RU2242404C2 - Aviation complex (modifications) - Google Patents

Abstract

FIELD: aircraft fuel systems.

SUBSTANCE: the complex has a carrier aeroplane, located on the assembly of the external store of which is a separable unmanned flight vehicle with a cruise engine located in the cavity of its fuselage for its extraction to the working position behind the fuselage contours. The fuel systems of the carrier aeroplane and the unmanned flight vehicle are interconnected by a communication line with a detachable coupler, with stop valves installed before and after it. The fuel system of the unmanned flight vehicle at the inlet of the communication line has an additional squeezed elastic fuel tank, located in the cavity of the fuselage for spreading in the point of location of the extractable engine, and a system of fuel utilization from the elastic fuel tank.

EFFECT: enhanced unrefuelled range.

11 cl, 9 dwg

Description

The invention relates to the fuel systems of aircraft (LA), and in particular to the fuel systems of unmanned aerial vehicles (UAVs), separated from the carrier aircraft. This technical solution also applies to fueling in flight.

The aviation complex is known (Russian Arms and Technologies. Encyclopedia of the XXI Century. Volume 1, p. 234. M .: Weapons and Technologies, 2000; additional information on the possibility of extending the X-55 cruise missile engine, virtual aviation reference http: www / airwar / m / weapon / kr / x55 / html, 2001), consisting of a carrier aircraft, on the external suspension unit of which a detachable unmanned aerial vehicle is located, in the cavity of the body of which there is a mid-flight engine with the possibility of its extension into the working position beyond the contours corps.

A known version of the aviation complex (Weapons and Technologies of Russia. Encyclopedia of the XXI century. Volume 1, p. 229, 231. M .: Weapons and Technologies, 2000), consisting of a carrier aircraft, in the cargo compartment of which on a rotating drum multi-position launcher the installation housed detachable unmanned aerial vehicles, in the cavity of the hull of each of which there is a marching engine with the possibility of its extension to the working position beyond the hull contours.

All these essential technical features are present in the variants of the proposed technical solution.

A feature of the constructive implementation of the known devices is that in the cavity of the UAV body after the engine is extended there remains free unused space, which can be used to accommodate an additional volume of fuel.

The proposed options solve the problem of using free space for an additional fuel tank in the cavity of the UAV hull after extending the main engine.

To implement the above technical result in the first version of the aircraft complex, which consists of a carrier aircraft, on the external suspension unit of which a detachable unmanned aerial vehicle is located, in the cavity of the housing of which there is a mid-flight engine with the possibility of its extension to the working position over the body contours, the aircraft fuel systems carrier and unmanned aerial vehicle are interconnected by a message line containing a detachable connector, before and after which overlapping valves are installed s, and fuel system of the drone inlet line message comprises additional elastic crimped fuel tank disposed in the body cavity with the opportunity to place an extendable pickup location engine and fuel system production of flexible fuel tank.

To implement the technical result in the second version of the aviation complex, which consists of a carrier aircraft, in the cargo compartment of which on the rotary drum of the multi-position launcher are located detachable unmanned aerial vehicles, in the cavity of the body of each of which is in the transport position a main engine with the possibility of its extension in the working position for the contours of the hull, the fuel systems of the carrier aircraft and each unmanned aerial vehicle are connected between with message lines containing detachable connectors, before and after which shut-off valves are installed, the fuel system of each unmanned aerial vehicle at the input of the message line contains an additional compressed elastic fuel tank located in the body cavity with the possibility of folding in the location of the retractable engine, and a fuel generation system from an elastic fuel tank, while the communication lines of the fuel system of each unmanned aerial vehicle with the fuel system of the nose-plane of Tell have a common portion between the launcher and the rocker carrier aircraft fuel system equipped with the rotation assembly.

In addition, in both versions, to ensure that the elastic tank is refueled from the carrier aircraft’s tank without power take-off from the carrier’s fuel system and minimally affects the parameters of the carrier’s fuel system, the communication line of the carrier’s and unmanned aerial vehicle’s fuel systems can be equipped with fuel pump.

