UA151311U - Aircraft with vertical takeoff and landing - Google Patents

Abstract

The aircraft with vertical take-off and landing includes a fuselage with a cabin, in the upper part of the fuselage three ring fans are fixed and placed on it in the shape of a triangle, while in each ring two engines with propellers are installed coaxially, in addition, the aircraft has two wings made of triangular with the ends cut off, and the stabilizer fixed to the lower part of the fuselage in such a way that the vertical planes of the wings and stabilizer are on the lines of the axes of the fans, the elevons are fixed to the lower part of the wings, and the rudder is mounted on the lower part of the stabilizer. At the same time, on the outer vertical ends of each wing and stabilizer there are landing pneumatic shock absorber legs, in addition, the aircraft control system is located in the fuselage, and there is a place on the wings for equipping it with removable weapons suspension units.

Description

The utility model belongs to aviation, namely to vertical take-off and landing (VTOL) aircraft, and can be used as a non-aerodrome-based vertical take-off and landing aircraft. The main field of application of the proposed LVZP is the organization of air transportation without being tied to the existing airport network and without the need to build new runways.

Many projects of LVZP that appeared in the second half of the 20th century are known (Ruzhytskyi 6.1.

American vertical takeoff planes. - M.: LLC "Astrel Publishing House", 2000. - 192 p.: ill.,

Hafer K., Zaks G. Technique of vertical take-off and landing. Prov. with him. - M: Mir, 1985. - 376 p., illustrations). At the same time, from the very beginning, all the layouts of LVZP that were developed could be attributed to two different types: LVZP that maintain the horizontal position of the fuselage both in cruise flight and in vertical take-off and landing (VZP) modes, as a rule, due to turning power plant and/or propellers and "Tailsitters" or, literally, "sitting on the tail" - LVZP, which do not have rotating power plants and/or propellers, and turn completely to a vertical position in the VZP modes. The undoubted advantage of "tailsitters" was considered higher weight efficiency and reliability, since they lacked mechanisms for turning engines and propellers. That is why such LVZPs attracted the attention of the military. For example, the Lockheed company developed the HEM-1 Baitop LVZP project for the US Navy (E.I. Ruzhitskyi. American vertical take-off aircraft. - M. LLC "Vydavnytstvo Astrel", 2000. - 192 p.: ill.). The peculiarity of this LVZP was the vertical position when finding the ground before take-off and after landing. For this, the LVZP had an X-shaped tail equipped with landing gear supports. Vertical take-off and landing (VZP) was performed due to the thrust of the propeller located in the nose part of the fuselage, which is driven by a gas turbine engine (GTM). After a vertical take-off, the LVZP gradually returned to a horizontal position and performed a cruising flight like a conventional aircraft. The advantage of this technical solution is the possibility of achieving high aerodynamic quality and good flight characteristics in cruising flight due to the large extension of the wing.

The main drawback is the low efficiency and poor controllability in the VZP modes, since here the control of the movement of the LVZP is provided only by the deviation of the aerodynamic rudders,

From what are blown by the jet of the screw. To create the necessary control moments, a high speed in the jet is required, and it can be achieved only by increasing the load on the swept area of the propeller, which reduces the efficiency of the propeller and increases fuel consumption at VZP modes.

There is also an aerial vehicle (LA), called a quadrocopter, belonging to the class of multicopters, which is a functional analogue of a helicopter (Yerokhin E., Kolomiets A.

Multicopters: a new type. Per:/Lumly.tsam.gy/apisiez/tiysorieg5.rai July, 2016). The lifting force of a quadcopter is created by four propellers located at the vertices of a quadrilateral, usually a square, and driven by individual electric motors (ED). Therefore, as a source of energy, batteries or fuel cells are used, which are located, as a rule, in the geometric center of the device. The control system and payload are also located there. An important feature of the quadcopter is that the axes of rotation of the propellers do not rotate relative to its design, and control forces and moments are created only by changing the thrust of the propellers. In this way, the quadcopter is fundamentally different from the helicopter, for the control of which it is necessary to equip the main rotor with a mechanical device for controlling the general and cyclic pitch, called in the domestic literature the yaw machine (AP). At the same time, an integral element of the design of the quadcopter is the electronic automatic stability improvement system (ASUU), which measures with the help of sensors (gyroscopes and accelerometers) the parameters of the aircraft's movement and regulates the thrust of the propellers by changing the instantaneous power (and rotation frequency) of the ED drives. It is the short time of transient processes inherent in ED that provides the quadcopter with acceptable stability and controllability characteristics when using propellers without AP. Thus, the quadcopter, while maintaining the functionality and efficiency of the helicopter, turns out to be simpler in design, more reliable in operation and cheaper in cost.

