RU108016U1 - FLYING MOTORCYCLE - Google Patents

Abstract

 1. A flying motorcycle, including a base support platform, motors, seat, control system, characterized in that it contains a base support platform of cross-type beams, at the end platforms of the cross beams of which motors with pulling multi-blade propellers located in ring frames with protective arc from below; pulling propellers directed upward with a horizontal plane of rotation, at least two propellers with an operating mode of rotation clockwise and at least two propellers with an operating mode of rotation counterclockwise; parking supports are attached from below to the base platform; on top in the middle of the base carrier platform on the mounting platform, a structure is installed to accommodate the pilot, or the pilot and passenger, or the pilot and cargo, including the seat for the pilot, or the pilot and passenger; automatic parachute rescue system is located in the upper part of the structure; the control system has an electronic-digital unit that provides automatic control of the position of the device in the air horizontally and vertically by supplying control signals to motors, using data from electronic sensors and calculating the speed of rotation for each individual propeller, and compensating for external influences, ensuring the transfer of executive commands to motors from motorcycle controls; control devices are located on the steering wheel. ! 2. A flying motorcycle according to claim 1, characterized in that the motors are located symmetrically at least two to the right and left of the central axis of the structure, which coincides with the motion vector, �

Description

The utility model relates to aeronautical engineering, namely, to structures of vertical takeoff and landing aircraft heavier than air and can be applied to manned aircraft in small aircraft.

The use of aircraft vertical takeoff and landing in modern conditions is widespread, because they can be successfully used if necessary to get to hard-to-reach places where there is no place to place the runways of airfields. This applies not only to sparsely populated remote and inaccessible areas, such as the extreme north, taiga or mountains, but also to urbanized areas, where existing buildings do not allow the creation of runways. All this determines the prospects and the wide variety of designs of aircraft for vertical take-off and landing, including helicopters. For example, USSR patents 340239, 480213, applications and patents of the Russian Federation 95100371, 98116096, 2002671, 2714484 and others. A special niche is occupied by small-sized aircraft of vertical take-off and landing with sufficient carrying capacity, capable of being used as an individual air vehicle; as an air vehicle of emergency response services, monitoring and traffic control, monitoring of state borders and all kinds of objects of special importance, search work during natural disasters and technological disasters, fires in the city and in the forest, monitoring events with a large crowd of people. In this case, a particularly important factor is not only the relatively small overall dimensions of the aircraft, but also the design that allows it to be used in tight flight conditions where there is a possibility of direct contact between the propeller blades and the obstacle.

A technical solution is known by source: http://www.auto.mail.ru/article.html?id=20913 publ. 02/26/2007 under the name "Flying Motorcycle" (US), containing a frame, three wheels, a single seat, components of a folding propeller and transmission, Rotax 582 engine. The autogyro folds the blades, which allows you to sit down by braking for 6 m and continue on motorcycle. Disadvantages: pre-flight preparation is required - unfolding of wings, a runway of 50 m is necessary, it is impossible to hang in the air in one place, it is impossible to use in cramped flight conditions.

A technical solution is known by source: http://www.ufosecret.ru/page_814.html publ. 02/04/1955, under the name "Flying Platform" (US) - a rotary-wing aircraft in which the size of the rotor is small compared to the hull, containing a platform with a diameter of 1.8 m, and the rotation of the screws is carried out by two engines, for the pilot there is a stand with handrails. Disadvantages: poor stability and controllability, insecurity - due to the small size of the rotors in case of engine failure, the high speed of lowering the platform can lead to disaster; the inability to install additional equipment.

A technical solution is known according to the patent RU 83760 U1 B64C 39/00 dated 01.12.2008 “Kiselev Aircraft”, in which it is proposed to use an airplane wing, rolled into a ring, a pipe with a plugged ring is introduced into the center of this design. In the side wall of the pipe around the circumference there are holes located so that the air entering the pipe exits through these holes and blows the upper and lower surfaces of the wing simultaneously. Inside the pipe there are four flaps controlled by the pilot. These dampers are located in 4 sectors and allow you to turn off the air in any of the four sectors of the wing. Changing the flow of air into a particular sector, you can change the direction of flight. On the fixed platform of the apparatus there are two blowers, rotating in opposite directions and supplying air to one pipe, providing dynamic stability of the apparatus in a horizontal position. Disadvantages: control complexity, low speed, lack of mobility.

