RU2497725C1 - Aircraft launching catapult - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly to drone launching catapult. Proposed catapult comprises guide 1 with carriage 2, carriage booster including power air cylinder 5 with piston 6 and cable 12 with pulleys 11. One end of said cable is connected with said carriage supporting the device for coupling with the drone while brake 3 is fitted at the guide. Carriage start position lock is arranged at said guide and carriage. Aforesaid booster comprises compressed gas source 17 and receiver. Controller allows inhibiting the compressed gas feed into cylinder unless the carriage contact with aforesaid brake. Stoppers are removed before said contact. Stoppers stay in contact with drone bottom surfaces while ledges and stoppers interact with mate power elements of the drone. Acceleration of carriage with drone created by the booster exceeds that generated by drone engine.

EFFECT: reliable launching.

10 dwg

Description

The invention relates to aircraft, in particular to devices for take-off unmanned aerial vehicles (UAVs).

A device for launching unmanned aerial vehicles is known (see UK patent application No. 2132577, IPC B64F 1/06, 07/11/1984), containing an inclined guide, a trolley on which a UAV is installed, which is moved along the guide by an accelerating device, an accelerating device, including a flywheel driven by an electric motor, a clutch system and the transmission of mechanical energy from the flywheel to the trolley.

Before starting with the help of a docking device, the aircraft is connected to the carriage located on the catapult in the starting position, and after its acceleration by the booster device to the required speed, the aircraft is disconnected from the carriage and the carriage is braked.

The disadvantage of this device is the limited reliability due to the large number of mechanical links.

Known catapult for launching aircraft (see Ukrainian patent No. 65062 A, IPC B64F 1/00, 03/15/2004), adopted as a prototype. The device comprises a housing, guides with a trolley, a system for accelerating the trolley along the guides, the housing is made as a cylindrical container with compressed gas with guides installed on it with a trolley, a power cylinder with a piston, automatic compressed gas supply, cable system, chain hoist, and a UAV mounting system on the trolley brake shock absorbers.

The device operates as follows. The catapult is refueled with compressed gas at the station. After arriving in the launch area, the catapult is transferred to its working position. The aircraft is mounted and mounted on a trolley mounted on rails. The systems that ensure the start are checked, the UAV engine is started, and the operating pressure is supplied from the compressed gas tank to the power cylinder with a piston interacting via a cable-block system with a trolley. After a set starting speed, the trolley is in contact with shock absorbers, while the attachment points of the UAV on the trolley are revealed, the device takes off. Returning the cart to its original position, you can start the next UAV. After one refueling of the tank, several UAVs can be launched.

The disadvantages of the prototype include the low reliability of the takeoff of the aircraft, due to the possibility of its contact with the elements of the catapult and the cart, resulting from their relative relative motion at close distances from each other, which can lead to touching the tail of the UAV and resulting in damage to the aircraft .

The launch of several UAVs after a single refueling of the vessel with compressed gas leads to a decrease in pressure in the vessel as the gas is consumed, and, accordingly, to the instability of the dynamic and kinematic parameters of the acceleration of the cart with the UAV, which, in turn, can cause the aircraft to break at the start.

The absence of a lock on the starting position of the trolley with an adjustable calibrated pull-out force leads to uncertainty about the moment the trolley starts to move and the acceleration parameters are unstable, since with this design the moment the trolley starts to start depends on the starting mass and thrust of the UAV power unit (for example, a propeller engine or a turbojet engine), climatic environmental conditions, the state of the contacting elements of the cart and the guide, and a number of other factors.

Since the supply of compressed gas to the power cylinder does not stop during the movement of the trolley, high shock overloads of the trolley occur at the moment of contact with shock absorbers, these overloads can lead to breakage of the trolley.

The use of a cable system with a chain hoist is practically unacceptable in the case of launching aircraft with a starting weight of more than 15 ... 20 kilograms, due to the large number of cable bends with long lines of contact with the blocks (up to 0.5 circles) at high transmitted force pulses and accelerations. Which, on the one hand, with small sections of the cable leads to its breakage, and on the other hand, with an increase in the section, to a sharp decrease in the efficiency due to the energy consumption for the deformation of the cable.

Disclosure of the UAV attachment points on the carriage after contact with shock absorbers leads to the transfer of shock overloads from the carriage to the aircraft, which under certain conditions can lead to its failure.

The objective of the invention is to increase the reliability of the launch of the aircraft, increase the resource of the device, reduce the cost of its operation, expand its functionality.