In addition, in the second embodiment:

- to ensure ease of assembly and installation with a minimum outer diameter, the rotation unit on the common section of the communication lines of the fuel system of each unmanned aerial vehicle with the fuel system of the carrier aircraft can be made in the form of a telescopic connection with a sealing gland;

- to increase the degree of tightness, the rotation unit on the common section of the communication lines of the fuel system of each unmanned aerial vehicle with the fuel system of the carrier aircraft can be made in the form of a flexible spiral bent pipeline.

In addition, in both variants of the known devices:

- to ensure the production of fuel from an elastic fuel tank in an autonomous UAV flight, the system for generating fuel from an elastic fuel tank can be made in the form of a communication line between an elastic fuel tank and a UAV fuel system containing a fuel pump, or can be made in the form of message lines of a compressed elastic fuel tank a tank in the upper and lower part with the corresponding parts of the cavity of the UAV fuel tank or communication lines of a compressed elastic fuel tank with a UAV compressed gas source, containing s shut-off valve and the fuel system of the UAV;

- to increase the degree of tightness of the UAV main fuel tank during storage and in autonomous flight, after fuel has been generated from the elastic tank, each communication line of the compressed elastic tank with the UAV fuel system can be equipped with a shutoff valve;

- to ensure the extension of the engine of the aircraft by the fuel pressure, the compressed elastic fuel tank during refueling can be the drive mechanism for the extension of the mid-flight UAV engine;

- to reduce the likelihood of damage to the elastic fuel tank during installation, refueling or emptying, transportation of the UAV and increase its safety factor, the compressed elastic fuel tank of the unmanned aerial vehicle can be placed inside a protective elastic cover, the volume and shape of the surfaces of which correspond to the volume and shape of the surfaces of the elastic fuel tank in the refilled condition.

Distinctive features of the proposed first and second versions of the aviation complex are:

- the interconnection of the fuel systems of the carrier aircraft and the UAV with a communication line containing a detachable connector;

- the presence of shutoff valves in the communication line of the fuel systems of the carrier aircraft and UAVs installed before and after the plug connector;

- the presence in the fuel system of an unmanned aerial vehicle at the inlet of the communication line of an additional compressed elastic fuel tank placed in the cavity of the body with the possibility of layout at the location of the retractable engine, and a system for generating fuel from an elastic fuel tank;

- the presence of a fuel pump in the communication line of the fuel systems of the carrier aircraft and UAVs.

In addition, in addition, in the second embodiment of the device, the distinguishing features are:

- the presence of a common area in the communication lines of the fuel system of each unmanned aerial vehicle with the fuel system of the carrier aircraft, which is located between the multi-position launcher and the fuel system of the carrier aircraft and is equipped with a rotation unit;

- the implementation of the rotation node on a common section of communication lines in the form of a telescopic connection with a sealing gland;

- the implementation of the rotation node on a common section of communication lines in the form of a flexible spirally curved pipeline.

In addition, in addition, the hallmarks of the proposed device options are:

- implementation of a system for generating fuel from an elastic fuel tank in the form of a communication line of a compressed elastic fuel tank with a fuel system of an unmanned aerial vehicle containing a fuel pump;

- implementation of a system for generating fuel from an elastic fuel tank in the form of communication lines of a compressed elastic fuel tank in the upper and lower parts with the corresponding parts of the UAV fuel tank;

- implementation of a system for generating fuel from an elastic fuel tank in the form of communication lines of a compressed elastic fuel tank with a UAV compressed gas source through a shutoff valve and with its fuel system;

- supply of each communication line of the compressed elastic fuel tank with the UAV fuel system with a shutoff valve;

- the use of a compressed elastic fuel tank when refueling as a drive mechanism for the extension of the UAV mid-flight engine;

- placement of a compressed UAV elastic fuel tank inside a protective elastic cover, the volume and shape of the surfaces of which correspond to the volume and shape of the surfaces of the elastic fuel tank in a filled state.

