RU2373117C1 - Aircraft take-off accelerator - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: accelerator comprises accelerating device representing operating cylinder 1, accommodating piston 4 with rod 5, braking device 8 and compressed gas chamber 7. Bracket 14 is rigidly fixed outside cylinder 1 to support starting position retainer representing crank 15. Rod part 5 extending beyond cylinder 1 accommodates pylon 10. Atop upper part of pylon 10 accommodated is the device to place aircraft furnished with electromechanical system intended for separation of aircraft from aforesaid pylon and representing acceleration pickup 11 connected, via controller 12, with electric drive 13. Outside power cylinder, rotary front supports 20 with retainers 24 and rear support 21 are arranged. To start the aircraft, bell crank handle is lifted. Compressed gas pushes piston 4 with rod 5 from cylinder till piston contact with braking device 8. Electric signal from acceleration pickup 11 comes to controller 12, for its microprocessor to generate signal to electric drive to release aircraft from pylon 10.

EFFECT: higher reliability, reduced sizes.

4 cl, 7 dwg

Description

The invention relates to the field of aviation technology, and more particularly to take-off devices of aircraft, mainly small unmanned vehicles.

For take-off of small-sized unmanned aerial vehicles, launchers of the catapult type are widely used, which allow for fast and efficient take-off of these aircraft with a power plant of relatively low power.

An important feature of small-sized aircraft launches is the possibility of their take-off on unequipped sites and in the field.

Known devices for take-off small-sized unmanned aerial vehicles from a catapult equipped with a trolley that is moved by an accelerating device along the catapult guides (see Research on methods for launching remotely piloted aircraft (translated from English by L. Travkina, E. Chubchenko), ONTI MAI, 1983; Testing a new launcher for UAVs. RAE trials of RPV launchers // Jane's deference weekly / - 1985 / - v.3. - No. 19; Aero Digest Magazine, December 1931; UK patent application No. 2132577). These devices as a whole can be characterized as follows.

The device contains an accelerating trolley, which is located on the catapult in the starting position. After it is accelerated by the accelerating device to the required speed, the aircraft mounted on the trolley is disconnected from it, and the trolley is braked.

A common drawback of such devices is the insufficient reliability of the takeoff of the aircraft, due to the possibility of its contact with the elements of the catapult and truck, resulting from their relative relative motion at close distances from each other.

Known catapult for take-off of an aircraft (see UK patent No. 1473089, B64F 1/06, 1977), containing a guide, accelerating and braking devices, propelling device made in the form of a parallelogram mechanism having an upper base equipped with a docking unit with the aircraft, and lower base pivotally interconnected by supports.

The disadvantage of this known catapult is that to ensure the required take-off speed of the aircraft when throwing it requires a large power throwing device. In addition, the insufficient high-pressure air pressure due to the low speed of the longitudinal movement of the aircraft does not allow the aerodynamic forces created by it to accelerate the rise of the aircraft and control its position relative to the propelling device when they are undocked and separated. This can lead to touching the tail of the aircraft and the catapult and, as a result, to damage to the aircraft. In addition, the low vertical and horizontal speeds of the aircraft relative to the guiding catapult lead to an increase in the time of its removal from the catapult after separation of the trolley, which increases the length of the take-off distance, and also increases the likelihood of contact with the catapult during take-off and thereby reduces the reliability of take-off.

Closest to the proposed one is a catapult for take-off of an aircraft (see RF patent for utility model No. 66733, publ. 09/27/2007), containing a guide, acceleration and braking device.

The accelerating device of the known catapult is made in the form of a working cylinder in communication with a source of compressed gas through a shut-off valve. The piston of the working cylinder is equipped with a cable fixed along its axis. The housing of the working cylinder is made in the form of a pipe with closed ends, in one of which a hole for the cable is made, the piston is placed in the housing of the working cylinder with the ability to move along its longitudinal axis and forms a working chamber located on the side of the hole in the end of the working cylinder body and constantly communicating with the output of the shut-off valve. The cable is passed through an opening in the end face of the working cylinder housing, covers a block placed on the catapult outside the working cylinder housing, and is attached to a trolley mounted on two longitudinal guides of the guide device. Front and rear supports of the parallelogram mechanism are pivotally connected to the trolley with an upper base mounted on them with a docking station with an aircraft. The catapult as a whole has stationary supports.

A disadvantage of the known catapult is that its accelerating device is difficult in its design, which reduces the reliability of the catapult.

In addition, it must be borne in mind that the launch of small-sized aircraft, as a rule, is carried out in the field from unprepared sites, therefore, the catapult, like the aircraft, has special requirements for their transportation and storage. Fundamentally important is the requirement to minimize the size of the catapult and the possibility of its transformation for transportation and storage. In some cases, it is necessary to ensure that the catapult is placed in a container in the soldier's shoulder bag.

This known catapult has a large longitudinal dimension for increasing the path of the cart with the aircraft, as well as a large vertical and transverse dimensions due to the presence of a parallelogram mechanism and stationary supports. This eliminates the possibility of its transformation into a state convenient for transportation and storage.

