RU144446U1 - CONSOLE OF THE WING OF THE PLANER OF THE AIRCRAFT USING IN THE POWER INSTALLATION PHOTOELECTRIC CONVERTERS - Google Patents

Abstract

Wing console of an aircraft glider using a power supply system based on photoelectric converters, containing panels of photoelectric converters, power transverse and longitudinal sets of the wing console, and a skin, characterized in that the panels of photoelectric converters are installed inside the structure of the wing console and are rotatable, while the wing console skin is made of transparent, and the power transverse and power longitudinal sets of the wing console are covered with reflective material.

Description

The technical field to which the utility model relates.

The utility model relates to the field of aeronautics, namely, to the design of aircraft gliders, in particular, to the design of aircraft using electric motors operating on the energy received from photoelectric converters (solar panels) as a power plant.

Photovoltaic converters used in the power plant of an aircraft are designed to convert the energy of solar radiation into electrical energy and use it to power electric motors, airborne equipment, as well as the battery charge of the aircraft.

State of the art

Many aircraft are known from the prior art that use a renewable power system based on solar panels consisting of photovoltaic cells (PECs) as a power plant. As a rule, solar panels are located on the surface of the bearing, stabilizing and / or controlling parts of the airframe, as well as on the fuselage of the aircraft.

From the application for the grant of a patent for the invention US 20060278757 A1, IPC B64C 37/02, publ. 12/14/2006, the twin-engine model of the aircraft, made of polymer composite materials, is known. On a well-known model of the aircraft, electric motors are installed, the power of which is provided by solar cells located on the upper surface of the wing.

The disadvantage of this solution is the impossibility of maximizing the energy received from the Sun, due to the installation of photovoltaic converters at non-optimal angles to the sun's rays, due to the geometry of the aircraft's airframe.

From publication US 5810284 A, IPC B64C 3/10, publ. 09/22/1998 a multi-engine aircraft is known that uses energy generated by solar panels as a source of electrical energy. A multi-engine aircraft is made according to the flying wing scheme, consisting of five sections. Light wood species, foamed polymeric materials and polymeric composite materials were used in the construction. Part of the casing is made of a thin polymer film.

The disadvantage of this solution is the impossibility of maximizing the energy received from the Sun, due to the installation of photoelectric converters at non-optimal angles to the sun's rays, due to the geometry of the airframe of this multi-engine aircraft.

The prior art also known aircraft using solar panels as a source of electrical energy. In the publication of patent US 4133501 A, IPC B64G 1/22, publ. 01/09/1979 a panel of a solar battery designed for a spacecraft is disclosed, made in the form of a single elastically deformable part. The specified panel is installed either in the curved curved position under tension with the abutment against the outer convex surface of the spacecraft, or in the expanded flat position, in which it protrudes from the outer surface, and the transition from the curved rolled position to the expanded position is due to the elastic expansion of the solar panel . In a curved curved position, the solar panel is held pressed against the outer surface of the spacecraft using locks mounted on this surface.

The disadvantage of this solution is the impossibility of maximizing the energy received from the Sun, due to the installation of photoelectric converters at non-optimal angles to the sun's rays, due to the geometry of the structure of the aircraft glider.

The closest analogue of the proposed utility model is an aircraft that uses solar energy as a source of electrical energy (see patent US 7762495 B2, IPC B64C 3/00, publ. 07.27.2010). The aircraft, which is the prototype of the proposed utility model, has bearing and control surfaces with a large elongation, a propulsion system and additional movable panels with photoelectric converters installed in the rear of the airframe, with the possibility of rotation around the tail beam. During the flight, panels with photoelectric converters, if possible, occupy a position perpendicular to the sun's rays, thereby ensuring the maximum power of the converted solar radiation.

The use of an additional panel with photoelectric converters negatively affects the flight path of the aircraft, as it is necessary to maintain a direct angle of incidence of sunlight on it, and the use of an additional panel affects the flight performance. An additional panel increases the mass of the aircraft and its resistance. In addition, the additional panel with photoelectric converters has a significant windage, which in the presence of a crosswind makes it necessary to fly with sliding in order to provide resistance to the deviation of the aircraft from a given flight path.

Utility Model Essence

The problem solved by the claimed utility model is the placement of the panels of photovoltaic cells (solar cells) inside the structure of the aircraft glider, with the possibility of rotation to obtain energy in the widest range of angles of incidence of sunlight, while minimizing the space occupied by photovoltaic cells, and without having a negative impact on the flight performance of the aircraft.