Due to the presence of these distinctive features in conjunction with the known (indicated in the restrictive part of the formula) when using any of the proposed devices, the following technical result is achieved - the maximum range of UAV autonomous flight is increased, as well as due to additional features:

- provides fueling of the elastic tank from the fuel system of the carrier aircraft with minimal impact on its parameters,

- provides control over the flow rate when generating fuel from an elastic fuel tank in an autonomous UAV flight, as well as the simplicity of the design of a system for generating fuel from an elastic fuel tank;

- provides an increase in the degree of tightness of the fuel system of an UAV with an elastic tank during storage and in autonomous flight of an UAV, after fuel has been generated from an elastic tank;

- provides the extension of the UAV engine with an elastic tank when refueling fuel in it;

- reduces the likelihood of accidental damage to the elastic fuel tank during installation, transportation of UAVs, refueling or emptying.

In addition, in the second embodiment of the proposed device for the rotation unit in the refueling line of elastic containers is provided:

- ease of assembly and installation;

- its minimum outer diameter;

- increased tightness.

As a result of a search by sources of patent and scientific and technical information, a set of features characterizing the proposed options for the aircraft complex with an additional compressed elastic fuel tank located in the cavity of the UAV body with a marching engine was not found. Thus, the present invention meets the eligibility criterion of "new."

Based on a comparative analysis of the proposed technical solution with the prior art according to the sources of scientific, technical and patent literature, it can be argued that between the totality of signs, including distinctive, and the functions performed by them and the goals achieved, there is no obvious causal relationship. Based on the foregoing, we can conclude that the technical solution does not follow explicitly from the prior art and, therefore, meets the eligibility criterion of "inventive step".

The proposed technical solution can be used to create aircraft systems with an increased range of UAV flight. Thus, the present invention meets the eligibility criterion of "industrially applicable".

Variants of the proposed devices are illustrated in figures 1-9.

Figure 1 presents the front view of the aircraft complex, explaining the device according to claim 1 of the claims.

Figure 2 presents a cross section of the fuselage of the carrier aircraft of the aircraft complex, explaining the device according to claim 2 of the claims.

Figure 3 presents a side view of the aircraft complex in the vicinity of the cargo compartment of the carrier aircraft (view B, figure 2) with the removed shell of the fuselage of the carrier aircraft, explaining the operation of the device according to paragraphs 2 and 3 of the claims.

In Fig. 4, embodiments of the rotation assembly on the fuel line of the device according to paragraphs 4 and 5 of the claims are presented (place C of Fig. 3).

Figure 5 presents a longitudinal section of the hull of an unmanned aerial vehicle in the vicinity of its cavity with a marching engine (section AA, Figs. 1 and 2), explaining the device according to paragraphs 1-3 and 6-11 of the claims.

In Fig.6 presents a section aa of Fig.1 and 2 with the extended position of the main engine of the UAV and a refueling elastic fuel tank.

In Fig.7 presents a cross section of the hull of an unmanned aerial vehicle in the vicinity of its cavity with a marching engine (section DD, Fig.5); on Fig presents a cross section of the hull of an unmanned aerial vehicle of its cavity with an extended marching engine (section EE, Fig.6), which further explain the operation of the device according to paragraphs 1-3 and 6-11 of the claims.

Figure 9 presents a schematic diagram of the fuel system of the aviation complex, explaining the operation of the proposed devices according to paragraphs 1-11 of the claims.