The main disadvantages of the quadcopter are the short range and duration of the flight, which is due to the insufficiently high energy capacity of modern batteries. In addition, like a helicopter, a quadcopter has a low maximum flight speed, usually no more than 100 km/h. Thus, the quadcopter is able to provide high efficiency of VZP modes, but loses to the classic aircraft scheme in cruising flight.

From the state of the art, no closest analogue identical to the proposed one has been found.

The basis of a useful model is the task of ensuring high efficiency of vertical take-off and landing modes while maintaining good flight and technical characteristics in cruise flight.

The task is solved by the fact that in an aircraft with vertical take-off and landing, which contains a fuselage with a pilot's cabin, in the upper part of the fuselage, three annular fans are fixed and placed on it in the shape of a triangle, while in each ring, two engines with propellers are installed coaxially. in addition, the aircraft has two triangular wings with truncated ends and a stabilizer fixed to the lower part of the fuselage in such a way that the vertical planes of the wings and the stabilizer are on the lines of the axes of the fans, on the lower part of the wings are fixed elevons, and on the lower part of the stabilizer is installed rudder, while on the outer vertical ends of each wing and stabilizer there are landing pneumatic shock absorber legs, in addition, the aircraft control system is located in the fuselage, and there is a place on the wings for the location of the weapons suspension units.

The pilot's cabin can be sealed.

The cockpit can be made open.

The aircraft control system can be made mechanical.

The aircraft control system can be operated on autopilot.

The aircraft control system can be made unmanned.

The implementation of a lightweight design with powerful electric motors in combination with the above features of the proposed useful model will allow you to quickly set this unit in motion, complete the task and land in almost any place. km/h., at the same time it allows to save electricity costs and increases the flight range. A large propeller sweep area and a low center of gravity ensure stability during vertical hovering and movement at low speeds.

The use of air ring fans increases the safety of operation and increases the thrust by 2095 and the efficiency of the system as a whole. As a result, lifting power increases, speed capabilities and control efficiency increase. The noise level of the device in urban conditions and the detection range during special operations are significantly reduced.

З The proposed useful model is explained by drawings.

In fig. 1 schematically depicts the general appearance of the aircraft.

In fig. 2nd stage of aircraft movement - phase I. Vertical takeoff.

In fig. From the stage of movement of the aircraft Phase II. Acceleration and height gain with a change in position from vertical to horizontal.

In fig. 4th stage of aircraft movement Phase III. Horizontal flight. (15-18 degrees).

In fig. 5th stage of the aircraft movement Phase IM. For landing, the device slows down and changes its position from horizontal to vertical.

In fig. 6th stage of aircraft movement Phase U. Landing in a vertical position.

An aircraft with vertical take-off and landing includes a fuselage 1 with a sealed cabin 2. On the upper part of the fuselage 1, three annular fans 3, 4, 5 are fixed, placed in the shape of a triangle. In each ring of fans 3, 4, 5, two engines are installed coaxially propellers, namely, propellers 6, 7 are installed in fan C, propellers 8, 9 are installed in fan 4, and propellers 10, 11 are installed in fan 5. Two wings are attached to the lower part of the fuselage 1 12, 13th stabilizer 14. Wings 12, 13 are triangular with cut ends and are fixed together with the stabilizer 14 on the lower part of the fuselage in such a way that the stabilizer 14 is located on the axis lines of fans 3, 4, 5. On the lower part of the wings 12, 13 fixed elevons 15, 16, respectively, and a rudder 17 is installed on the lower part of the stabilizer 14. On the outer vertical ends of each wing 12, 13 and stabilizer 14 there are positions metal pneumatic damping legs 18, 19, 20. The aircraft control system 21 is placed in the fuselage 1 behind the pilot's cabin 2, and on the wings 12, 13 there is a place for equipping the weapons suspension units. The aircraft control system can be mechanical, manual, autopilot and unmanned.

The cockpit for the pilot can be made open. In this case, the person sits in the chair and fastens the seat belts. Protective equipment is required for flights.

The proposed utility model functions as follows.

The plane is lifted by starting all fans 3, 4, 5 of the engine, propellers 6, 7, 8, 9, 10, 11, which are rotated, as a result of which there is a lifting force in the vertical plane, and the plane rises into the air. With the help of the control system, which is carried out 60 by transferring the elevons 15, 16 to the lower position, after which the aircraft with the set speed goes to a horizontal position. When taking a horizontal position, the elevons 15, 16 are transferred to a neutral position. Maneuvering in the horizontal plane is carried out by changing the position of the rudder 17, and for maneuvering in the vertical plane, the wings 12, 13 with the control elements of the elevons 15, 16 are used. To land the plane, it is necessary to reduce the speed of the fans 3, 4, 5 and transfer the elevons 15, 16 to the upper a position that will ensure a quick reset of the speed and acceptance of the vertical position of the unit. After that, the elevons 15, 16 are transferred to the neutral position, and by maintaining certain revolutions of the screws 6, 7, 8, 9, 10, 11, landing is carried out on the shock-absorbing legs 18, 19, 20.

