RU172327U1 - UNMANNED AERIAL VEHICLE - Google Patents

Abstract

The utility model relates to aircraft, in particular to unmanned aerial vehicles. An unmanned aerial vehicle contains a glider on which the propulsion system is located. The glider is made in the form of two parallel wings placed on the beams, located crosswise relative to each other, and fixed on the beams by means of couplers, the glider being equipped with an additional wing attached to the beams between the existing wings and parallel to them, and the engines of the propulsion system are placed on the beams in the space between the wings and symmetrically with respect to the additional wing. The technical result consists in improving the technical characteristics of an unmanned aerial vehicle. 5 s P. f-ly, 3 ill.

Description

The utility model relates to aviation technology, in particular to unmanned aerial vehicles (UAVs) of vertical take-off and landing, designed to carry out a wide range of works, including ensuring the prompt delivery of video equipment to the place of video recording, video recording in hard-to-reach places, monitoring territories, industrial enterprises and railway stations, ports, pipeline routes, power lines, etc.

Recently, there has been a significant increase in the interest in using UAVs for solving a variety of tasks, the fulfillment of which by manned aircraft for various reasons is impossible or impractical.

Currently, UAVs are most actively used to solve the following problems:

- remote environmental monitoring with sampling from hard-to-reach places with visual control of measurements and sampling sites, as well as their delivery to the place of analysis;

- search and rescue operations;

- monitoring of sea and river highways and reservoirs, monitoring of objects and routes of production, production and transportation of electric energy, natural gas, oil and its products, hazardous chemicals and other substances;

- patrolling borders, military, administrative, economic facilities, large industrial enterprises with hazardous production, monitoring strategic transportation routes, monitoring mobile facilities and population groups, monitoring and ensuring security during public events;

- notification of the occurrence and development of accidents, natural disasters or dangerous situations in controlled areas, identifying the operational situation and the presence of victims in criminogenic places, as well as in places of chemical infection, etc.

To solve the above problems, a large number of UAV design schemes have been developed.

Currently, UAV designs that provide vertical take-off and landing, horizontal movement to a given point, and UAV hovering at a given point are the most promising.

So, for example, a combined UAV is known, made according to the flying-wing fuselage-free aerodynamic design and consisting of the following basic elements: a free-flying wing, a lifting engine, a traction motor and a stabilizer.

The free-carrying wing is designed to accommodate units and assemblies of the apparatus. A nose fairing is installed in front of the wing, inside of which there is a control unit, electronic monitoring equipment, a transceiver unit, antennas, a flight-navigation system, etc.

The front part of the free-carrying wing has a shape that provides minimal aerodynamic drag, and controls are installed in the rear part of the wing. Equipment has been installed on the wing, which, depending on the purpose of the UAV, may be different, for example, for environmental purposes.

The UAV lifting engine is installed in the center of mass of the free-carrying wing. It is designed to create the vertical thrust needed to implement launch modes, hovering over a given point and landing. The lifting engine is designed to rotate the screw, the axis of which is vertically fixed inside the sleeve located in the center of mass of the UAV.

The traction motor is designed to create a horizontal component of traction. It is mounted at the rear of the free-standing wing.

The UAV stabilizer is designed to shift the center of pressure away from the center of mass, which ensures an increase in the static stability margin of the UAV. The stabilizer is made in the form of a plate, which is fastened with the help of the tail beams to the free-standing wing at a small angle, which is necessary to create the initial lifting force for the planning flight of the UAV. The stabilizer is installed between the tail beams with the possibility of rotation relative to its horizontal axis, providing UAV control by pitch angle.

When starting the UAV, the lifting engine is turned on. The traction motor is off. As soon as the thrust created by the lifting engine exceeds the starting mass of the UAV, it breaks off the surface and rises vertically up to gain the desired height. After gaining the required altitude, at the command of the UAV control system, the lifting engine is turned off and the traction engine is switched on, through which the UAV is moved horizontally.

If necessary, the UAV hangs in the air above a given point. To do this, the traction engine, together with the UAV control system, works in such a way that the UAV is located above a given point on the surface. Then it turns off, and the lift motor turns on.