The devices shown in figures 1-9 contain a carrier aircraft 1, on the external suspension assembly of which 2 (figure 1) and in the cargo compartment 3 (figure 2) on the rotating drum 4 (figure 3) of the multi-position launcher 5 are detachable UAV 6, in the cavity 7 of the housing 8 (figure 5) which is placed the main engine 9 with the pylon 10, as well as the mechanism 11 of the extension of the engine 9 in the working position for the contours of the housing 8 (6). The extension mechanism 11 is made in the form of a lever parallelogram and is equipped with a synchro rod 12, a drive 13, as well as latches of the internal 14 and external 15 positions of the engine 9; elastic fuel tank 16 for the best filling of the volume of the cavity 7 after the extension of the engine 9 consists of two parts 17 and 18, interconnected through the flanges 20 and 21 overflow channel 19; an elastic fuel tank 16 of the UAV fuel system 6 is communicated by line 22 with the fuel system 23 of the carrier aircraft 1; the communication line 22 with the fuel system 23 of the carrier aircraft 1 has a detachable connector 24 mounted on the external node of the suspension 2 or on the drum 4; shutoff valves 25 are installed before and after connector 24 in line 22; the system for generating fuel from the elastic fuel tank 16 can be made in the form of a communication line 26 with the fuel tank 27 of the UAV fuel system 6 containing the fuel pump 28, or in the form of communication lines 29 and 26 of the compressed flexible fuel tank 16 in the upper and lower parts with the corresponding parts of the fuel tank 27 of the UAV fuel system 6, or in the form of a line 30 connecting the tank 16 to the compressed gas source, for example, the compressor of the main engine 9 through the shutoff valve 31 and the communication line 26 of the tank 16 with the fuel system of the UAV 6 - fuel m tank 27. When placing the UAV 6 on the drum 4 of the multi-position launcher 5 of the line 22, the messages of each elastic fuel tank 16 of the corresponding UAV 6 have a common section 32 (figure 3) between the multi-position launcher 5 and the fuel system 23 of the carrier aircraft 1, equipped with knot of rotation 33.

The rotation unit 33 can be made in the form of a telescopic connection 34 (figure 4) with a sealing gland 35 or in the form of a flexible spiral bent pipe 36.

Each communication line 26 and 29 of the compressed elastic fuel tank 16 with the fuel tank 27 of the fuel system of the UAV 6 can be equipped with a shutoff valve 37.

Compressed elastic fuel tank 16 may be the drive mechanism 11 for the extension of the engine 9 of the UAV 6 for the contours of the housing 8 in the working position, passing through the walls of the flexible fuel tank when refueling fuel pressure on the structural elements of the main engine 9.

Compressed elastic fuel tank 16 may be placed inside the protective elastic cover 38.

Line 22 (Fig.1, 9) or its portion 32 (Fig.3-5) of the fuel system of the UAV 6 - compressed elastic fuel tank 16 with the fuel system 23 of the carrier aircraft 1 can be equipped with a fuel pump 39.

The fuel from the fuel system of the UAV 6 - fuel tank 27 is supplied to the main engine through line 40.

The device according to claim 1 of the claims works as follows. Before separating the UAV 6 from the assembly 2 (Fig. 1) of the external suspension of the carrier aircraft 1, the retracted position of the engine 9 is unlocked by pulling out the latch 14 and the engine 9 (Figs. 5 and 6) is released by actuating the drive 13, which drives the mechanism 11. Synchronism in the operation of the levers of the mechanism 11 is provided by the synchro-link 12. The extension of the engine ends after the latch 15 of the external position of the engine 9.

After the engine 9 has been extended to the working position, the bypass valves 25 open in the line 22 of the UAV fuel system 6 — elastic fuel tank 16 with carrier system 23 fuel system 1 bypasses of the body 8 if they do not automatically open by mechanical action when docking the UAV 6 to the carrier aircraft 1, and under the action of a hydrostatic pressure drop in the fuel system 23 of the carrier aircraft 1 with respect to the compressed elastic fuel tank 16 located below the fuel level in the fuel system e 23, the fuel from the fuel system 23 through the message line 22 enters the compressed fuel tank 16, which is straightened and takes up after filling the volume in the cavity 7 of the UAV body 8, freed up after the main engine 9 has been extended. The time for refueling of the elastic fuel tank 16 may be reduced if the fuel system 23 of the carrier aircraft 1 has a means of pressurizing the fuel (pump or pressurization system of the fuel tank of the carrier aircraft 1).

