein the drive motor is electrically connected to the power control system and executes commands from the power control system.

[0009] In one embodiment, the braking mechanism is located at the tail end of the launch platform. The braking mechanism includes a hydraulic pump, a brake caliper, brake pads, a jack, and a return spring. The hydraulic pump is electrically connected to the launch control system and is connected to the jack through a high-pressure pipeline. Under the action of the hydraulic pump, the jack pushes the brake caliper and brake pads to brake the tow vehicle. When the hydraulic pump stops working, the brake caliper and brake pads are released and reset under the action of the return spring.

[0010] In one embodiment, the starting end of the launch platform is provided with a first limit switch, a force sensor, and an electromagnet, and the tail end of the launch platform is provided with a second limit switch. The first limit switch, the second limit switch, and the force sensor are electrically connected to the launch control system. One end of the force sensor is connected to the launch platform, and the other end of the force sensor is connected to the electromagnet. The towing vehicle contacts the first limit switch and the electromagnet before being launched, and the reset vehicle contacts the second limit switch before being reset.

[0011] In one embodiment, the launch platform is provided with a leveling mechanism at its bottom.

[0012] Based on the same inventive concept, this invention also proposes a control method for an aircraft aerodynamic catapult system, comprising the following steps: S1. Enter the aircraft number and call the corresponding control program for ejection energy requirements; S2. Carbon dioxide from the carbon dioxide storage tank is injected into the phase change device through the filling machine, and then enters the energy storage tank through the first solenoid valve; S3. When the temperature and pressure of carbon dioxide in the storage tank reach the set range, the heating device stops heating, the filling machine stops filling liquid, and the first solenoid valve closes. S4. Confirm that the towing vehicle and the reset vehicle are located at the starting end and the tail end of the launch platform, respectively; that the force sensor has obtained the thrust within the set range and the hydraulic pump is powered on and pressurized; start the second solenoid valve and servo control valve to charge the cylinder; and move the piston and towing vehicle to drive the aircraft to launch pneumatically. S5. After the aircraft is ejected, close the second solenoid valve and the servo control valve to reset.

[0013] In one embodiment, the reset process in step S5 first involves depressurizing the hydraulic pump, energizing the third solenoid valve to release air from the cylinder, driving the reset vehicle to push the tow truck back to the starting end of the launch platform, then driving the reset vehicle back to the tail end of the launch platform, and finally closing the third solenoid valve.

[0014] This invention heats supercritical carbon dioxide in a storage tank, causing it to undergo a phase change and expand. The resulting high-pressure gas enters the catapult mechanism, which then drives the catapult to launch the aircraft. This invention possesses the technical capabilities of a wide range of controllable energy, precise and controllable launch force, high maneuverability, short-distance takeoff, and rapid and continuous launch of medium and large aircraft. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the aircraft aerodynamic catapult system according to an embodiment of the present invention; Figure 2 This is a schematic diagram showing the correspondence between the main logic and the device control logic flow in an embodiment of the present invention; Figure 3 This is a schematic diagram of the main logic flow in an embodiment of the present invention; In the diagram: 1-Ejection mechanism, 2-Carbon dioxide storage tank, 3-Filling machine, 4-Phase change device, 5-First solenoid valve, 6-Storage tank, 7-Second solenoid valve, 8-High-pressure pipeline, 9-Servo control valve, 10-Third solenoid valve, 11-Hydraulic pump, 12-Control cable, 13-Power supply, 14-Launch control system, 101-Launch platform, 102-Force sensor, 103-First limit switch, 104-Electromagnet, 105-Trailer, 106-Launch guide rail, 107-Brake mechanism, 108-Reset guide rail, 109-Reset vehicle, 110-Second limit switch, 111-Drive device, 112-Leveling mechanism, 113-First fixed pulley, 114-Buffer spring, 115-Moving piston, 116-Cylinder, 117-Traction rope, 118-Second fixed pulley, 119-Reset rope, 120-Third fixed pulley. Detailed Implementation

[0016] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0017] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the specification of this invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "or / and" as used herein includes any and all combinations of one or more of the associated listed items.