UAV flight can take place in accordance with the flight task both according to a given program, and according to radio commands transmitted by the operator from a ground-based remote control point. The ground-based remote control station generates commands transmitted over the air to the on-board electronic equipment installed on the UAV. In this case, the pitch angle control is carried out by turning the stabilizer around the axis, and the yaw angle control is carried out by rotating the aerodynamic controls, which are keels, interconnected by a connecting rod and installed on both sides of the stabilizer.

UAV flight control is carried out using the flight-navigation system. At the same time, the results of a remote survey of the terrain, as well as video and telemetry information, are transmitted to the ground-based remote control point via a UAV transceiver antenna.

UAV landing is carried out vertically when the traction engine stops and the lift is switched on.

(see RF patent for utility model No. 98394, class B64C 27/22, 2010).

As a result of the analysis of the design of the known UAV, it should be noted that it provides the possibility of vertical entry and landing, horizontal movement, hovering over a given point. However, the design scheme used in the well-known UAV - one lift and one marching engine leads to the fact that during the flight (hovering) only one engine always works, and the second is switched off, that is, it is ballast. This leads to an increase in the mass of the UAV, as a result of which it is not able to develop high speed. Placing a lifting engine in the center of mass of the wing makes it difficult to center the equipment when it is mounted on the wing. When lifting a UAV, it is necessary to overcome the aerodynamic drag of the wing, which leads to a slowdown in the lift speed and increased loads on the lift engine. It should also be noted that a single propeller of the lifting engine creates a torque that can lead to spurious rotation of the flying wing during vertical take-off. To control the flaps, such a device must be equipped with a rather complex radio control system. This complicates the aircraft, and also reduces its reliability and survivability in the fall and collisions.

A multi-screw UAV of vertical take-off and landing is known, consisting of two articulated modules: a lifting-marching module, carrying an even number of power plants and a module of equipment, control and target load, a power frame is placed inside this module, in the central part of which a vibration-damping column is vertically fixed, representing a tubular fine-corrugated structure made of composite material.

In the upper part of the vibration damping column there is a two-stage vibration damping hinge attached by means of a ring to the vibration damping column. The lifting-marching module has the ability to swing around the axes installed in the vibration-damping column. The vibration-damping hinge also contains a ring to which the head of the lifting-marching module is attached through the axes. This design of a two-stage vibration damping hinge allows you to freely deflect the lift-march module in two planes, providing control of the device along the axes OX and OZ. Pylons are attached to the head of the lifting-marching module, at the ends of which there are installed engines of the propulsion system, equipped with rotors of a single or coaxial type.

The deviation of the lift-march module is provided by servos through control rods.

A sufficiently large excess of the plane of the rotors over the position of the center of mass of the apparatus ensures its high stability during the operation of the target load.

Take-off of the device is carried out with the vertical position of the power plants. Rotating propellers rotor propellers throw the air flow down and thereby ensure the separation of the apparatus from the surface of the earth. The device freezes at a certain height above the launch site. The aerodynamic noises and vibrations created by the power plants of vibration and rotors are suppressed in the vibration-damping hinge. Part of the outstanding vibrations transmitted through the vibration damping hinge is finally damped by the vibration damping column, thereby providing comfortable conditions for the target load of the apparatus.

The control of the apparatus in height is provided by a change in the pitch of the rotors with a corresponding change in the power of the power plants according to the signals of the control system.

After takeoff and climb, the UAV can go into horizontal flight, creating propulsive force by tilting the lift-march module and, accordingly, by tilting the planes of propellers in the direction of flight direction. The aerodynamic layout of the device allows it to move in any direction at the same speed.

(see RF patent No. 2403183, class B64C 29/00, 2010).