After the refueling of the elastic fuel tank is completed, the shutoff valves 25 are closed and the UAV 6 is separated and the main engine 9 is started (it is possible to combine these operations). When the UAV 6 is separated, the fuel systems of the carrier aircraft 1 and UAV 6 are disconnected by disconnecting the connector 24 on line 22. In autonomous flight of UAV 6, a system for generating fuel from an elastic fuel tank 16 is activated and fuel flows through line 26 from an elastic fuel tank 16 to a fuel system of UAV 6 - a fuel to 27, from which on line 40 enters the boosters 9, providing an increase in maximum range UAV 6.

The device according to claim 2 of the claims works as follows (see figure 2 and 3). The rotation of the drum 4 of the multi-position launcher 5 in the cargo compartment 3 of the carrier aircraft 1 is activated so that the UAV 6 intended for separation is located in the lower part opposite the hatch of the cargo compartment 3.

The rotation of the drum 4 while maintaining the possibility of communication of the compressed elastic fuel tank 16 with the fuel system 23 of the carrier aircraft 1 is ensured by the presence of a rotation unit 33 located on a common section 32 of the lines 22 of each UAV 6 (Fig. 2). The rotation node 33 provides a rotation stationary relative to the drum 4 of the portion of the common portion 32 with respect to the rest of the portion 32 and the carrier aircraft 1.

Next, open the hatch of the hatch of the cargo compartment 3 of the carrier aircraft 1.

Further operation of the device for separation of the UAV 6, located opposite the hatch of the carrier aircraft 1 coincides with the operation of the device according to claim 1 of the claims.

After separation of the UAV 6, the rotation of the drum 4 clockwise or counterclockwise is re-activated, and the next UAV 6, which is intended for separation, is installed opposite the hatch of the cargo compartment 3, and the operation of the device is repeated similarly to the device according to paragraph 1 of the claims.

The device according to claim 3 of the invention works similarly to the device according to claims 1 or 2, while supplying the line 22 (FIGS. 1, 9) or its portion 32 (FIGS. 3-5) of the message of the elastic fuel tank 16 with the fuel system 23 of the aircraft -carrier 1 with a fuel pump 39, which is used when refueling the elastic fuel tank 16, provides fueling due to the power of the pump 39, without power take-off in the fuel system 23 of the carrier aircraft 1, and therefore has a minimal effect on the parameters of the fuel system 23 of the carrier aircraft 1.

The device according to claim 4 of the formula of the invention works similarly to the device according to claim 2, in addition, a specific embodiment of the rotation assembly 33 (Figs. 3, 4) on a common section 32 of the communication line of compressed elastic fuel tanks 16 with the fuel system 23 of the carrier aircraft 1 in the form of a telescopic connection 34 provides ease of assembly of the telescopic connection 34 by simply translating the end movable part of the common portion 32 into the cylindrical enclosure of the telescopic connection 34. The slotted annular gap telescoping connection gland 35 prevents fuel from leaking through the gap. The proposed design provides the ability to obtain the minimum outer diameter of the rotation unit in the form of a telescopic connection 34, which is determined from the condition of "setting" with a thin-walled case of the connection 34 of the end movable part of the common section 32 with a minimum technological annular gap, it is possible to rotate the movable part of the section 32 of the communication line 22.

The device according to claim 5 of the invention works similarly to the device according to claim 2, wherein the rotation assembly 33 (FIGS. 3 and 4), made in the form of a flexible spiral bent pipeline 36, does not contain a detachable connection, while it is possible to rotate stationary relative to the drum multi-position launcher 5 parts of a common section 32 of the highway 22 messages elastic fuel tanks 16 with the fuel system 23 of the carrier aircraft 1 and increased tightness of the rotation unit compared with the previous version of the device.