[0018] like Figure 1 As shown, this embodiment discloses an aircraft aerodynamic catapult system based on the principle of carbon dioxide phase change expansion, including a catapult, a power mechanism, a reset mechanism, a braking mechanism, and a launch control system.

[0019] In this embodiment, the ejection mechanism 1 includes a launch platform 101, a cylinder 116, a tow 105, a moving piston 115, and a traction device. The cylinder 116 is located inside the launch platform 101, and the moving piston 115 is located inside the cylinder 116. The surface of the launch platform 101 is provided with a launch guide rail 106. The tow 105 moves along the launch platform 101 via the launch guide rail 106. The moving piston 115 is connected to the tow 105 via the traction device and provides power to the tow 105.

[0020] The launch platform 101 is equipped with a leveling mechanism 112 at its bottom, which adaptively adjusts to contact the ground.

[0021] In this embodiment, the towing vehicle 105 is equipped with a towing interface, a locking and releasing mechanism, a magnetic interface, a reset interface, and a brake plate. The towing vehicle 105 supports and pushes the aircraft along the launch rail 106 of the launch platform 101 to accelerate. The towing vehicle 105 locks and releases the aircraft through the locking and releasing mechanism. The towing vehicle 105 is connected to the reset vehicle 109 through the reset interface.

[0022] In this embodiment, the traction device includes a first fixed pulley 113, a second fixed pulley 118, and a traction rope 117. The first fixed pulley 113 is installed at the starting end of the launch platform 101, the second fixed pulley 118 is installed at the tail end of the launch platform 101, and the traction rope 117 passes around the surfaces of the first fixed pulley 113 and the second fixed pulley 118, connecting the moving piston 115 and the towing vehicle 105.

[0023] In this embodiment, the power mechanism includes a carbon dioxide storage tank 2, a filling machine 3, a phase change device 4, a first solenoid valve 5, an energy storage tank 6, a second solenoid valve 7, and a servo control valve 9, which are connected in sequence through a high-pressure pipeline 8.

[0024] In this embodiment, the first solenoid valve 5, the second solenoid valve 7, and the third solenoid valve 10 are respectively connected to the power generation and control system 14 through the measurement and control cable 12. During operation, they execute the commands of the power generation and control system 14 to control the opening and closing of the high-pressure pipeline 8.

[0025] In this embodiment, the carbon dioxide storage tank 2 is equipped with a shut-off valve and a safety valve, and the gas inside the tank is carbon dioxide.

[0026] In this embodiment, the filling machine 3 includes a filling pump, an inlet solenoid valve, an outlet solenoid valve, an exhaust valve, a safety valve, a temperature sensor, a pressure sensor, a flow meter, a control console, etc. The filling machine 3 is connected to the control system 14 through a measurement and control cable 12. During operation, the filling machine 3 executes the commands of the control system 14 to control the start and stop of the filling pump, the inlet and outlet solenoid valves, the exhaust valve, and the control console, regulates the filling pressure and flow rate, and feeds back the pressure, temperature, flow rate and other parameters to the control system 14 in real time.

[0027] In this embodiment, the phase change device 4 includes an electric heating device, pipelines, temperature sensors, pressure sensors, a heating controller, a heat insulation protective cylinder, a safety valve, etc. The phase change device 4 is connected to the power generation and control system 14 through a measurement and control cable 12. During operation, it executes the commands of the power generation and control system 14, controls the start and stop of the heating controller, regulates the heating power, the temperature and pressure of the gas inside the device, and feeds back the temperature, pressure and other parameters to the power generation and control system 14 in real time.

[0028] In this embodiment, the energy storage tank 6 includes a high-pressure insulated gas tank, a heating device, a heating controller, a temperature sensor, a pressure sensor, a safety valve, etc. The heating device is installed inside the high-pressure insulated gas tank. The energy storage tank 6 is connected to the power generation and control system 14 through a measurement and control cable 12. During operation, the energy storage tank 6 executes the commands of the power generation and control system 14 to control the start and stop of the heating controller, regulate the heating power, the temperature and pressure of the gas inside the tank, and feed back the temperature, pressure and other parameters to the power generation and control system 14 in real time.