As a result of the analysis of the known UAVs, it should be noted that in its design the engines of the propulsion system provide UAV operation both during lifting (lowering) and during horizontal flight, vibration damping elements reduce the vibration of the equipment module, which improves the quality of work of the target equipment installed on the UAV. However, a significant drawback of the known UAV is the high aerodynamic drag due to the need to move the UAV in the vertical and horizontal directions without changing the position of the bearing aerodynamic surfaces of the UAV, as well as placing a large number of special equipment on them. One of the disadvantages of this engine is the placement of the engine outside the center of mass, which leads to an unstable position of the UAV when changing the flight mode. All this leads to a decrease in speed and range. The absence of wings and, therefore, not the use of their lifting force, determine the low speed and range.

Known combined UAV containing a free-flying wing, designed to accommodate and fasten the nodes and assemblies of the device. A nose fairing is installed in the front part of the wing, inside of which there is a control unit, monitoring equipment, a transceiver unit, antennas, a flight-navigation system, etc. The front part of the free-flying wing has a shape that provides minimal aerodynamic drag. Inside the free-standing wing, special equipment is fixed.

The UAV propulsion system consists of four lifting engines located symmetrically about the axis of the apparatus and outside it. Lifting motors by means of beams are rigidly attached to the free-carrying wing of the UAV, and the axis of the shafts of these engines pass through the center of mass of the apparatus, while the entire payload fully occupies the entire free volume of the free-carrying wing. Each engine consists of a lifting screw attached with a skeg to a sleeve that connects the rotary engines to the wing of the UAV.

Rotary engines are designed to create the thrust necessary to move the UAV in the horizontal plane, as well as for vertical take-off and landing of the device.

When starting the UAV, the rotary engines are in a position that ensures the vertical rise of the UAV. As soon as the total thrust created by the engines exceeds the starting weight of the UAV, it breaks off the surface and begins to climb to gain the desired height. Since the axis of the shafts of the lifting motors pass through the center of mass of the UAV, the apparatus is statically stable during its lifting.

After gaining a predetermined height at the command of the control system, the engines are put into horizontal flight mode.

If necessary, the UAV hangs in the air above a given point. For this, the engines operate in such a way that the UAV is located above a given point on the surface. Then, on command, they are put into hover mode.

In this case, the total thrust created by the engines should be equal to the starting weight of the UAV.

UAV landing is carried out when the engines are in take-off and landing mode. At the same time, the UAV lands smoothly.

(see RF patent for utility model No. 71960, class B64C 39/00, 2008) is the closest analogue.

As a result of the analysis of the known UAV, it should be noted that it provides vertical take-off and landing, as well as horizontal movement with the possibility of hovering at a given point. The presence of four engines increases the reliability of the UAV, since it can work in case of failure of two of them. The removal of engines on beams beyond the wing contour increases its stability. However, a non-optimal aerodynamic configuration leads to a large aerodynamic drag, both in vertical and horizontal flight. This reduces the speed of flight, as well as the length of time the device is in the air and range. The removal of engines on the beams beyond the wing contour reduces the reliability and survivability of the UAV during falls and collisions.

The technical result of the utility model is to improve the technical characteristics of the device, namely to increase the speed and range of both horizontal and vertical flight by reducing aerodynamic drag at each stage of the flight and ensuring the stability of the UAV in flight.

The specified technical result is achieved by the fact that in an unmanned aerial vehicle containing a glider, on which the propulsion system is located, it is new that the glider is made in the form of two parallel wings placed on beams located crosswise relative to each other and fixed on beams by means of couplers, and the glider is equipped with an additional wing attached to the beams between the existing wings and parallel to them, and the engines of the propulsion system are placed on the beams in the space I wait for the wings and symmetrically with respect to the additional wing, while the ties can be attached to the wings with the possibility of removal, and the additional wing and beams are equipped with places for setting the payload. The wings are connected to the beams with the possibility of separation, and the beams are connected to each other with the possibility of separation or relative rotation.

The essence of the claimed utility model is illustrated by graphic materials on which:

- in FIG. 1 - UAV is presented, side view;

- in FIG. 2 - presents a UAV, a top view for vertical flight or a front view for horizontal flight;

- in FIG. 3 - UAV beams.