The device according to claim 6 of the invention works similarly to the device according to any one of paragraphs 1-5, while the implementation of the system for generating fuel from the elastic fuel tank 16 in the form of a line 26 containing the fuel pump 28 will allow, after switching on the pump 28, to transfer fuel to the fuel tank 27, as well as control the transfer time by changing the performance of the pump 28. During the pumping of the fuel, the elastic fuel tank 16 receives atmospheric pressure from the outside, is crimped, reducing the internal volume.

The device according to claim 7 of the formula of the invention works similarly to the device according to any one of paragraphs 1-5, while the generation of fuel from the elastic fuel tank 16 via line 26 to the fuel tank 27 of the UAV fuel system 6 occurs due to the hydrostatic pressure drop while lowering the fuel level in tank 27 of the UAV fuel system 6, since when the system for generating fuel from the elastic fuel tank 16 is executed in the form of lines 29 and 26 of the message of the flexible fuel tank 16 in the upper and lower parts with the corresponding parts of the fuel tank and 27, both fuel tanks 16 and 27 are communicating vessels.

The device according to claim 8 of the claims works similarly to the device according to any one of paragraphs 1-5, wherein the system for generating fuel from the elastic fuel tank 16 in the form of a line 30 communicated through a shut-off valve 31 (FIGS. 5 and 9) with a source of compressed gas UAV 6, for example, by the compressor of the main engine 9, and the communication line 26 of the elastic fuel tank 16 with the fuel system of the UAV 6, its fuel tank 27, will ensure the transfer of fuel from the additional elastic fuel tank 16 in autonomous flight of the UAV 6 to the fuel tank 27 HAND pressurized gas from the source 6. UAV shut-off valve 31 when filling the fuel tank of compressed elastic 16 is in the closed position and is opened at the right time in the autonomous flying UAV 6 kinked fuel from tank 16 through line 26.

The device according to claim 9 of the claims works similarly to the device according to any one of paragraphs 1-8, while, additionally, the presence of shutoff valves 37 (Figs. 5 and 9) on the communication lines 26 and 29 of the elastic fuel tank 16 with the UAV fuel system 6 - tank 27 will allow by closing the shut-off valves 37 to prevent fuel from entering the cavity of the compressed elastic fuel tank 16 when refueling the fuel tank 27 of the UAV 6, which will increase the tightness of the fuel tank 27 and reduce the load on the elastic tank 16 during transportation of the UAV 6 by preventing Ia in contact with the fuel tank 16, and the associated increase in its mass, and also by eliminating the dynamic loads associated with the movement of trapped in the cavity compressed elastic tank 16 part of the fuel.

The device according to claim 10 of the claims works similarly to the device according to any one of paragraphs 1-9, wherein, after releasing the latch 14 (FIGS. 5 and 6) of the internal position of the engine 9 and opening the shutoff valves 25 in the communication line 22, the overpressure fuel enters cavity of the elastic fuel tank 16. The excess pressure of the fuel in the cavity of the elastic fuel tank 16 is transmitted through its walls to the structural elements of the engine 9, providing a transfer of force to drive the mechanism 11 and extend the engine 9 in e rs position of hull lines 8 UAV 6, wherein the flexible fuel tank 16 during refueling will serve as the drive mechanism 11 until the engagement latch 15, an external motor 9 position.

The device according to claim 11 of the claims works similarly to the device according to any one of paragraphs 1-10, while during the transportation of the UAV 6, as well as during installation, refueling of the elastic fuel tank 16 and the generation of fuel from it, the outer surface of the elastic fuel tank 16 is based on the inner the surface of the protective cover 38 (Fig. 9), which excludes the contact of the walls of the elastic fuel tank 16 with the structural elements of the UAV 6 located in the cavity 7 of the housing 8 (Fig. 5), and thereby reduces the likelihood of damage to the walls of the elastic fuel tank 16. In addition, during refueling, the elastic fuel tank 16 under the influence of excessive fuel pressure is expanded to its maximum volume when refueling completely, while due to the correspondence of the volume and shape of the surfaces of the protective elastic cover 38 (Fig. 9) to the volume and shape of the surfaces elastic fuel tank 16 in the filled state, the walls of the elastic tank 16 and the elastic protective cover 38 perceive excessive fuel pressure together, which ensures an increase in the elastic safety factor tank 16.