[0029] In this embodiment, the cylinder 116 is divided into three parts from right to left: acceleration section, depressurization section, and tail section, corresponding to the three movement states of the moving piston 115. The acceleration section is equipped with a buffer spring 114, an air inlet, and an exhaust port. The air inlet is connected to the servo control valve 9 through a high-pressure pipeline 8, and the exhaust port is connected to the third solenoid valve 10 through a high-pressure pipeline 8.

[0030] In this embodiment, the servo control valve 9 is connected to the launch control system 14 through the measurement and control cable 12. The servo control valve 9 executes the program commands of the launch control system 14 to control the real-time opening of the valve, thereby regulating the gas flow and pressure in the pipeline, so that the gas pressure in the acceleration section of the cylinder 116 of the ejection mechanism 1 remains balanced and stable, providing sufficient driving force for the moving piston 115 to drive the tow tractor 105 to eject the aircraft.

[0031] In this embodiment, the reset mechanism includes a reset carriage 109, a drive device 111, a third fixed pulley 120, a reset guide rail 108, and a reset rope 119. The third fixed pulley 120 is disposed at the starting and ending ends of the launch platform 101. The reset guide rail 108 is disposed on the surface of the launch platform 101. The reset rope 119 passes over the surface of the third fixed pulley 120 and connects the reset carriage 109 and the drive device 111. Driven by the drive device 111, the reset carriage 109 reciprocates along the reset guide rail 108. The drive device 111 includes a drive motor and a reducer, and is connected to the launch control system 14 via a measurement and control cable 12. It executes the commands of the launch control system 14 and controls the start, stop, forward and reverse rotation of the drive motor.

[0032] In this embodiment, the starting end of the launch platform 101 is equipped with a first limit switch 103, a force sensor 102, and an electromagnet 104, while the tail end of the launch platform 101 is equipped with a second limit switch 110. The first limit switch 103 and the second limit switch 110 are respectively connected to the launch control system 14 via a control cable 12, and provide real-time feedback of the circuit connection and disconnection status to the launch control system 14. One end of the force sensor 102 is connected to the launch platform 101, and the other end is connected to the electromagnet 104, used to test the thrust of the aircraft during the pre-launch preparation. The force sensor 102 is connected to the launch control system 14 via a control cable 12, and provides real-time feedback of the force parameters to the launch control system 14.

[0033] Before being launched, the tow 105 contacts the first limit switch 103 and the electromagnet 104. Before the reset 109 pushes the tow 105 to reset, it contacts the second limit switch 110 at the reset 109 origin (tail end of the launch platform 101).

[0034] The magnetic force of electromagnet 104 must be greater than the initial thrust of the aircraft. During the preparation and ejection process, electromagnet 104 remains in a continuous working state, using magnetic force to hold the magnetic interface of tow 105, thereby achieving the fixed force lock of tow 105. At the moment of ejection, under the thrust of tow 105, it breaks free from tow 105.

[0035] In this embodiment, the traction rope 117 and the reset rope 119 are made of ultra-high molecular weight polymer braided rope, which is resistant to tension, drag, sun exposure, moisture, and corrosion.

[0036] In this embodiment, the braking mechanism 107 is located at the tail end of the launch platform 101. The braking mechanism 107 includes a hydraulic pump 11, a brake caliper, brake pads, a jack, and a return spring. The hydraulic pump 11 is connected to the launch control system 14 via a control cable 12, executes the commands of the launch control system 14, controls the start and stop of the hydraulic pump 11, and provides real-time feedback of the pump pressure to the launch control system 14. The hydraulic pump 11 is connected to the jack via a high-pressure pipeline 8. Under the action of the hydraulic pump 11, the jack pushes the brake caliper and brake pads to brake the tow vehicle 105. When the hydraulic pump 11 stops working, the brake caliper and brake pads are released and reset under the action of the return spring. During the release of the brake, the brake fluid pressure in the hydraulic pump 11 drops to 0, and the braking mechanism 107 is released and reset.