A technical solution is known according to patent RU 86560 U1 B64C 29/00, B64C 39/00 dated 12/01/2008 “Aircraft of vertical take-off and landing”, comprising a wing bent into the contour, having a profile of an airplane wing, inside of which a fuselage is mounted with a varying gap, and a power plant installed in such a way that pumps air flow in the wing plane in the direction of the center of the fuselage on the wing. On the outer edge of the wing and on the upper surface of the fuselage there are louvers of the intake manifold, and the wing flaps are installed in the lower part of the wing. Disadvantages: low carrying capacity, to ensure a given carrying capacity, the size should increase, the complexity of the design to ensure the necessary flight characteristics.

A technical solution is known according to patent RU 82674 U1 B64C 29/00 dated 11.11.2008 “Unmanned aerial vehicle of helicopter type”, consisting of a spherical fuselage, hollow inside, a pair of coaxial rotors and an electric motor, located in the annular channel along the equator of the fuselage, and internal a cart located in the region of the lower extreme point of the fuselage; thus, the center is used for payload, which makes the structure energy efficient. Disadvantages: when using the design for a pilot aircraft, an increase in carrying capacity will require an increase in size, engine power, the use of an electric drive entails a short flight time, there is no possibility of installing additional equipment other than video surveillance systems.

A technical solution is known according to patent RU 36345 U1 dated 02.12.2003. This device includes a two-part housing mounted on a shaft and separated by satellites; a cab located on top; two rotors located one above the other, the upper screw with the ends of the blades fastened together by a flat movable ring, forming the upper open part of the body, and the lower screw located in the body and the outer ends of its blades fastened along the ring with a vertical strip; four engines designed to rotate the screws and stabilize against rotation of the cab, located in the housing; the lower part of the housing is rigidly fixed with the upper screw and having a. their upper part is horizontal slit-like openings with petals located in them mounted on torsions, and in the lower part there is a nozzle, in the region of which a retractable landing device is located in the lower part of the shaft, control petals are placed under the nozzle. The disadvantage of such an aircraft is its structural complexity, which means low reliability. So, the drive rotation of the screws from different engines creates different torques, resulting in rotation of the cab. The stabilization of rotation, which in this model is provided by two additional engines. This not only complicates, but also complicates the design, which leads to increased fuel consumption in flight. At the same time, the need for constant speed adjustment to compensate for the rotation of the engine cabin when changing the flight mode complicates the control of the device. The control petals located on the torsion bars in slit-like horizontal holes during a change in the lifting speed of the apparatus spontaneously also change their position. This occurs as a result of the vertical displacement of the outer part of the upper screw, and with it the lower part of the housing and the slit-like holes themselves, from the inner platform on which the torsion bars are located, as a result, the design of the apparatus and its control become more complicated.

A technical solution is known according to the patent for utility model RU 84824 U1 dated January 26, 2009, “Aircraft of vertical take-off and landing”, including a cabin mounted on a shaft, a body consisting of two parts, the upper of which is open and represents the upper screw, the ends the blades of which are fastened together by a movable ring, and the bottom is rigidly fixed to the top, the motors located inside the body and the lower screw, the outer ends of the blades of which are fastened in a ring located in the lower part of the body of the nozzle, landing device stst and petals of management. The cab is rigidly fixed to the shaft, in the case there is an additional gearbox connected to the engines and transmitting rotation to the screws and stabilizer wings, and the landing gear is combined with the control petals.

Disadvantages: the complexity of the design, especially the screw group, the large size to ensure a given carrying capacity, the inconvenience of landing the pilot, the inconvenience or inability to place additional equipment.

Closest to the claimed utility model is a technical solution according to the source: http://www.membrana.ru/articles/technic/2007/07/04/190200.html dated July 4, 2007 under the name "Flying Saucer M200X" (US ) containing a platform, a fuselage, eight Rotapower engines with a capacity of more than two horsepower per 453 grams of its weight, eight propellers in an annular rim, a hull, a cockpit, and a pilot's seat. The diameter of the plate is 3 meters, the height is about 1 meter. Cruising speed of 80-120 km / h, cruising range of 160 km, flight altitude of 3 m. Manual control, with the participation of electronics. Disadvantage: a solid body (fuselage) increases the weight of the device, respectively, it requires more engine power, high energy consumption, increased noise from eight engines worsens the working conditions of the pilot, low mobility in cramped flight conditions, cumbersome layout, high cost.