The technical result of the invention is the development of a catapult design for takeoff of an aircraft having a system for separating the UAV from the cart, eliminating the possibility of damage to the apparatus; well-defined parameters for accelerating a cart with a UAV, the ability to launch a UAV with a large starting weight and traction of a power plant, a large number of UAV launches without refueling the device, reduced shock overloads when braking a truck, and increasing safety.

The specified technical result is achieved by the fact that in the catapult for take-off of an aircraft containing a guide with a trolley, an accelerating device of the trolley, including a power pneumatic cylinder with a piston and a cable with blocks, one end of the cable is connected to the trolley, a docking unit with an aircraft is mounted on the trolley , a brake device is installed on the guide, new is that on the guide and the trolley there is a device for fixing the starting position of the trolley with adjustable calibrated straining force The booster device contains a source of compressed gas and a receiver, a source of compressed gas is connected to the receiver through a valve device, a pressure gauge and an overpressure relief valve are installed on the receiver, a power pneumatic cylinder is connected to the receiver through an electro-pneumatic valve, the electro-pneumatic valve is controlled by a programmable controller, and a docking unit with the aircraft contains freely rotating roller fixed in the upper part of the cart symmetrically with respect to the vertical longitudinal plane of symmetry of the cart in an amount of at least four, as well as protrusions securing the aircraft in all degrees of freedom except for moving in the forward direction, retractable stoppers securing the aircraft from moving in the forward direction, the second end of the cable is fixed to the piston, while the controller provides the termination of the supply of compressed gas to the power pneumatic cylinder until the trolley contacts the brake device, the stops are removed until the trolley contacts the brake device, the rollers are in contact with the lower the surfaces of the aircraft, the protrusions and stoppers interact with the reciprocal power elements of the aircraft, the acceleration of the cart with the aircraft, created by the booster, exceeds the acceleration of the aircraft, created by its power plant.

The installation on the rail and carriage of the device for fixing the starting position of the carriage with an adjustable calibrated pull-out force makes it possible to ensure stable acceleration parameters of the carriage with the aircraft, and enables the UAV to be launched with various starting masses and thrusts of the power plant, regardless of the climatic conditions of the environment, the state of the contacting elements of the carriage and the guide , and other factors.

Introducing a separate compressed gas source and receiver into the booster device, connecting the compressed gas source to the receiver through a valve device, installing a pressure gauge and an overpressure relief valve on the receiver, communicating the power pneumatic cylinder with the receiver through an electro-pneumatic valve, controlling an electro-pneumatic valve from a programmable controller allows you to rigidly determine the acceleration parameters carts with UAVs, eliminate aircraft breakdowns at launch, provide a large number of UAV launches without dosing avki devices, increase security.

Providing the controller with the termination of the supply of compressed gas to the cylinder until the bogie is in contact with the brake device allows to reduce shock overloads when braking the bogie and to prevent its breakdown.

The design of the docking assembly with the aircraft, including at least four freely rotating rollers fixed in the upper part of the carriage symmetrically with respect to the vertical longitudinal plane of symmetry of the carriage, as well as protrusions that fix the aircraft in all degrees of freedom except for movement in the forward direction , retractable stoppers that fix the UAV from moving in the "forward" direction and are removed until the cart contacts the braking device, roller contacting UAV lower surfaces, and the interaction of the projections with counter stops power elements of the aircraft, the acceleration trolley UAV generated booster device exceeding the acceleration of the aircraft created by its propulsion system allows the aircraft to avoid breakage during startup.

Fastening the second end of the cable to the piston determines the design of the acceleration device with a minimum number of cable bends with contact lines with blocks less than half the circumference, which makes it possible to launch UAVs with a large starting mass without breaking the cable and reducing the efficiency.

The combination of structural elements, their relative position, the form of the elements and the relationship between them allow to ensure high reliability of the launch of the aircraft, a large resource of the device, reduce the cost of operation, expand the functionality of the device.

The essence of the invention is illustrated by drawings, where

- figure 1 - the device is in the initial state with an aircraft installed on it (the pneumatic system of the booster is not shown);

- figure 2 - the device is in its original state with an aircraft installed on it (top view);

- figure 3 - (remote element A) the spring block of the locking device starting position before the movement of the trolley;

- figure 4 - (remote element A) the spring block of the device for fixing the starting position after the start of the movement of the trolley (arrows indicate the direction of movement of the trolley and sliders);

- figure 5 - (remote element B) hinged bar device for fixing the starting position before the start of the movement of the trolley;

- 6 - (remote element B) hinged bar device for fixing the starting position after the start of the movement of the trolley (arrows indicate the direction of movement of the trolley and rotation of the hinged bar);

- Fig.7 - (remote element B) - node docking with an aircraft before the movement of the trolley (stopper extended);

- Fig. 8 - (remote element B) —the docking unit with the aircraft at the moment of contact of the truck with the brake device (the stopper is removed, the UAV rolls on rollers, the arrows show the direction of UAV movement and rotation of the rollers);

- Fig.9 - the device at the moment of contact of the truck with the brake device (the arrow shows the direction of movement of the UAV);

- figure 10 is a pneumatic diagram of a booster device.

