RU2049701C1 - Aviation system - Google Patents

Abstract

FIELD: aviation. SUBSTANCE: system consists of several aeroplanes 1 and 2 and connecting device 7 which connects tips of panels of wings 5 and 6 of aeroplanes of this group. Aeroplanes 1 and 2 are oriented in group for circumferential motion in one direction. When engines are started, device 7 holds moving aeroplanes in group and after rising to required height, device is unlocked releasing the aeroplanes for flight. EFFECT: simplified construction for vertical take-off. 4 cl, 5 dwg

Description

 The invention relates to aviation, mainly unmanned aircraft, i.e. to unmanned vehicles with a large elongation of the wings, for example to high-altitude, as well as for schemes "flying wing".

 Known devices that contribute to the takeoff of aircraft, for example, [1] It is a simple engineering structure based on a truck. It has a rotating balanced rod, in a particular case 6 m long. The unwinding and take-off are carried out using the aircraft’s own power plant and do not need additional power plant.

 However, such a device does not contribute to the vertical take-off of unmanned vehicles, which is so necessary in the conditions of their use on rough terrain. In addition, it is bulky, mounted on a special machine. In this way, it is possible to launch only small-sized unmanned vehicles, since heavier ones (weighing more than 2 tons) will require the creation of extremely bulky and massive balanced rotating rods that can no longer fit on cars.

 Closest to the invention is a technical solution [2] taken as a prototype. This device is an aviation system containing aircraft oriented to move in a circle in one direction, and a means for connecting and undocking with remote control.

 The disadvantages of this system are the bulkiness and complexity in the manufacture of means for connecting aircraft, requiring significant financial costs for its construction. This stationary large structure with a hydraulic drive device for lifting aircraft, adapted to hold them and subsequent undocking, needs to be installed on the foundation. In addition, the vertical movement of aircraft is limited by the size of the connection tool itself, as well as its rigid connection to the ground.

 The aim of the invention is to simplify the design while providing vertical take-off.

 For this, the means for connecting and arranging the aircraft is made in the form of a fastening device, connected with the possibility of unlocking relative to the seats at the ends of the wing consoles of the aircraft, equipped with means for lowering it to the ground after unlocking, and the remote control contains a drive with an autonomous power source for the said mounting device . The fastening device is made in the form of ball locks and contains a means for lowering to the ground after milling. The drive for the mounting device is made in the form of a rack-and-pinion gearbox with an electric motor, and an electric battery is used as an autonomous power source.

 The remote control contains electric motor switches located on the wing consoles of the aircraft and a communication circuit with the operator.

 Figure 1 is a General view of the system; figure 2 means for connecting and undocking in the docked position of the aircraft system, side view; figure 3 is the same, a top view; figure 4 the left part of the means for connecting and undocking at the time of uncoupling of the wing consoles; figure 5 aviation system after undocking the aircraft.

 The system consists of at least two aircraft 1 and 2, namely unmanned aircraft containing engines 3 and 4. The ends of the wing consoles 5 and 6 are connected by means of a special tool 7 for connecting and undocking, made in the form of a mounting device. The planes in the system are oriented for moving in a circle in one direction, i.e. the thrust vectors of their engines are directed in opposite directions so that during their operation a torque of rotation of one direction is created. Aircraft docked in this way should be of the same weight. In addition, the aircraft have heights of 8 and 9. The tool for connecting and undocking is equipped with a descent tool made in the form of a parachute 10 or an autorotating screw.

 The housing 11 of the means for connecting and undocking the aircraft 1 and 2 has a rubber shock absorber 12. The tool itself is made in the form of a fastening device, which is formed by pins 13 and 14, on each of which one of the ball locks 15 and 16 is placed, interacting with the axes 17 and 18 and fixing the position of the mounting device relative to the seats on the wing consoles 5 and 6. The axles 17 and 18 have gear racks 19 and 20 at the ends, engaged with the gear 21, rigidly mounted on the shaft of the electric motor 22 with a reduction gear 23. This forms a drive d for fixing the wing consoles. An electric battery 24 is used as a stand-alone source. The remote control element 25 is a switch 25 of an electric motor 22 connected by an electric circuit to an operator.