[0037] In this embodiment, the launch control system 14 includes a test module and a control module. It collects the status parameters of each component of the aircraft aerodynamic catapult system, executes the working procedure according to the criteria for preparation, catapult operation, and post-catapult takeoff operation, and analyzes and obtains the results. The launch control system 14 is powered by the power supply 13.

[0038] Based on the same inventive concept, this invention also provides a control method for an aircraft aerodynamic catapult system based on the principle of carbon dioxide expansion and work. This method controls the actions of each component of the aircraft aerodynamic catapult system during the catapult and repositioning processes via a launch control system, and includes the following steps: S1. Enter the aircraft number and call the corresponding control program for ejection energy requirements; S2. Carbon dioxide in carbon dioxide storage tank 2 is injected into phase change device 4 through filling machine 3 and enters energy storage tank 6 through first solenoid valve 5; S3. When the carbon dioxide in the energy storage tank 6 undergoes a phase change due to heating, and the temperature and pressure reach the set range, the phase change device 4 stops heating, the filling machine 3 stops injecting liquid, and the first solenoid valve 5 closes. S4. Confirm that the towing vehicle 105 and the reset vehicle 109 are located at the starting end and the tail end of the launch platform 101 respectively, the force sensor 102 obtains the thrust reaching the set range and the hydraulic pump 11 is powered on and pressurized, start the second solenoid valve 7 and the servo control valve 9 to charge the cylinder 116, and the moving piston 115 and the towing vehicle 105 drive the aircraft to be pneumatically ejected. S5. After the aircraft is ejected, close the second solenoid valve 7 and the servo control valve 9 to reset.

[0039] In one embodiment, the reset process in step S5 first involves depressurizing the hydraulic pump 11, energizing the third solenoid valve 10 to release air from the cylinder 116, driving the reset vehicle 109 to push the tow vehicle 105 back to the starting end of the launch platform 101, then driving the reset vehicle 109 back to the tail end of the launch platform 101, and finally closing the third solenoid valve 10.

[0040] This invention heats supercritical carbon dioxide in a storage tank, causing it to undergo a phase change and expand. The resulting high-pressure gas enters the catapult mechanism, which then drives the catapult to launch the aircraft. This invention possesses the technical capabilities of a wide range of controllable energy, precise and controllable launch force, high maneuverability, short-distance takeoff, and rapid and continuous launch of medium and large aircraft.

[0041] The main logic of the control method corresponds to the ejection and reset processes in the equipment control logic. The corresponding content of the ejection process in the control method and equipment control logic is as follows: Figure 2 , Figure 3 And as shown in Table 1:

[0042] It should be noted that in this invention, "aircraft" is a general term for both "unmanned aerial vehicles" and "manned aircraft".

[0043] The phrase "different aircraft types with different numbers correspond to different ejection energy supply requirements" mentioned in the equipment control logic ejection process refers to the fact that different aircraft have different masses, ejection overloads, and ejection speeds, and therefore have different ejection energy supply requirements. The ejection energy supply requirements refer to the demand for the sum of the internal energy and pressure energy of carbon dioxide in the energy storage tank, which is essentially the demand for the temperature and pressure of the gas in the energy storage tank.

[0044] Based on the aircraft's mass and the requirements for ejection overload and ejection speed, a simulation model of the aircraft ejected by carbon dioxide phase change expansion was established. The simulation calculation and analysis yielded the corresponding relationship between the aircraft's mass, ejection overload, ejection speed and the temperature, pressure and servo control valve control curves of the energy storage tank carbon dioxide.

[0045] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An aircraft aerodynamic catapult system, characterized in that, include: The ejection mechanism includes a launch platform, a cylinder, a tow trolley, a moving piston, and a traction device. The cylinder is located inside the launch platform, and the moving piston is located inside the cylinder. The surface of the launch platform is provided with a guide rail. The tow trolley moves along the launch platform via the guide rail. The moving piston is connected to the tow trolley via the traction device and provides power to the tow trolley. The power mechanism includes a carbon dioxide storage tank, a filling machine, a phase change device, a first solenoid valve, an energy storage tank, a second solenoid valve, and a servo control valve, which are connected in sequence through a high-pressure pipeline. The end of the high-pressure pipeline is connected to the cylinder. A reset mechanism, comprising a reset carriage and a drive device, wherein the reset carriage reciprocates along the guide rail under the drive of the drive device, thereby pushing the tow vehicle back from the tail end of the launch platform to the starting end of the launch platform; A braking mechanism for braking the tractor; The launch control system collects the status parameters of each component of the aircraft's aerodynamic catapult system as a criterion for operation and executes the control program.