The catapult includes a guide 1 with a trolley 2, a brake device 3 and an accelerating device.

The guide 1 is a square box mounted on the supports 4 in an inclined position, while the upper and lower longitudinal faces of the box are in a vertical plane.

A power pneumatic cylinder 5 with a piston 6 is installed inside the box.

In the lower part of the guide 1 there is a hinged bar 7 (Fig. 5) of the device for fixing the starting position of the carriage 2, as well as cables 8 with checks 9 (Fig. 7) for fixing the retractable stoppers 10 of the docking unit of the carriage with the aircraft. The stops 10 are held in extended position by checks 9 connected to the cables 8, the second ends of the cables are fixed on the guide 1.

In the upper part of the guide 1 is installed a brake device 3, in the case shown in figure 2, it is a rubber buffer. At the upper end of the guide also installed freely rotating blocks 11 for the cable 12.

The cart 2 is located on the guide 1 with the possibility of moving along it under the action of the accelerating device, equipped with a docking unit with an aircraft and a spring block 13 (Figs. 3, 4) of the device for fixing the starting position.

In the lower part of the trolley 2 there are two pairs of freely rotating rollers 14 with the possibility of rolling along two opposite sides of the guide 1, located in an inclined plane.

In the upper part of the trolley 2 there is a docking unit with an aircraft.

It consists (figure 4) of installed symmetrically with respect to the vertical longitudinal plane of symmetry of the trolley of freely rotating rollers 15, as well as two protrusions 16 and two retractable stoppers 10.

In the rear part of the trolley (Figs. 3, 4) a spring block 13 of the device for fixing the starting position of the trolley 2 is installed, consisting of two spring-loaded sliders with adjustable clamping force connected by a pin (positions are not shown in the drawings).

The accelerating device of the trolley 2 includes a power pneumatic cylinder 5 with a piston 6, a cable 12 with blocks 11, (see Fig. 10) a source of compressed gas 17, a receiver 18. A source of compressed gas is connected to the receiver through a valve device 19. A pressure gauge 20 is installed on the receiver and an overpressure relief valve 21. The power pneumatic cylinder 5 is in communication with the receiver through an electro-pneumatic valve 22. The electro-pneumatic valve 22 is controlled from a programmable controller 23.

The housing of the power pneumatic cylinder 5 is made in the form of a cylindrical pipe with closed ends, in one of which a hole for the cable is made. The piston 6 is placed in the housing of the power pneumatic cylinder 5 with the possibility of movement along its longitudinal axis and the formation of a working chamber located on the side of the hole in the end of the housing of the power pneumatic cylinder.

The cable 12 is passed through an opening in the end face of the housing of the power pneumatic cylinder, covers blocks 11 mounted on the upper end of the guide 1, one end of the cable is connected to the carriage 2, and the second is fixed to the piston 6 along its axis.

The controller 23 of the electro-pneumatic valve 22 is programmed to stop the supply of compressed gas to the power pneumatic cylinder 5 at a certain point in time - until the bogie 2 contacts the braking device 3.

In addition, in order to improve braking conditions, the housing of the power pneumatic cylinder 5 can be equipped with drainage holes made in its side wall, while the dimensions and location of the drainage holes along the length of the power pneumatic cylinder are selected based on the condition of the cavity of the working chamber with the environment before the contact of the truck 2 with a brake device 3, as well as the conditions for the formation of a closed end face of a power pneumatic cylinder 5 when the piston 6 is displaced to it by a piston 6 that is closed in volume by the brake chamber.

The catapult works as follows.

Initially, the device is in the starting state shown in FIGS. 1, 2. The trolley 2 is located at the beginning of the guide 1 and is held by the locking device for starting position, consisting of a hinged bar 7 and a spring unit 13, on which the calibrated straining force is set.

The aircraft 24 is mounted on the carriage 2, the rollers 15 fixed in the upper part of the carriage are in contact with the lower surfaces of the UAV. The protrusions 16 and the stoppers 10 interact with the reciprocal power elements of the aircraft 24. The protrusions 16 and the rollers 15 fix the aircraft 24 in all degrees of freedom, except for moving in the forward direction. The stops 10 are pulled up and fix the aircraft from moving in the forward direction.