 The cover 26 protects the means for launching, for example, a parachute 10. The stops 27 and 28 on the pins 13 and 14 serve to limit their introduction into the consoles, where they interact by means of ball locks 15 and 16 with the wing consoles 5 and 6, on the seats of which are made annular grooves 29 for receiving balls of locks 15 and 16.

 In operation, the system operates as follows.

 After starting the power plants, unmanned aerial vehicles, in this case with self-orientating landing gears, spin around the axis of rotation to take-off speed. At the same time, rudders of heights 8 and 9 are set to dive, pressing the nose struts of both aircraft to the take-off area and preventing their premature separation from the ground. After reaching take-off speed, elevators at the command of the operator are smoothly transferred to the take-off position and a group of devices takes off vertically upward, continuing to rotate around their common axis of rotation.

 After a group of unmanned aerial vehicles has set a safe altitude, that is, an altitude at which it is impossible to collide with surrounding objects, a trip from the ground occurs upon command. Aircraft under the influence of centrifugal forces fly apart in different directions, and the means for connecting and undocking smoothly descends by parachute 10.

 The means for connecting and undocking works as follows.

 During the course of the axes 17 and 18 (Fig. 2) towards the gear 21, the balls of the locks 15 and 16 enter the inside of the pins 13 and 14, which in this position lead into the ends of the consoles to the stops 27 and 28. After the opposite (from the gear towards consoles) the axes 17 and 18 move the lock balls fall into the annular groove 29 (Fig. 4) of the ends of the consoles, thus ensuring fixation. At the command of the operator, the switch 25 closes the power supply circuit of the electric motor, which, rotating the gear 21, pulls the axles onto itself, releases the balls of locks 15 and 16 from engagement (Fig. 4) and the aircraft under the action of centrifugal forces scatter in different directions.

 Light cover 26, freed from the ends of the consoles, flies away under the action of aerodynamic forces, pulls an articulated parachute 10 behind it, on which the device smoothly makes a landing. Instead of a parachute, autorotating aerodynamic surfaces can be used. In the housing of the means for connection and undocking, there may be a fuel tank, intended only for power supply of power plants at the take-off stage.

 It is necessary to take into account that to ensure vertical take-off and to make a long flight for military and civilian purposes, rotary-wing unmanned aerial vehicles are currently used abroad, which, firstly, are uneconomical in cruising flight due to the peculiarities of their aerodynamic layout, and secondly , such devices in our country are not yet available. Therefore, it is very important that the aviation system allows vertical take-off without complex substantial alterations to the already operating aircraft-type aircraft and to eliminate the lag in this area.

 The technical and economic effect will also take place due to increased safety at the take-off stage in the proposed manner. When starting an unmanned aerial vehicle from a catapult, there are cases of a sudden engine stop when leaving the rails, which often results in serious aircraft breakdowns. When using the proposed aviation system in the event of engine failure in one of the unmanned aerial vehicles, the group will land smoothly, continuing to rotate around a common axis. Even with the failure of all engines, the group, rotating due to inertia, will make an accident-free landing.

 It should also be noted that the proposed aviation system allows “launching” launches of a large number of aircraft-type aircraft simultaneously.

Claims (4)

 1. Aviation system, containing aircraft oriented to move in a circle in one direction, and means for connecting and undocking with remote control, characterized in that, in order to simplify the design while ensuring its vertical take-off, means for connecting and undocking aircraft in the form of a fixing device connected with the possibility of unlocking relative to the seats at the ends of the wing consoles of aircraft, equipped with means for its descent to the ground after unlocking, and the distance The control includes a drive with an independent power source for said mounting device.  2. The system of claims. 1 and 2, characterized in that the mounting device contains ball locks, fixing the position of the device relative to the seats at the ends of the wing consoles of the aircraft.  3. The system of claims. 1 and 2, characterized in that the drive for the mounting device is made in the form of a rack-and-pinion gearbox with an electric motor, and an electric battery is used as an autonomous power source.  4. The system of claims. 1 to 3, characterized in that the remote control contains located on the wing consoles of aircraft electric motor switches associated with the operator.

Images