The present invention solves the problem of obtaining a technical result, which consists in increasing the reliability of the operation of the catapult, as well as in reducing its size and ensuring further reduction in size during transformation for transportation and storage.

To obtain the specified technical result, the proposed catapult for take-off of the aircraft, as well as the closest known catapult, contains an accelerating device made in the form of a working cylinder having a chamber for compressed gas. Inside the working cylinder is a piston with the ability to move along its longitudinal axis. In addition, the catapult contains a locking trigger position, brake means and a docking unit with the aircraft.

Distinctive features of the proposed catapult are that in one end of the working cylinder there is a filling hole for connecting to a source of compressed gas, equipped with a check valve to which one side of the piston faces. The specified chamber for compressed gas is formed by a part of the working cylinder, enclosed between this hole and the side of the piston facing it. The piston has a rod oriented along the longitudinal axis of the working cylinder and extending beyond its limits through an opening in the end of the working cylinder opposite to the filling hole. The brake means is placed in the working cylinder near its end opposite the filling hole.

On the part of the rod extending beyond the limits of the working cylinder, a docking unit with an aircraft, made in the form of a pylon, is fixed. On the upper part of the pylon is fixed means for installing an aircraft with an electromechanical system of separation from the pylon. The latter is made with the possibility of triggering when changing the sign of the acceleration of the pylon. Outside of the working cylinder, a bracket is fixed on it, on which a start position lock is installed, made in the form of a rocking chair. A roller with a sleeve of elastic material is installed on one end of the rocking chair, and its second end is a handle for turning the rocking chair. On the part of the rod extending beyond the working cylinder, a canine with a niche is made for interaction with the rocking roller. Outside, two rotary front bearings are installed on the working cylinder with the help of fastening units equipped with clamps for their working position, and the rear support is rigidly fixed.

The attachment site of each of the rotary front bearings is made in the form of a three-stage hinge containing a sphere with a hole, while the lock of the working position of the front support contains a cylindrical body with a longitudinal groove, a spring and a movable pin are installed in the body for the interaction of one end with the specified hole of the sphere, the other the end of the pin abuts against the spring, the pin has a handle mounted to move along the longitudinal groove of the cylindrical body.

The electromechanical system for separating the aircraft from the pylon can be made in the form of an acceleration sensor mounted on the pylon, connected via an electric controller to remove the connection between the aircraft and the pylon, which is carried out using a rotary fixing bracket that interacts with the response element of the aircraft.

The brake means may be in the form of a coil spring or a package of elastic material with an opening for the piston rod.

The invention is illustrated by the drawings shown in figures 1-6, which depict:

figure 1 - General view of the catapult with a fixed aircraft on it until the launch;

figure 2 - catapult at the time of take-off of the aircraft;

figure 3 - lock start position;

figure 4 - mounting elements of the aircraft on the pylon;

figure 5 - stopper for fixing the rotary supports;

in FIG. 6 - catapult in the working position and in the position for transportation and storage.

The catapult contains (Fig. 1) an accelerating device made in the form of a working cylinder 1. A filling hole 2 with a check valve 3 is made in one end of the working cylinder 1. A piston 4 with a rod 5 is installed inside the working cylinder 1. The piston is made as part of a sphere. The rod has a part 6 extending beyond the limits of the working cylinder 1. A part of the working cylinder 1 between the filling hole and the inner surface of the piston sphere part 4 facing it forms a chamber 7 for injecting gas under pressure. The execution of the piston in the form of a hemisphere allows you to increase the internal volume of the chamber for pumping gas. The brake device is made in the form of a compression spring 8 or a package of elastic material. To seal the cylinder cavities, seals 9 are used.

On the outside of the working cylinder of part 6 of the rod 5, a docking unit for the catapult is fixed to the aircraft, made in the form of a pylon 10, as well as an electromechanical system for separating the aircraft from the pylon, made in the form of an acceleration sensor 11 mounted on the pylon, connected via an electric controller 12 to 13.

An element for removing the connection between the aircraft and the pylon is located on the upper part of the pylon (Fig. 4) and is made in the form of a fixing bracket 33 fixed to the electric drive 13. The detachable mount of the aircraft to the catapult is made in the form of a bracket 34 and rollers 35 mounted in the bracket.

Outside the working cylinder 1, a bracket 14 is fixed (Fig. 3), on which a start position lock is installed, made in the form of a rocker 15. A roller 16 with a sleeve 17 made of elastic material is fixed at one end of the rocker 15, and the second end of the rocker 15 is handle 18 for turning it.

On the outer part 6 of the rod 5 is made a fang 19 with a niche 40 for interaction with the roller 16 of the rocking 15.

On the working cylinder 1, the front rotary supports 20 and the rear support 21, as well as the latches 24 of the position of the front supports 20 are fixed by means of fastening units 30 (Fig. 1). Supports are designed to install the catapult in the working position.

