RU193778U1 - Unmanned aerial vehicle - Google Patents

Abstract

The utility model relates to unmanned aerial vehicles (UAVs) and can be used as part of an unmanned aerial system. More than 98% of the details of the hull of an aircraft (LA) consist of composite materials to reduce the weight of the entire product. The modular design of the device includes the following parts: bow, center and tail, wing consoles, power unit module (SU), tail unit. This solution allows to reduce the transported volume of the product and carry out modular repairs. The payload and target load, as well as the transmitter / receiver are located in the nose of the fuselage. In the rear part there are blocks with electronic equipment and a battery. Each unit is sealed with the possibility of heat removal. As a power plant, which is installed in the power plant module (SU), an internal combustion engine (ICE) with a pushing screw is used. To start the engine and charge the battery, a starter-generator is installed. Air cooling of the power plant occurs through the side and upper windows of the SU module. For takeoff and landing a wheeled three-post chassis is used. The main fuel tank (TB) is located in the central part of the aircraft body. The internal volumes of the fuselage and wing can further increase fuel reserves, which has a positive effect on the duration of the flight. The skin (shell) of the aircraft is a composite sandwich structure made of fiberglass. The body of the apparatus is additionally reinforced in the most loaded places with carbon fiber. These places are the nose, lower, and tail parts of the fuselage, as well as the tail unit of the aircraft. All operations for the manufacture of aircraft body parts are carried out in formative elements (matrices). The method of vacuum infusion and manual molding is used.

Description

The utility model relates to unmanned aerial vehicles (UAVs) and can be used as part of an unmanned aerial system.

A useful model of an unmanned aerial vehicle is known (patent RU N 2380286 C1, IPC ВСС 39/04, 01/27/2010), including a fuselage with a two-beam tail part, a propeller-type propulsion system, a wing, horizontal and vertical tail, steering cars and chassis. The power part of the fuselage is made in the form of a metal truss and contains a compartment with on-board electronic equipment and a compartment with the main fuel tank. The following parts are attached to the power part of the fuselage: in the fore part - a truss, in the rear part - a motor frame, from above in the middle part - wing spars. The spars are made tubular with the possibility of their use as an additional fuel tank. Tail beams are made in the form of metal pipes. The vertical tail is made in the form of two inclined keels with rudders and placed at the ends of the tail beams. Between the beams placed horizontal tail, made in the form of a stabilizer with elevator. The fuselage skin consists of a front fairing, a main fairing and an engine hood. An increase in the duration and altitude of the flight is achieved with a high ratio of payload to take-off weight, and improvement of flight technical and operational characteristics.

The disadvantages of this model of the aircraft is the presence of a two-beam tail, which creates a small amount of internal space of the hull, the rectangular wing does not allow to achieve high flight speed.

The closest analogue in design is a utility model of an unmanned aerial vehicle, (patent RU N 143213 U1, IPC ВСС 5/02, 02/25/2014), consisting of a fuselage with large extension arms, closed power plant, V-tail, tricycle retractable landing gear. The internal combustion engine (ICE) is located near the center of mass of the UAV, and the torque to the pushing screw is transmitted through the universal joint. The screw is located in the annular channel. Fuel tanks (TB) are located in the fuselage and in the wing.

The disadvantages of this model: the annular channel of the screw-fan complicates and complicates the design; placing the power plant closer to the center of the fuselage reduces the internal net volume of the hull; the use of cardan transmission, chassis mechanization makes the case heavier and reduces the reliability of the device.

The problem, which the real utility model is aimed at, is to create UAVs with improved aerodynamic and operational characteristics.

The technical result achieved using this utility model is aimed at improving operational characteristics leading to an increase in the duration and range of flight.

The technical result is achieved by the fact that the UAV, made according to the airplane scheme, has a fuselage, wing consoles, a closed power unit, ICE with a pushing propeller, tail unit, three-post chassis, blocks with electronic equipment, the main fuel tank located in the module of the central part of the body, fuel tanks in the wing consoles, the fuselage consisting of composite materials, and the device itself has a modular structure and consists of a separate module of the bow, center, tail and power unit module, all the muzzle consists of composite shells and stiffeners, while in the bow module there are containers for payload and an additional fuel tank, the tail unit is T-shaped, the wing with tips has a slight sweep, the electronic blocks are sealed and installed with the possibility of heat removal.

The use of modern computer-aided design systems allowed us to develop a design with optimal weight and size and aerodynamic performance.

The utility model is illustrated by drawings, where

in FIG. 1 - shows a General view of the aircraft;

in FIG. 2 - a layout of units and housing elements is presented.

When designing this aircraft, goals were set to achieve optimal flight performance (LTH): time, flight range and payload mass.

For UAVs, both civilian and military, there is a conditional classification by take-off weight: light (up to 20 kg), medium (20 to 200 kg), heavy (more than 200 kg). Most aircraft belonging to the middle class are made according to the airplane (traditional) scheme, i.e. lifting force is created due to the oncoming flow on the wing. The power plant is located in the rear.

The unmanned aerial vehicle contains (Fig. 1) a bow module 1, a central module 2 and two wing consoles 5 having ailerons 6 and servos 18, a tail module 3 having vertical and horizontal tail 8, a rudder 10 and a elevator 9 A power unit 4 is attached to the rear part, including (Fig. 2) ICE 17, an input device 11 and 12, a thrust screw 13. The front landing gear 15 and the main landing gear 14. The wing consoles 5 and the center section 2 are fixed to each other carbon fiber tubes 19 and 20. The main blocks with p by the radio-electronic equipment located in the rear part 3, the transmitter-receiver 21 and the photo-video equipment 16 in the bow.

Due to the design features, the utility model has the following advantages. The bow module 1 allows you to place a container with a payload and additional TB. Additional TBs are located in the wing consoles 5. The wingtips 7 can reduce the inductive resistance of the UAV, and the relatively large areas of the wing 5 can increase the lift. ICE 17 with a pushing screw 13 are located in the power unit 4 to protect parts and assemblies from external influences. For effective cooling of the engine and units, air intakes 11 and 12 are installed.

The nose module 1, central 2, tail 3, power unit 4, as well as the wing 5, vertical 10 and horizontal 8 tail are made of composite shells by vacuum infusion and stiffeners made of carbon fiberglass and fiberglass by manual molding. Separate modules improve maintainability.

The tricycle landing gear 14 and 15 allows UAVs to take off and land from any hard and straight surface 10-15 meters long.

Wing consoles 5, horizontal tail 8, landing gears 14 and 15 have quick-detachable connections, which will improve UAV mobility and reduce transported dimensions. The fuselage modules can reduce the time for repair and maintenance.

Thus, the developed middle-class UAV has an increased range and duration of flight, as well as high performance due to the above-described structural changes: an increase in fuel volume due to wing tanks and an additional tank in the bow, the use of a wing with a relatively large area, the use of composite materials, the use of a modular fuselage design, equipment placement in airtight containers.

Claims (1)

The unmanned aerial vehicle, made according to the airplane scheme, has a fuselage, wing consoles, a closed power plant, ICE with a propeller, tail unit, three-post landing gear, blocks with electronic equipment, the main fuel tank located in the central module, fuel tanks in the wing consoles moreover, the fuselage consists of composite materials, characterized in that the apparatus has a modular structure and consists of a separate module of the bow, center, tail and power module, all modules with they remain from composite shells and stiffeners, while in the bow module there are containers for payload and an additional fuel tank, the tail unit is T-shaped, the wing with tips has a slight sweep, the electronic blocks are sealed and installed with the possibility of heat removal.

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