The proposed solution provides the ability to change the installation angles of the panels of photovoltaic cells relative to the design of the glider of the aircraft, which allows to obtain solar energy in the widest range of angles of incidence of sunlight.

The technical result of the proposed utility model is to maximize the resulting solar energy in the widest range of angles of incidence of sunlight.

This technical result is achieved by rotating the panels of the photoelectric converters to obtain energy in the widest range of angles of incidence of sunlight, with the smallest possible space occupied by the panels of the photoelectric converters, and also due to the absence of a negative effect on the flight performance of the aircraft, at least two wing consoles which contain photoelectric converters, power transverse and power longitudinal th sets wing console and trim, with the photoelectric converters are installed inside the structure of the wing console and arranged to be rotatable about the axis, wherein the wing panel skin is made transparent, and the transverse and longitudinal power wing console sets are covered with reflecting material.

Brief Description of the Drawings

Details, features, and advantages of this utility model follow from the following description of examples of implementation of the claimed aircraft using the drawings (Fig. 1-5).

In FIG. 1 shows a general view of the wing console.

In FIG. 2 shows a cross-section of a glider structure, view of a power element (wing spar).

In the figures, the positions indicate the following elements:

1 - upper transparent casing of the wing console;

2 - lower transparent casing of the wing console;

3 - spar of the front wing console;

4 - spar of the rear wing console;

5 - ribs;

6 - photoelectric converters;

7 - swivel cables;

8 - rotary rollers;

9 - nodes of the hinge of photovoltaic converters;

10 - wing console.

Utility Model Disclosure

The proposed solution (see Fig. 1) is to place the panels of the photovoltaic cells inside the airframe, for example, inside the wing console.

The wing console (10) of the aircraft glider is made according to the two-spar design and consists of the upper (1) and lower (2) skins, power longitudinal and power transverse sets. Elements of the longitudinal set include the front (3) and rear (4) side members, and the ribs (5) to the transverse one.

The upper surface of the wing console is made in the form of a casing (1), which is a thin polymer transparent film through which the sun's rays fall on the photoelectric converters (6). The skin of the wing console (1) also performs the function of protecting the photoelectric converters from external factors.

The lower surface of the wing console (10) is made in the form of a casing (2), which is a thin polymer transparent film for additional illumination of the lower surface of the photoelectric converters (8), as well as protecting the photoelectric converters from external factors.

Photoelectric converters (6) are made bilateral, i.e. provide the ability to receive sunlight from both sides. Due to this embodiment, photovoltaic converters (6) can convert the energy of solar radiation into electricity both from sunlight falling from above or from the side, and from rays reflected from the earth's surface, clouds, and the mirror surface of a longitudinal and transverse power set.

Photovoltaic converters (6) are sources of electricity necessary for many hours of continuous operation of an electric power plant, on-board equipment, steering gears, charge on-board batteries, payload, etc.

Elements of the longitudinal power set and the transverse power set are made according to the principle of truss design. To minimize shadow losses, the power longitudinal and power transverse sets of the proposed wing console of the aircraft are coated with a reflective material or composition, such as a mirror film, paint, etc.

The panels of the photovoltaic converters (6) are fastened to the design of the airframe console by means of a swivel located in the hinge assemblies (9) of the photovoltaic converters (6) (see Fig. 2), thus providing the necessary degree of freedom of one or another photovoltaic converter ( 6). Hinge assemblies (9) of photovoltaic converters are mounted on the power set of the wing console, in this case, on the front and rear spars.

The control panels of the photoelectric converters (6) are made using ropes (7) and a system of rotary rollers (8). The cables (7) are fixed, in turn, from two sides to each panel of the photoelectric converters (6). By tensioning one or another cable (7), the position of the panel of photoelectric converters (6) is changed relative to sunlight. The tension of the cables (7) is carried out by a drive (for example, based on an electric motor) through the rotary rollers (8).

In addition to position control, the described cable system can be used as part of a switching network that combines panels of photoelectric converters.

Changing the installation angles of the panels of photoelectric converters is carried out automatically by commands from the automatic control system of the aircraft, formed, in turn, depending on the current geographical location, time of year, altitude and direction of flight of the aircraft. In addition, the rotation of the panels of the photoelectric converters is carried out in such a way that they prevent shadowing of each other.

Claims (1)

The wing console of a glider of an aircraft using a power supply system based on photoelectric converters, comprising panels of photoelectric converters, power transverse and longitudinal sets of wing consoles, and skin, characterized in that the panels of photoelectric converters are installed inside the structure of the wing console and are rotatable, the wing console skin is transparent, and the power transverse and power longitudinal wing console sets are covered with reflective aterialom.