The mount 30 (Fig. 5) of each of the front pivot bearings 20 is a three-stage hinge and contains a sphere 31 with an opening that is designed to interact with the pin 23 of the latch 24. The latch 24 of the position of the front supports 20 is made in the form of a cylindrical body 26 with a longitudinal groove 28. A spring 27 and a movable pin 23 are installed in the cylindrical body 26, one end of which abuts the spring 27 and to which the handle 25 is attached. The handle 25 is mounted to move along the groove 28 of the cylindrical body 26 together the movable pin 23.

The mounting unit 30 is mounted on the working cylinder 1 using the legs 50 (Fig.6).

The device is used and operates as follows.

Before starting the aircraft, the catapult is installed in the working position, for which the front rotary supports are deployed in the direction of the pylon 10 until the pin 23 of the clamp 24 of each rotary support falls into the hole of the sphere 31, after which the rotary supports occupy a fixed position relative to the working cylinder 1.

After installing the catapult in the working position, the rocker handle 18 is lowered down (Fig. 3), while the other end of the handle 18 with the fixed roller 16 rises up and down until the roller 16 rests on the canine 19. Upon contact with the canine 19 the elastic sleeve 17 is deformed and the roller 16 moves along the surface of the canine 19, occupying a position in its niche 40.

Then, high-pressure gas is supplied to the working cylinder 1 through the filling hole 2. When the working pressure in the chamber 7 is reached, the gas supply is stopped. Check valve 3 prevents the escape of gas from the chamber. The catapult is ready to launch the aircraft.

After that, on the pylon 10 place the aircraft, as shown in figure 1, and start the engine of the aircraft.

To launch the aircraft, the rocker handle 18 is lifted up, while the other part with the roller 16 mounted on it is lowered down. Upon contact with the canine 19, the elastic sleeve 17 is deformed and the roller 16 moves down along the surface of the canine 19 until it leaves its niche 20. In this case, the compressed gas moves the piston 4 with the rod 5 from the working cylinder 1 until the piston 4 contacts the brake means 8.

To separate the aircraft from the pylon 10 of the catapult, the signal of the acceleration sensor 11 mounted on the pylon 10 is used, the sensitive element of which reacts to a change in the overload sign at the moment of contact of the piston 4 with the brake means 8. The electrical signal from the acceleration sensor is transmitted to the controller 12 as a pulse, the microprocessor which gives a command to the electric drive 13 to rotate the latch bracket 33 to the left, as shown in Fig.4. The rotation of the bracket-latch 33 is carried out at the time of complete braking of the rod with the pylon, when in the center of mass of the aircraft there is a force pushing the aircraft from the pylon forward in the direction of movement.

The rotation of the bracket-latch 33 allows you to free the aircraft from communication with the pylon, as a result of which the aircraft with the engine running detaches from the pylon and takes off.

At the end of the launches, the front swivel bearings 20 are folded. To do this, the handle 25 of the latch 24 is moved back in the opposite direction to the start. In this case, the movable pin 23 together with the handle leaves the opening of the sphere 31, the supports 20 are deployed and they occupy a position along the working cylinder 1. After this, the catapult is ready for transportation or storage.

Claims (4)

1. A catapult for take-off of an aircraft, comprising an acceleration device made in the form of a working cylinder with a chamber for compressed gas, inside of which there is a piston, a starting position lock, brake means and a docking unit with an aircraft, characterized in that in one end of the working cylinder a filling hole is made with a non-return valve, between which the specified chamber for compressed gas is formed between the piston and the piston has a rod extending beyond the working cylinder through an opening in its end face, against braking means is placed near the end of the filling hole, near this end in the working cylinder, on the part of the rod extending beyond the working cylinder, a docking unit is fixed in the form of a pylon, on the upper part of which is placed means for installing the aircraft, equipped with an electromechanical system to separate the aircraft from the pylon, in addition, the bracket on which the start position lock is installed is fixed outside the working cylinder e rocking chair, on one end of which a roller with a sleeve made of elastic material is installed, and the second end of the rocking chair is a handle for turning it, and a canine with a niche for interaction with the rocking roller is made on the part of the rod extending beyond the working cylinder, in addition , outside the rotary front bearings with clamps of their working position and a rigidly fixed rear support are installed on the working cylinder. 2. The catapult according to claim 1, characterized in that each of the rotary front supports is installed by means of a three-stage hinge containing a sphere with a hole, and the latch of the working position of the support contains a cylindrical body with a groove and a movable pin having an end extending beyond the body for interaction the specified hole of the sphere, and the second end of the pin located inside the housing is made abutting against a spring located at the end and having a handle made to move along the groove. 3. The catapult according to claim 1 or 2, characterized in that the electromechanical system for separating the aircraft from the pylon contains an acceleration sensor mounted on the pylon connected via an electric controller to rotate the latch bracket interacting with the response element of the aircraft. 4. The catapult according to claim 1 or 2, characterized in that the brake means is made in the form of a coil spring or a package of elastic material with an opening for the piston rod.

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