2. The aircraft pneumatic catapult system according to claim 1, characterized in that: The traction device includes a first fixed pulley, a second fixed pulley, and a traction rope. The first fixed pulley is installed at the starting end of the launch platform, and the second fixed pulley is installed at the tail end of the launch platform. The traction rope passes around the surfaces of the first and second fixed pulleys and connects the moving piston to the towing vehicle.

3. The aircraft pneumatic catapult system according to claim 1, characterized in that: The cylinder is provided with an air inlet and an air outlet. The high-pressure pipeline of the power mechanism is connected to the air inlet to provide power to the cylinder. The air outlet is provided with a high-pressure pipeline and a third solenoid valve. A buffer is provided inside the cylinder.

4. The aircraft pneumatic catapult system according to claim 1, characterized in that: The towing vehicle is equipped with a towing interface and a locking and releasing mechanism. The towing vehicle supports and propels the aircraft along the guide rail of the launch platform through the towing interface, and the towing vehicle locks and releases the aircraft through the locking and releasing mechanism.

5. The aircraft pneumatic catapult system according to claim 1, characterized in that: The drive device includes a drive motor and a reducer. The drive motor is electrically connected to the power control system and executes the commands of the power control system.

6. The aircraft pneumatic catapult system according to claim 1, characterized in that: The braking mechanism is located at the tail end of the launch platform. The braking mechanism includes a hydraulic pump, brake calipers, brake pads, a jack, and a return spring. The hydraulic pump is electrically connected to the launch control system and is connected to the jack through a high-pressure pipeline. Under the action of the hydraulic pump, the jack pushes the brake calipers and brake pads to brake the tow vehicle. When the hydraulic pump stops working, the brake calipers and brake pads are released and reset under the action of the return spring.

7. The aircraft pneumatic catapult system according to claim 1, characterized in that: The launch platform is equipped with a first limit switch, a force sensor, and an electromagnet at its starting end, and a second limit switch at its tail end. The first limit switch, the second limit switch, and the force sensor are electrically connected to the launch control system. One end of the force sensor is connected to the launch platform, and the other end of the force sensor is connected to the electromagnet. The towing vehicle contacts the first limit switch and the electromagnet before launch, and the reset vehicle contacts the second limit switch before reset.

8. The aircraft pneumatic catapult system according to claim 1, characterized in that: The launch platform is equipped with a leveling mechanism at its bottom.

9. A control method for an aircraft aerodynamic catapult system as described in any one of claims 1-8, characterized in that, Includes the following steps: S1. Enter the aircraft number and call the corresponding control program for ejection energy requirements; S2. Carbon dioxide from the carbon dioxide storage tank is injected into the phase change device through the filling machine, and then enters the energy storage tank through the first solenoid valve; S3. When the temperature and pressure of carbon dioxide in the energy storage tank reach the set range, the phase change device stops heating, the filling machine stops injecting liquid, and the first solenoid valve closes. S4. Confirm that the towing vehicle and the reset vehicle are located at the starting end and the tail end of the launch platform, respectively; that the force sensor has obtained the thrust within the set range and the hydraulic pump is powered on and pressurized; start the second solenoid valve and servo control valve to charge the cylinder; and move the piston and towing vehicle to drive the aircraft to launch pneumatically. S5. After the aircraft is ejected, close the second solenoid valve and the servo control valve to reset.

10. The control method for an aircraft aerodynamic catapult system according to claim 9, characterized in that: The reset process in step S5 involves first depressurizing the hydraulic pump, energizing the third solenoid valve to release air from the cylinder, driving the reset vehicle to push the tow truck back to the starting end of the launch platform, then driving the reset vehicle back to the tail end of the launch platform, and finally closing the third solenoid valve.

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