The technical task of the claimed utility model is the creation of a small-sized, mobile, safe and easy-to-use aircraft structure.

To achieve this task, a technical solution is proposed, according to which the aircraft consists of a basic supporting platform of a frame structure, cross type. The frame is made of lightweight profiled materials (for example, rolled metal from duralumin). Four aircraft engines with multi-blade propellers in annular frames are installed at the end sites of the frame cross beams. Bottom ring frames have protective arcs. The propellers are pulling, directed upward, the plane of rotation of the propellers is horizontal. From below, parking supports are attached to the base platform. It is possible to install small diameter wheels on the supports to enable the apparatus to be moved on the ground or on paved grounds. From above, in the middle of the carrier platform, a structure is installed on the mounting platform to accommodate the pilot, passenger and cargo.

Depending on the task of this device, different layouts of the pilot's seat, passenger and the place of cargo transportation are possible. An option that repeats the generally accepted form of the motorcycle body, in which the pilot and passenger are placed on the seat, and the cargo is placed in closed side containers. An option for transporting small loads, according to which the pilot is seated on the seat, and the passenger seat is replaced by a loading platform, as well as the option of placing the pilot and passenger in the cockpit.

Any version of the design of the placement of the pilot and passenger in the upper part is equipped with a parachute-type rescue system, which is activated automatically when the normal operation of the propeller-driven groups of a device is interrupted and there is a possibility of flight disruption and crash of the device.

Four propellers are used in the design of the apparatus - two propellers with an operating mode of rotation clockwise and two propellers with an operating mode of rotation counterclockwise. This configuration is necessary to compensate for the torque that occurs when the propeller rotates, trying to deploy the device. The presence of two propellers rotating in one direction and two in the other compensates for this torque.

The flying motorcycle is equipped with an electronic-digital unit, which provides automatic control of the position of the device in the air horizontally and vertically by supplying control signals to aircraft engines. The indicated unit uses data from several electronic sensors and calculates the rotation speed for each individual propeller, also compensates for external influences, such as wind, and ensures the transfer of executive commands to aircraft engines from the control devices of the device. Control devices are located on the steering wheel.

Effect: the claimed utility model provides for the creation of a small-sized, mobile, safe and easy-to-use aircraft structure.

The technical result is achieved due to the fact that the claimed design of a flying motorcycle contains a basic load-bearing platform of a cross-type frame structure, on the end platforms of the cross beams of which four aircraft motors with multi-blade propellers are installed in annular frames, equipped with protective arches from below, pulling propellers pointing upward, plane of rotation horizontal propellers, two propellers with an operating mode of rotation clockwise and two propellers with an operating mode of rotation counterclockwise Relkom; parking supports are attached from below to the base platform, on which wheels of small diameter are installed to enable the apparatus to move on the ground or on paved grounds; from above in the middle of the supporting platform on the mounting platform, a structure is installed to accommodate the pilot, passenger and cargo; contains an automatic parachute rescue system, which is located in the upper part of the structure; contains an electronic-digital unit that provides automatic control of the position of the device in the air horizontally and vertically by supplying control signals to aircraft engines, using data from electronic sensors and calculates the speed of rotation for each individual propeller, compensates for external influences, such as wind, ensures the transfer of executive commands to aircraft engines from the control devices of the device; control devices are located on the steering wheel. A flying motorcycle can be additionally equipped with video surveillance and fixation devices, instrumentation, additional lighting devices that are mounted in the lower nose of the structure to accommodate the pilot or on the carrier frame to the right and left of the pilot's seat or cockpit. Also on the carrier frame of the device to the right and left of the structure for placing the pilot are fastening elements for transporting oversized long cargo.