The UAV is made in the form of a glider, containing two parallel to each other wings 1 and 2, connected to the ends of the beams 3 and 4. The connection of the wings with the ends of the beams can be carried out in various known ways, for example, blind grooves are made on the wings, into which they are brought in when assembling the UAV ends of beams. The power circuit of the assembled beams and wings is carried out with ties 5 and 6. Couplers can be made in the form of cables or rods, one end of each of which is removably fastened to the wing, and the second end of each of the couplers is threaded. So, a pair of couplers is placed on the wings along one axis, and a tightening sleeve is screwed onto their threaded ends. Similarly, another pair of couplers is installed. Ties can have a U-shape, the cross-member of each of which is laid along the wing, and their ends are facing each other. The connection (tightening) of the ties 5 and 6 can be carried out similarly to the above (by means of threaded couplings) or a quick-clamping device, for example, lever or eccentric type.

The above layout of the airframe forms a light and very rigid spatial design.

It is easy to notice that the UAV glider described above is made according to the “biplane” scheme, embodying all the advantages of this design (flight stability, easy controllability, maneuverability, which allows developing high flight speed in combination with effective flight control). To increase the flight range and stability of the UAV (which is especially important when using non-standard suspensions, in which it is difficult to ensure proper alignment of the UAV), an additional wing 7 is fixed on the beams 3 and 4, preferably removably, that is, in this case, the “biplane glider” scheme »Is converted to a triplane. This scheme allows you to provide optimal flight conditions for range and controllability, for example, in adverse weather conditions. An additional wing 7 is located between the wings 1 and 2 and parallel to them.

It is most advisable to attach an additional wing to the beams 3 and 4 in the place of their crossing. This ensures the alignment of the UAV.

There are places on the wing 7 and / or beams 3 and 4, for example, brackets, mounting slots, etc., for mounting a payload, for example, 360 ° cameras, air sample analyzers, etc. On (in) wing 7, place UAV operation control unit, transceiver unit, antenna devices, flight and navigation equipment, etc. This arrangement avoids problems with UAV alignment.

The UAV propulsion system is made in the form of engines (screw or jet). The number of engines can be different, but not less than two. The engines are placed on beams 3 and 4 symmetrically with respect to the additional wing 7. This arrangement is necessary to ensure the alignment of the UAV and control its position both in vertical and horizontal flight. In FIG. 2 shows a UAV with four engines 8, 9, 10, 11, which does not mean that their number cannot be different. The engines of the propulsion system are mounted on beams 3 and 4 longitudinally, that is, parallel to the bearing planes of wings 1, 2 and 7.

It is easy to see that the advantage of the UAV design is also the possibility of its easy assembly and disassembly. So the power circuit of the elements of the airframe is provided due to the quick and convenient pulling together with their ties. Such a connection is provided using standard means and does not cause difficulties for specialists. Beams 3 and 4 are most advisable to connect with each other with the possibility of separation or relative rotation to fold them into a transport position, in which they occupy a minimum of space. Structurally, this can be provided in a variety of known ways, for example, with a coupling bolt 12, passed through the holes of the beams made in the place of their crossing. In the working position, the coupling bolt is passed into the holes of the beams and due to the tightened nut provides a rigid connection of the beams in the working position. To bring the beams into the transport position (or storage position), the bolt tightening force is weakened, and the beams relative to the bolt, which in this case is the axis, are turned into the transport position, bringing them together. If it is necessary to disconnect the beams for transportation (as well as repair or replacement), unscrew the nut from the coupling bolt, remove the bolt from the holes of the beams and disconnect the beams. All components and assemblies used for assembling the UAV are known, standard version, and are used for their intended purpose. Their constructive implementation is not the subject of patent protection in this application. The software tools used in UAV flight control are also standard.

UAV works as follows. UAV operation can be controlled from a ground control station or according to a program entered into the UAV control unit.

We consider the operation of the UAV using the example of its use for video recording of emergencies, disasters, etc. For video recording on regular places of wing 7 or beams 3, 4, video cameras are mounted.

The starting position of the UAV - wings 1 and 2 are located vertically by the bearing planes, engines 8, 9, 10, 11 (let it be the engines that rotate the screws) of the propulsion system are located vertically, which is necessary to create a vertical lifting force.