Claims (11)

1. The aircraft complex, consisting of a carrier aircraft, on the external suspension unit of which a detachable unmanned aerial vehicle is located, in the cavity of the housing of which there is a mid-flight engine with the possibility of its extension to the working position over the body contours, characterized in that the fuel systems of the carrier aircraft and unmanned aerial vehicles are interconnected by a message line containing a detachable connector, before and after which shutoff valves are installed, and the fuel system of the unmanned aerial vehicle The apparatus at the input of the communication line contains an additional compressed elastic fuel tank located in the cavity of the housing with the possibility of layout at the location of the retractable engine, and a system for generating fuel from the elastic fuel tank. 2. Aircraft complex, consisting of a carrier aircraft, in the cargo compartment of which on a rotating drum of a multi-position launcher are detachable unmanned aerial vehicles, in the cavity of the body of each of which is in the transport position a main engine with the possibility of its extension to the working position for the contours of the body, characterized in that the fuel systems of the carrier aircraft and each unmanned aerial vehicle are interconnected by communication lines containing detachable soy carriers, before and after which shutoff valves are installed, the fuel system of each unmanned aerial vehicle at the inlet of the communication line contains an additional compressed elastic fuel tank located in the body cavity with the possibility of folding out at the location of the retractable engine, and a fuel generation system from the elastic fuel tank, of this line of communication of the fuel system of each unmanned aerial vehicle with the fuel system of the carrier aircraft have a common section between the multi-position a quick installation and a fuel system of a carrier aircraft equipped with a rotation unit. 3. The aviation complex according to claim 1 or 2, characterized in that the communication line of the fuel systems of the carrier aircraft and the unmanned aerial vehicle is equipped with a fuel pump. 4. The aviation complex according to claim 2, characterized in that the rotation unit on the common section of the communication lines of the fuel system of each unmanned aerial vehicle with the fuel system of the carrier aircraft is made in the form of a telescopic connection with a sealing gland. 5. The aviation complex according to claim 2, characterized in that the rotation unit on a common section of the communication lines of the fuel system of each unmanned aerial vehicle with the fuel system of the carrier aircraft is made in the form of a flexible spiral bent pipeline. 6. The aviation complex according to any one of claims 1 to 5, characterized in that the fuel generation system from the elastic fuel tank is made in the form of a communication line of the compressed elastic fuel tank to the fuel system of an unmanned aerial vehicle containing a fuel pump. 7. The aviation complex according to any one of claims 1 to 5, characterized in that the fuel generation system from the compressed elastic fuel tank is made in the form of communication lines of the compressed elastic fuel tank in the upper and lower parts with the corresponding parts of the fuel tank of an unmanned aerial vehicle. 8. Aircraft complex according to any one of claims 1 to 5, characterized in that the system for generating fuel from an elastic fuel tank is made in the form of communication lines of a compressed elastic fuel tank with a compressed gas source of an unmanned aerial vehicle containing a shutoff valve and with an unmanned fuel system aircraft. 9. The aviation complex according to any one of claims 1 to 8, characterized in that each communication line of the compressed elastic fuel tank with the fuel system of an unmanned aerial vehicle is equipped with a shutoff valve. 10. Aircraft complex according to any one of claims 1 to 9, characterized in that the elastic fuel tank is the drive mechanism for the extension of the main engine. 11. Aircraft complex according to any one of claims 1 to 10, characterized in that the compressed elastic fuel tank of the unmanned aerial vehicle is placed inside a protective elastic cover, the volume and shape of the surfaces of which correspond to the volume and shape of the surfaces of the elastic fuel tank in a filled state.

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