The essence of the claimed utility model is explained by the images in figures 1-5, where in figures 1-3:

1 - carrier platform;

2 - four groups of aircraft engines with multi-blade propellers;

3 - protective ring guard screws;

4 - parking supports;

5 - protective arcs;

6 - a motorcycle (case) or a design that repeats the shape of a motorcycle;

7 - automatic parachute rescue system;

8 - cargo platform;

9 - cockpit of the pilot and passenger.

Figure 4, 5 shows the layout of the engines:

figure 4 - forward beam of the first motor, where 1, 2 - engines with clockwise rotation, 2, 3 - engines with counterclockwise rotation;

figure 4 - forward "collapse" between the beam of the first and third motors, where 1, 2 - engines with clockwise rotation, 2, 3 - engines with counterclockwise rotation.

Application (see figures 1, 2, 3). A flying motorcycle consists of a base carrier platform (1) of a frame structure (Figs. 1, 2, 3) of a cross type. The frame is made of lightweight profiled materials, for example, rolled metal from duralumin. Four aircraft engines with multi-blade propellers (2) in annular frames (3) are installed at the end sites of the frame cross beams. Bottom ring frames have protective arcs (5). The propellers are pulling, directed upward, the plane of rotation of the propellers is horizontal. From below, parking supports are attached to the base platform (4). It is possible to install small diameter wheels on the supports to enable the apparatus to be moved on the ground or on paved grounds. At the top in the middle of the carrier platform, a structure (6) is installed on the mounting pad to accommodate the pilot, passenger and cargo. This design can be performed in various versions: a variant that repeats the generally accepted form of the motorcycle body (Fig. 1, item 6), in which the pilot and passenger are placed on the seat, and the cargo is placed in closed side containers; an option for transporting small loads (Fig. 2), in which a pilot is placed on the seat, and the passenger seat is replaced by a cargo platform (Fig. 2, pos. 8); the option of placing the pilot and passenger in the cockpit (Fig.3 pos.9). Any version of the design of the placement of the pilot and passenger in the upper part is equipped with a parachute-type rescue system (7), which is triggered automatically in case of violation of the normal operation of the propeller groups of the device and there is a possibility of disruption of the flight and the fall of the device.

Four propellers are used in the design of the apparatus - two propellers with an operating mode of rotation clockwise and two propellers with an operating mode of rotation counterclockwise. This configuration is necessary to compensate for the torque that occurs when the propeller rotates, trying to deploy the device. The presence of two propellers rotating in one direction and two in the other compensates for this torque. In the attached diagram of FIGS. 4, 5, the arrangement of propellers on engines with numbers 1-2 install propellers with a working rotation in the clockwise direction, and on engines with numbers 3-4 install propellers with a working rotation in a counterclockwise direction. Since an equal number of propellers rotate simultaneously in opposite directions, the forces between them are equalized and this allows the device to steadily soar in the air without rotating around its axis.

The inventive device is equipped with an electronic-digital unit, which provides automatic control of the position of the device in the air horizontally and vertically by supplying control signals to aircraft engines. It uses data from several electronic sensors and calculates the rotation speed for each individual propeller, also compensates for external influences, such as wind, and also provides the transfer of executive commands to aircraft engines from the control devices of the device.

In flight, the device occupies a horizontal position relative to the surface of the earth, can hover over a specific place, move left, right, forward, backward, up and down, rotate around its vertical axis. To fly in any direction, the device must go out of balance, which increases the speed of rotation of the propellers, the opposite direction of movement. This makes the device lean over and start moving in that direction. The rotation in place is due to the imbalance of speed between the opposite pairs of propellers, one opposite pair rotates faster, and the other opposite pair slows down a little. Thus, the apparatus is rotated while maintaining the height at which it is located. Safety of use is ensured by an automatic parachute rescue system, as well as protective rings around the propellers.

The inventive aircraft can be equipped with additional video surveillance and fixation devices, instrumentation, additional lighting devices that can be mounted in the lower bow of the cockpit (Fig. 1, 2, item 6; 3, item 9) or the supporting frame of the apparatus to the right and left of the cockpit (Fig. 1, 2, 1). Also, on the supporting frame of the device to the right and left of the cockpit (Fig. 1, 2, 1), fastening elements (grips) can be located for transporting oversized (long) cargo that does not fit into standard closed side containers. When performing the apparatus of FIG. 2, the cargo platform is equipped with soft straps for securing the cargo; lock-type grips for fastening and holding a closed-type cargo container or a special chair for the emergency transportation of a sick person in the emergency medical service or the Ministry of Emergencies.

