Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
  • B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C39/00—Aircraft not otherwise provided for
  • B64C39/08—Aircraft not otherwise provided for having multiple wings

Definitions

• the invention relates to aviation, namely, to vertical take-off and landing aircraft (VTOL) and aircraft.
• VTOL vertical take-off and landing aircraft
• VTOL aircraft maintaining a horizontal position of the fuselage as in cruising flight
• VTOL vertical take-off and landing
• the indisputable advantage of “tailsitters” was considered to be higher weight efficiency and reliability, since they do not have mechanisms for turning engines and propellers.
• a quadrocopter which belongs to the class of multicopters, which is a functional analogue of a helicopter (Erokhin E., Kolomiets A. Multicopters: new ed.) http://www.uav.ru/Articles July, 2016).
• the lifting force of a quadcopter is created by four propellers located at the vertices of a quadrangle, usually a square, and driven by individual electric motors (EM). Therefore, rechargeable batteries or fuel cells are used as an energy source, which are usually located in the geometric center of the device.
• the control system and payload are also located there.
• the short time of transient processes characteristic of the electric motor provides the quadcopter with acceptable stability and controllability characteristics when using propellers without propellers.
• the quadcopter while maintaining the functionality and efficiency of a helicopter, turns out to be simpler in design, more reliable in operation and cheaper in cost.
• a quadcopter has a low maximum flight speed, usually no more than 100 km/h.
• the quadcopter is capable of providing high efficiency of the GDP modes, but loses to the classical aircraft design in cruising flight.
• the basis of the proposed technical solution is the task of ensuring high efficiency of vertical takeoff and landing modes while maintaining good performance characteristics in cruising flight.
• the problem was solved in an aircraft with vertical take-off and landing, containing a fuselage with a pilot’s cabin, three ring fans are fixed in the upper part of the fuselage, placed on it in the shape of a triangle, with two engines with propellers coaxially installed in each ring, in addition, the aircraft has two triangular wings with cut ends and a stabilizer attached to the lower part of the fuselage in such a way that the vertical the planes of the wings and stabilizer are located on the lines of the axes of the fans, the elevons are fixed on the lower part of the wings, and the rudder is installed on the lower part of the stabilizer; landing pneumatic shock-absorbing legs are located on the outer vertical ends of each wing and stabilizer; in addition, the aircraft control system is located in the fuselage, and on the wings there is space for the location of weapon suspension units.
• a wing with a large area provides greater lift during horizontal movement at speeds of more than 150 km/h, while saving energy consumption and increasing flight range.
• the large propeller sweep area and low center of gravity ensure stability during vertical hovering and movement at low speeds.
• the use of air ring fans increases operational safety and increases draft by 20% and the efficiency of the system as a whole. As a result, lifting force increases, speed capabilities and control efficiency increase.
• the noise level of the device in urban environments and the detection range during special operations are significantly reduced
• the aircraft control system be mechanical for use in all cases as a backup system control in case of failure of the main electronic system and is an additional option for the device.
• the aircraft control system be on autopilot if the aircraft is used as a vehicle in the form of a taxi for citizens.
• the aircraft control system be unmanned when performing military and rescue operations, when the presence of a pilot is risky or his presence is not required to perform the necessary operations.
• Fig. 1 is a schematic general view of a vertical take-off and landing aircraft constructed in accordance with the present invention.
• Fig. Figure 2 shows the stage of aircraft movement - phase I. Vertical take-off.
• FIG. Figure 3 shows the stage of aircraft movement - phase II. Acceleration and climb with a change in position from vertical to horizontal.
• Fig. Figure 4 shows the stage of aircraft movement - phase III. Horizontal watering. (15-18 degrees).
• Fig. Figure 5 shows the stage of aircraft movement - phase IV. To land, the device slows down and changes its position from horizontal to vertical.
• Figure 6 shows the stage of aircraft movement - phase V. Landing in a vertical position.
• the elevons 15, 16 are fixed, respectively, and the rudder 17 is installed on the lower part of the stabilizer 14.
• the aircraft control system can be mechanical, manually controlled, autopiloted or unmanned.
• the pilot's cabin can be sealed and open. In this case, the person sits in a chair and fastens his seat belts. Protective equipment is required for flying.
• a vertical takeoff and landing aircraft works as follows.
• the aircraft is lifted by starting all fans 3, 4, 5 of the propulsion system, the propellers 6, 7, 8, 9, 10, 11 are set into rotation, resulting in a lifting force in the vertical plane, and the aircraft rises into the air.
• a control system which moves the elevons 15, 16 to the lower position, after which the aircraft, with a set of speed, moves to a horizontal position.
• the elevons 15, 16 are transferred to the neutral position. Maneuvering in the horizontal plane is carried out by changing the position of the rudder 17, and for For the vertical plane maneuver, wings 12, 13 with control elements for elevons 15, 16 are used.
• the proposed technical solution is characterized by high maneuverability, has good speed characteristics, lifting force and control efficiency.
• the advantage of the aircraft is its high speed, maximum (350 km/h) and cruising (-250 km/h) speed, efficiency, low noise level, high stability in any flight mode, safety (if one of the engines in each fan fails, the second one will work in emergency mode), also all aircraft have an emergency parachute rescue system for the safe landing of the aircraft along with a passenger or cargo.
• the large load capacity (more than 200 kg) allows for armoring (protection from bullets of up to 7.62 mm caliber) of vital components and mechanisms of the aircraft.
• the proposed technical solution has a wide range of uses.
• the most successfully proposed invention can be used as a vertical take-off and landing aircraft (aircraft) without an airfield base.
• the main area of application proposed by VTOL aircraft is the organization of air transportation without being tied to the existing airfield network and without the need to build new runways.
• This aircraft design can be used as a versatile platform to perform various missions listed below, as well as for cargo delivery. It can be used as a military, rescue, police, or passenger vehicle. Can also be used as a civilian city vehicle with automatic (unmanned), remote, manual control with a sealed cabin with a life support system and climate control, airbags and a multimedia system to move one passenger over a distance of up to 100 km, for use as a taxi or private transport, as a rescue apparatus with a winch with automatic (unmanned), remote, manual control, with an open cabin, for evacuating people from hard-to-reach places in emergency conditions, as a quick response fire apparatus with automatic (unmanned), remote control, with a capsule up to 200 liters for fire extinguishing, on high floors of high-rise buildings or in hard-to-reach places, as a police vehicle with automatic (unmanned), remote, manual control, for quick response in urban conditions, rapid delivery of special forces, for video surveillance of troublemakers, can be equipped with floodlights and special equipment.
• the declared technical solution can be used on the battlefield in wartime, namely for reconnaissance, patrolling, landing, evacuation of the wounded from the battlefield, bombing ground targets, neutralization of air targets, neutralization of surface targets, use as a projectile aircraft, cargo transport.
• the use of the proposed aircraft design will ensure a high level of versatility of use, by eliminating the need to build special airfields and ensuring operation even from unequipped sites, including from fishing vessels, from unpaved sites, for example, in rural areas.

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• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Toys (AREA)
• Load-Engaging Elements For Cranes (AREA)

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Publications (1)

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Citations (6)

• 2022
  • 2022-06-02 UA UAU202201863U patent/UA151311U/uk unknown
  • 2022-07-06 WO PCT/UA2022/000032 patent/WO2023234909A1/ru unknown

Patent Citations (6)

Non-Patent Citations (2)

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