Take-off and vertical rise of the UAV is carried out with the engines of the propulsion system turned on.

Rotated by engines vertically located rotor propellers throw airflow down and thereby ensure the separation of the UAV from the ground. The device performs a vertical ascent and freezes at a predetermined height above the launch site. Given that when ascending to a given height, the wings 1, 2, 7 of the airframe are vertically supported by bearing surfaces, their aerodynamic surfaces practically do not resist the process of lifting a UAV to a given height. This can significantly increase the lifting speed and reduce the load on the engine.

After takeoff and gaining a predetermined altitude, UAVs are transferred to the horizontal flight mode. To do this, by controlling the engines of the propulsion system, the UAV is rotated 90 ° to a position in which the wings 1, 2 and 7, as well as the engines 8, 9, 10, 11 of the propulsion system, are in a horizontal position.

In horizontal flight mode, the program control system or in manual control mode controls the engine thrust for stabilization and flight control by pitch, heading and roll, that is, the UAV rotation mechanism, as a separate structural unit, is absent, which greatly simplifies the UAV design and reduces its weight .

After a 90 ° turn, the UAV flies horizontally to a predetermined point for video recording. Flight control is carried out, as already noted above, either from the control point, or according to the program entered in the UAV control unit. During the flight, wings 1, 2 and 7 are located horizontally, that is, the glider during the horizontal flight operates according to the “triplane” scheme, using all the advantages of this scheme. The use of such a scheme for horizontal flight provides high UAV stability, easy maneuvering, and also allows you to develop high flight speed. Aerodynamic drag during horizontal flight of the UAV is minimal.

Upon arrival at the survey point, the UAV, similar to that described above, makes a 90 ° turn, freezes at a given point. At the command of the control unit or from the operator’s console, the cameras are turned on, shooting and transmitting the image to the operator’s console in real time. Given that the UAV is distinguished by a very rigid structure, vibration during engine operation has a minimal effect on the quality of shooting.

After the shooting process is completed, the operation of the cameras is turned off, as described above, the UAV is deployed 90 °, after which it performs a horizontal flight to the landing site, which is carried out by the vertical movement of the UAV down.

Thanks to the implementation of the glider according to the “triplane” scheme and the possibility of UAV rotation by 90 °, the aerodynamic characteristics of the UAV are optimal both in the modes of ascent - descent and horizontal flight. The UAV design has high rigidity due to the rigid connection of the wings and beams with ties, which minimizes vibration during flight and, thereby, improves the quality of video recording if the UAV is designed for this purpose. The engines of the propulsion system are located in a space limited by wings and couplers, which allows you to reliably protect them without resorting to additional protection elements, which also reduces the weight of the UAV.

It is also very important that in flight, the payload, which often has a cost much higher than the cost of the UAV itself, is reliably protected by wings above and below, and on the sides with ties that do not interfere with its operation, since in this case the UAV is turned by 90 °.

After the operation, the UAV can be easily disassembled to increase its convenience during transportation or storage.

Claims (6)

1. An unmanned aerial vehicle containing a glider, on which the propulsion system is located, characterized in that the glider is made in the form of two parallel wings placed on beams located crosswise relative to each other and fixed on the beams by means of couplers, the glider being equipped with an additional a wing attached to the beams between the existing wings and parallel to them, and the engines of the propulsion system are placed on the beams in the space between the wings and symmetrically with respect to the additional la. 2. An unmanned aerial vehicle according to claim 1, characterized in that the couplers are removably attached to the wings. 3. The unmanned aerial vehicle according to claim 1, characterized in that the additional wing and beams are equipped with places for setting the payload. 4. An unmanned aerial vehicle according to claim 1, characterized in that the wings are connected to the beams with the possibility of separation. 5. Unmanned aerial vehicle according to claim 1, characterized in that the beams are connected to each other with the possibility of separation. 6. Unmanned aerial vehicle according to claim 1, characterized in that the beams are connected to each other with the possibility of their relative rotation.

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