The inventive utility model can be used as an individual air vehicle; as an air vehicle of emergency response services, monitoring and traffic control, monitoring of state borders and all kinds of objects of special importance, search work during natural disasters and technological disasters, fires in the city and in the forest, monitoring events with a large crowd of people. The relatively small size of the device and the protective ring frames around the propellers allow the use of this device in cramped flight conditions where there is a possibility of direct contact between the propeller blades and the obstacle.

Thus, the design of the proposed flying motorcycle with small dimensions provides stability, mobility, the ability to transport small loads, reliable, convenient and safe to use.

Claims (10)

1. A flying motorcycle, including a base support platform, motors, seat, control system, characterized in that it contains a base support platform of cross-type beams, at the end platforms of the cross beams of which motors with pulling multi-blade propellers located in ring frames with protective arc from below; pulling propellers directed upward with a horizontal plane of rotation, at least two propellers with an operating mode of rotation clockwise and at least two propellers with an operating mode of rotation counterclockwise; parking supports are attached from below to the base platform; on top in the middle of the base carrier platform on the mounting platform, a structure is installed to accommodate the pilot, or the pilot and passenger, or the pilot and cargo, including the seat for the pilot, or the pilot and passenger; automatic parachute rescue system is located in the upper part of the structure; the control system has an electronic-digital unit that provides automatic control of the position of the device in the air horizontally and vertically by supplying control signals to motors, using data from electronic sensors and calculating the speed of rotation for each individual propeller, and compensating for external influences, ensuring the transfer of executive commands to motors from motorcycle controls; control devices are located on the steering wheel. 2. The flying motorcycle according to claim 1, characterized in that the motors are located symmetrically at least two to the right and left of the central axis of the structure, which coincides with the motion vector, and the fourth and second behind, and the propellers of the first and second motors rotate clockwise, and the propellers of the third and fourth rotate counterclockwise, while the twin motors with different directions of rotation of the propellers in front and behind create unidirectional air flow. 3. The flying motorcycle according to claim 1, characterized in that the motors are configured forward by the beam of the first motor, the first and second motors, the propellers of which rotate clockwise, are located on the central axis of the structure, which coincides with the motion vector, front and rear, respectively, and the third and fourth, the propellers of which rotate counterclockwise, are located on the right and left symmetrically to the central axis of the structure, which coincides with the motion vector. 4. The flying motorcycle according to claim 1, characterized in that the motorcycle casing or a structure repeating the shape of the motorcycle casing installed in the central part of the base carrier platform comprises a motorcycle frame, a fuel tank, seats and an automatic rescue system. 5. The flying motorcycle according to claim 1, characterized in that in the central part of the base carrier platform a motorcycle body or a structure repeating the shape of the motorcycle body is used, with two seats for the pilot and passenger, while the parachute-type automatic rescue system is located in the upper part behind passenger seat. 6. The flying motorcycle according to claim 1, characterized in that in the central part of the base carrier platform a motorcycle body or a structure repeating the shape of the motorcycle body is used, with one seat for the pilot and a cargo platform located behind the pilot’s seat, while the automatic parachute rescue system type located in the upper part behind the pilot's seat. 7. The flying motorcycle according to claim 1, characterized in that the Central part of the base carrier platform in front, top and rear is protected by a cabin containing the pilot's and passenger's seats; while the automatic parachute rescue system is located in the upper part of the cab lid. 8. The flying motorcycle according to claim 1, characterized in that small diameter wheels are mounted on the parking supports to enable the apparatus to be moved on the ground or paved areas. 9. The flying motorcycle according to claim 1, characterized in that it is equipped with video surveillance and fixation devices, instrumentation, additional lighting devices that are mounted in the lower nose of the structure to accommodate the pilot or on the base carrier platform symmetrically to the right and left of the center. 10. The flying motorcycle according to claim 1, characterized in that on the base carrier platform symmetrically to the right and left of the center are fastening elements for transporting oversized long cargo.