RU29282U1 - AVIATION COMPLEX (OPTIONS) - Google Patents

Abstract

1. An aviation complex consisting of a carrier aircraft, on the external suspension assembly 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 beyond 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 placed in the cavity of the housing with the possibility of layout at the location of the retractable engine, and a fuel generation system 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 hull, characterized in that the fuel systems of the carrier aircraft and each unmanned aerial vehicle are interconnected by communication lines containing detachable connections 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 it at the location

Description

AVIATION COMILEX (options) The utility model relates to the fuel systems of aircraft (LA), namely 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 XXI Century Volume 1, p. 234, Moscow, Arms and Technologies Publishing House, 2000), consisting of a carrier aircraft with an air suspension unit on its external assembly; a detachable unmanned aerial vehicle apparatus, in the cavity of the housing of which there is a marching engine with the possibility of its extension to the working position for the contours of the housing. A well-known version of the aviation complex (Arms and Technologies of Russia. Encyclopedia XXI Century Volume 1, p. 229, 231, Moscow, publishing house Arms and Technologies, 2000), consisting of a carrier aircraft, in the cargo compartment of which on a rotary drum multi-position launcher placed detachable unmanned aerial vehicles, in the cavity of the hull of each of which there is a mid-flight engine with the possibility of its extension to the working position for the contours of the hull. 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 variants of the utility model solve the problem of using free space for an additional fuel tank in the cavity of the UAV case after the propulsion engine is extended. To implement the above technical result in the first version of the aviation complex, which consists of a carrier aircraft, on the external suspension unit of which a detachable unmanned aerial vehicle is located, in the body cavity of which there is a main engine with the possibility of its extension to the working position behind 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 cavity Object - device IPC: B 64 D 37/02, 37/12, 37/14 In a 64 D 39/00

housing with the possibility of layout in the location of the retractable engine, and a system for generating fuel from an elastic 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 detachable unmanned aerial vehicles are located, in the cavity of the body of each of which a propulsion engine is located in the transport position with the possibility of its extension into the working position for the contours of the hull, the fuel systems of the carrier aircraft and each unmanned aerial vehicle are connected between each with communication 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 communication 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 a rotation unit.

In addition, in both variants of the known devices for providing refueling of an elastic tank from a tank of a carrier aircraft without power take-off from the fuel system of a carrier aircraft and minimal influence on the parameters of the fuel system of the carrier aircraft, the communication line of the fuel systems of the carrier aircraft and unmanned aerial vehicle can be equipped with a fuel pump.

In addition, in the second embodiment of the known device:

- 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 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 boiling 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 an elastic tank, each communication line of a compressed elastic tank with a UAV fuel system can be equipped with a shutoff valve; - to ensure the extension of the engine of the aircraft with 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 an 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: -connection between the fuel systems of the carrier aircraft and the UAV with a communication line containing a detachable connector; - the availability 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 located in the body cavity with the possibility of layout at the location of the retractable engine, and the fuel generation system from the 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 spiral bent pipeline. h - the implementation of the system for generating fuel from an elastic fuel tank in the form of a communication line of a compressed elastic fuel tank with the fuel system of an unmanned aerial vehicle containing a fuel pump; -performing a system for generating fuel from an elastic fuel tank in the form of communication lines for a compressed elastic fuel tank in the upper and lower parts with the corresponding parts of the UAV fuel tank; -performing 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 shut-off 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 main propulsion UAV 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: -fueling of the elastic tank from the fuel system is ensured carrier aircraft with minimal impact on its parameters. -provides flow control 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 UAV fuel system with an elastic tank during storage and in an autonomous flight of an UAV, after fuel has been generated from an elastic tank; -Provided extension of the UAV engine with an elastic tank when refueling fuel in it; -Recreases the likelihood of accidental damage to the elastic fuel tank during installation, transportation BP.LA, 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 proposed utility model meets the eligibility criterion new. The proposed technical solution can be used to create aircraft systems with an increased range of UAV flight. Thus, the proposed utility model meets the eligibility criterion of industrial applicability. Variants of the proposed devices is illustrated by the drawings of FIG. 1-9. Pa fig. Figure 1 shows the front view of the aviation complex, I explain; the device according to claim 1 of the utility model formula. Pa fig. 2 is a cross-sectional view of the fuselage of a carrier aircraft of an aircraft complex, illustrating a device according to claim 2 of the utility model formula. Pa fig. 3 is a side view of an aircraft complex in the vicinity of the cargo compartment of a carrier aircraft (view B, FIG. 2) with the shell of the carrier fuselage removed, explaining the operation of the device according to paragraphs 2 and 3 of the utility model formula. Pa fig 4 presents embodiments of the rotation unit on the fuel line of the device according to paragraphs 4 and 5 of the formula of the utility model (place C fig.Z). Pa fig. 5 shows a longitudinal section of the body of an unmanned aerial vehicle in the region where its cavity with a marching engine is located (section AA, FIG. 1 and FIG. 2), an explanatory device according to paragraphs 1-3 and 6-11 of the utility model formula, Pa. FIG. 6 is a section A-A of FIG. 1 and FIG. 2 with the extended position of the UAV mid-flight engine and the fuel tank filled with elastic. Pa fig. 7 shows a cross section of the body of an unmanned aerial vehicle in the region where its cavity with a marching engine is located (section DD, FIG. 5), and FIG. 8 shows a cross section of the body 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 utility model formula. Pa fig. 9 is 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 utility model formula. Presented in FIG. 1-9, the device comprises a carrier aircraft 1, on the external suspension unit of which 2 (Fig. 1) and in the cargo compartment 3 (Fig. 2) on the rotating drum 4 (Fig. 3) of the multi-position launcher 5 are detachable UAVs 6, cavity 7 of the housing 8 (Fig. 5) which is placed mid-flight engine 9 with the pylon 10, as well as the mechanism 11 of the extension of the engine 9 to the working position for the contours of the housing 8 (Fig. 6). The extension mechanism 11 is made in the form of a lever parallelogram and

equipped with a synchro-link 12, 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 aligned with line 22 with the fuel system 23 of the carrier aircraft 1; communication line 22 with fuel system 23 of carrier aircraft 1 has a detachable connector 24 mounted on an external suspension unit 2 or on a 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 line 26 of the communication; containing the fuel tank 27 of the fuel system of the UAV 6; it contains a fuel pump 28, or in the form of lines 29 and 26 of the communication of the compressed elastic 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 of the connection of the tank 16 with a source of compressed gas, for example, the compressor of the main engine 9 through the shut-off valve 31 and the line 26 of the message of the tank 16 with the fuel system UAV 6 - topl 27. When placing the UAV 6 on the drum 4 of the multi-position launcher 5 of the line 22 of the connection, each elastic fuel tank 16 of the corresponding UAV 6 has a common section 32 (Fig. 3) between the multi-position launcher 5 and the fuel system 23 of the carrier aircraft 1 equipped with a rotation unit 33.

The rotation unit 33 can be made in the form of a telescopic connection 34 (Fig. 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 during refueling fuel pressure on the structural elements of the sustainer engine 9.

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

Line 22 (Fig. 1, Fig. 9) or its portion 32 (Figs. 3-5) of the UAV fuel system 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 utility model formula works as follows. Before separating the UAV 6 from node 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 is released (Figs. 5 and 6)

engaging the actuator 13, which drives the mechanism 11. The synchronization 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 in the line 22 of the UAV fuel system 6 — elastic fuel tank 16 with fuel system 23 of the carrier aircraft 1 are opened for the contours of the UAV 6 if they are not automatically opened 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 via the connection line 1; 22 enters the compressed fuel tank 16, which is straightened and takes up the volume in the cavity 7 of the UAV body 8, which is freed up after the main engine is extended 9. After refueling, the elastic fuel tank 16 can 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 is used to generate fuel from an elastic fuel tank 16 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 utility model formula works as follows (see Fig. 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.