This machine can be used as a universal platform for the various tasks listed below, as well as for the delivery of goods. Military, rescue, police, passenger, that the speed of the device can be more than 300 km/h. Can be used as a civilian urban 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 up to 100 km, for use as a taxi or private transport, as an automatic (unmanned), remote, hand-operated winch rescue apparatus, with an open cabin, for the evacuation of people from hard-to-reach places in emergency conditions, as an automatic (unmanned), remote-controlled rapid response fire apparatus, with a capsule containing up to 200 liters of fire extinguishing agent, on high floors of high-rise buildings or in hard-to-reach places, as a police apparatus with automatic (unmanned), remote, manual control, for quick response in urban conditions, quick delivery of special forces, video surveillance of violators of order, will be equipped with special signals, searchlights and special means

The declared aircraft can be used on the battlefield and in wartime, namely - reconnaissance, patrolling, landing, evacuation of the wounded from the battlefield, bombing of ground targets, neutralization of air targets, neutralization of surface targets, use as a projectile aircraft, cargo transport. A large load capacity (more than 200 kg) allows you to protect (protection against bullets with a caliber of up to 7.62 mm) vital components and mechanisms of the device.

Z The advantages of the aircraft are high maximum (350 km/h) and cruising (7250 km/h) speeds, economy, low noise level, high stability in any flight mode, safety (if one of the engines in each fan fails, the other will work in emergency mode), all aircraft also have an emergency parachute rescue system for safe landing of the aircraft together with a passenger or cargo. The absence of liquid fuel and other combustible substances on board increases the survivability of the aircraft under fire from small arms, which makes it possible to remain in flight even in the event of direct hits to any parts of the aircraft except for engines, propellers, main boards and electronics, vital organs of the pilot "in this case, it is possible to intercept control of the operator or autonomous software of the device and evacuation from the combat zone), as well as the main control systems of the device.

The use of an all-electric propulsion system gives a significant advantage over jet-gasoline competitors due to the absence of a thermal trace in the infrared range (hot engines, exhaust, jet), which will avoid the guidance of systems

Anti-aircraft defense of the enemy and will significantly reduce the possibility of detection due to thermal imagers and other systems in the infrared range. Another advantage of the design is the low cost of the device and operation.

The use of the proposed aircraft design will ensure a high level of universality of application, by eliminating the need for the construction of special airfields and ensuring operation even from unequipped sites (including from fishing vessels, from dirt sites, for example, in rural areas, etc.). In addition, the proposed useful model is characterized by high maneuverability, has good speed characteristics, lifting power and control efficiency.

Claims (5)

USEFUL MODEL FORMULA 1. An aircraft with a vertical take-off and landing, containing a fuselage with a cabin, in the upper part of the fuselage, three annular fans are fixed and placed on it in the shape of a triangle, while in each ring, two engines with propellers are installed coaxially, in addition, the aircraft has two the wings, made triangular with cut ends, and the stabilizer fixed on the lower part of the fuselage in such a way that the vertical planes of the wings and the stabilizer 60 are on the lines of the axes of the fans, on the lower part of the wings are fixed elevons, and on the lower part of the stabilizer a rudder is installed, while on the outer vertical ends of each wing and stabilizer there are landing pneumatic shock absorber legs, in addition, the fuselage houses the aircraft control system, and the wings have space for equipping it with removable weapons suspension assemblies. 2. The aircraft according to claim 1, which differs in that the cabin is sealed. Z. The aircraft according to claim 1, which differs in that the cockpit is made open. 4. An aircraft according to any of claims 1-3, which is characterized by the fact that the aircraft control system is mechanical. 5. An aircraft according to any of claims 1-3, which is characterized by the fact that the aircraft control system is performed on an autopilot. b. The aircraft according to any of claims 1-3, which is characterized by the fact that the aircraft control system is made unmanned. 433 dlteesssetn o? morning and M ia Shan sk sk o y" X h HM DEN t odi y iva mash SHE POL NY oo oo I She ho Shi N r nn scha BUT: I I her po a I Zh. 1: day of ShK Gi i she 12 ri anna x shki: IZ feny, V V | EK un nen ČE Ta ZE xx CHOKU not yet i ny ZI yet Days i. shi ee SHY p te ; hv i A v SCHE I she: i KE Esh v. En Fig. 1