From a source of compressed gas 17, which can be a compressor (driven by an electric motor or internal combustion engine) or charged with gas under a pressure of about 100 atm. the cylinder, through the valve device 19, the receiver 18 is charged with gas (for example, air) to a certain pressure (of the order of tens of atmospheres). The pressure value is determined depending on the starting weight and thrust of the power plant UAV. When using a high-pressure cylinder 17 as a source, it is possible to additionally apply a pneumatic reducer tuned to the required pressure for filling the receiver 18.

Using a pressure gauge 20, the pressure level in the receiver is monitored 18. With excessive pressure in the receiver, the valve 21 will discharge it into the atmosphere.

Next, the UAV power plant is launched and brought to maximum thrust mode, after which an electric command is sent to the programmable controller 23 (by programming the controller 23, the time for shutting off the compressed gas supply to the power pneumatic cylinder 5 is set, this time is determined depending on the pressure in the receiver 18, the starting mass and traction of the UAV power plant 24).

The controller 23 opens the electro-pneumatic valve 22, the compressed gas is supplied to the working chamber of the power pneumatic cylinder 5.

The gas pressure force on the piston 6 through the cable 12, thrown through the blocks 11, is transmitted to the carriage 2. When the traction on the carriage reaches the thrust value corresponding to the actuation force of the locking device of the starting position, the hinged bar 7 is reset from the pin of the spring unit 13. Carriage 2 starts moving along the guide 1 catapult and accelerates along with the aircraft 24. After the start of the movement of the cart, the checks 9 are pulled out of the holes of the stoppers 10, the stoppers are removed by the action of the springs installed on them inside the cart and release 24 aircraft by fixing the direction of "forward". However, the UAV is kept on the cart due to interaction with the rollers 15 and the protrusions 16, since the acceleration of the cart with the aircraft, created by the booster, exceeds the acceleration of the aircraft, created by its power plant.

Before the contact of the truck 2 with the brake device 3 of the catapult, the controller 23 closes the electro-pneumatic valve 22, the gas supply to the working chamber of the power pneumatic cylinder 5 is stopped. Moreover, near the closed end of the power pneumatic cylinder 5 when the piston 6 is displaced to it, a piston braking chamber closed in volume is formed.

When equipping the power pneumatic cylinder 5 with drainage holes, before the contact of the truck 2 with the brake device 3, compressed gas is released from the working chamber through the opening drainage holes, which helps to brake the truck 2. This reduces the overloads that occur when the truck 2 hits the brake device 3.

After moving along the entire length of the guide 1, the carriage 2, together with the aircraft 24, acquires the speed necessary for the take-off of the UAV.

At the end of the guide 1, the carriage 2 interacts with the brake device 3, which dampens its speed.

When braking the trolley 2, the aircraft 24, due to the thrust of the power plant and inertia forces, moves in the forward direction and rolls along the rollers 15 of the trolley with its lower surface, leaves it and starts an autonomous flight.

Claims (1)

A catapult for take-off of an aircraft, comprising a guide with a trolley, an accelerating device of the trolley, including a power pneumatic cylinder with a piston and a cable with blocks, one end of the cable is connected to the trolley, a docking unit with an aircraft is mounted on the trolley, a brake device is installed on the guide, which differs the fact that on the guide and the trolley there is installed a device for fixing the starting position of the trolley with adjustable calibrated pulling force, the accelerating device contains a source of compressed gas and the receiver, the source of compressed gas is connected to the receiver through a valve device, a pressure gauge and an overpressure relief valve are installed on the receiver, the power pneumatic cylinder is connected to the receiver via an electro-pneumatic valve, the electro-pneumatic valve is controlled by a programmable controller, the docking unit with the aircraft contains symmetrically fixed to the top of the truck with respect to the vertical longitudinal plane of symmetry of the trolley, freely rotating rollers in an amount of at least four, as well as protrusions, fixing the aircraft in all degrees of freedom with the exception of moving in the forward direction, retractable stoppers securing the aircraft from moving in the forward direction, the second end of the cable is fixed to the piston, and the controller stops the supply of compressed gas to the power pneumatic cylinder until the contact of the trolley with the brake device, the stops are removed until the contact of the trolley with the brake device, the rollers are in contact with the lower surfaces of the aircraft, the protrusions and stops interact with the reciprocal power elements of the aircraft, the acceleration of the cart with the aircraft, created by the booster, exceeds the acceleration of the aircraft, created by its power plant.

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