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

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

The 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 utility model formula. v 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 utility model formula. The device according to claim 3 of the utility model formula works similarly to the device according to pL or A.2, while supplying the line 22 (Fig. 1, Fig. 9) or its portion 32 (Fig. 3-5) of the message of the elastic fuel tank 16 with the fuel system 23 of the carrier aircraft 1 with the 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 carrier aircraft 1. Devices according to claim 4, the utility model formula works similarly to the device according to claim 2, in addition, the concrete embodiment of the rotation assembly 33 (Figs. 3, 4) on the common section 32 of the communication line of the 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 a cylindrical housing of the telescopic connection 34. Located in the slotted annular gap of the bodies scopic compound gland 35 prevents fuel from leaking through the gap. The proposed design makes it possible to obtain the minimum outer diameter of the rotation unit in the form of a telescopic connection 34, which is determined from the condition that the thin-walled case encloses the connection 34 of the end movable part of the common section 32 with a minimum technological annular gap. p. 5 of the formula of the utility model works similarly to the device according to p. 2, while the rotation node 33 (Fig. 3 and Fig. 4), made in de flexible spiral bent pipe 36, does not contain a detachable connection, while it is possible to rotate stationary relative to the drum of the multi-position launcher 5 of the portion of the common section 32 of the highway 22 communication 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 utility model formula works similarly to the device according to any one of paragraphs 1-5, wherein the execution of the fuel generation system 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. In the process of pumping 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 utility model formula works similarly to the device according to any one of paragraphs 1-5, while the production 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 the 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, the elastic fuel tank 16 communicates in the upper and lower parts with the corresponding parts of the fuel about tank 27, both fuel tanks 16 and 27 become interconnected vessels. The device according to claim 8 of the utility model formula 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 shutoff valve 31 (FIG. 5 and FIG. 9) the UAV 6 compressed gas source, for example, the compressor of the main engine 9, and the communication line 26 of the elastic fuel tank 16 with the UAV fuel system 6, its fuel tank 27, will provide fuel transfer from the additional elastic fuel tank 16 in the autonomous flight of the UAV 6 to the fuel tank to 27 by the pressure of compressed gas from the UAV source 6. The shutoff valve 31 when refueling the compressed elastic fuel tank 16 is in the closed position and opens at the necessary time in autonomous flight of the UAV 6 to transfer fuel from the tank 16 along line 26. The device according to claim 9 of the formula of the utility model works similarly to the device according to any one of paragraphs 1-8, while, additionally, the presence of shutoff valves 37 (Fig. 5 and Fig. 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 p 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 fuel from entering the tank 16 and the associated an increase in its mass, and also due to the exclusion of dynamic loads associated with the movement of 16 parts of the fuel that fell into the cavity of the compressed elastic tank. The device according to claim 10 of the utility model formula works similarly to the device according to any one of paragraphs 1-9, however, 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 into the 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, ensuring the transfer of force H to drive the mechanism None engine extension 9 in the operating position for the contours of the hull 8 of the UAV 6, while the elastic fuel tank 16 in the process of refueling will act as the drive of the mechanism 11 until the latch 15 of the external position of the engine 9 is activated. The device according to claim 11, and the utility model formula works similarly to the device according to any from paragraphs 1-10, while in the process of transporting the UAV 6, as well as during installation, refueling of the elastic fuel tank 16 and the development of fuel from it, the outer surface of the elastic fuel tank 16 rests on the inner surface of the shield Foot cover 38 (FIG. 9), which eliminates 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 the fueling process, the elastic fuel tank 16 under the influence of excess pressure of the fuel is expanded to its maximum volume at full refueling, 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 of the elastic fuel about the 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 safety factor of the elastic tank 16.

Claims (11)

1. An aviation complex consisting of a carrier aircraft, on the external suspension assembly 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 beyond 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. An aviation complex consisting of a carrier aircraft, in the cargo compartment of which on a rotating drum of a multi-position launcher, detachable unmanned aerial vehicles are located, in the cavity of the hull of each of which the main engine is located in the transport position with the possibility of its extension into the working position beyond the hull contours, 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, the communication lines 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 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 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 sustainer 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.