RU2397114C1 - Drone plane with nuclear warhead - Google Patents

Abstract

FIELD: transport. ^ SUBSTANCE: invention relates to aircraft engineering. Drone plane comprises airframe, warhead, constant-area wing, variable-area wing, turbojet engine and rocket booster. Drone plane comprises also power plant with two screw propellers fitted outside, on airframe lower tail part. Variable-area sweep forward wing consists of telescoping parts. Constant-area sweepback wing is furnished with elevons. ^ EFFECT: higher maneuverability. ^ 6 cl, 11 dwg

Description

The invention relates to the field of aviation.

Known unmanned aerial vehicle (UAV), made with the possibility of launching from a submarine and containing the fuselage, warhead, fixed-wing wing, variable-wing wing, turbojet engine and rocket accelerator / US Patent 5615847, 1997 /.

The known unmanned aerial vehicle has a rocket accelerator, designed only to rise to the surface of the water with a vertical initial section of movement in the air, and a rotary wing of variable area, which is fixed by a hinge in the middle of the fuselage.

A well-known unmanned aerial vehicle can be detected already when moving on a vertical initial section in the air with the appropriate means of observing the enemy and destroyed in the air before it reaches the target.

The invention is aimed at solving the problem of reducing the likelihood of UAV destruction by air defense means by implementing a trajectory that includes an additional section of movement under water due to a rocket accelerator and an additional section of movement along the water surface due to propellers, flight using the effect of the effect of the screening surface of the water at heights of up to 100 m due to turbojet engines, a wing of a constant area and a deployed wing of a variable area.

The invention is also aimed at solving the problem of increasing the protection of the apparatus by using air-to-air missiles.

To solve these problems, an unmanned aerial vehicle comprising a fuselage, a warhead, a constant-area wing, a variable-area wing, at least one turbojet engine and a rocket accelerator is proposed.

The apparatus is equipped with a power unit having two propellers, which are located outside on the lower rear of the fuselage, the variable-wing wing is made of reverse sweep of telescopically extendable parts, and the constant-wing wing is made of direct sweep with elevons.

The device is configured to start from a submarine.

The device has two lift-march turbojet engines, each of which is equipped with a breakthrough membrane located in the air intake, and a breakthrough membrane located in the nozzle.

The power plant includes a tank with liquid hydrocarbon fuel, a cylinder with an oxygen-containing oxidizing agent, an internal combustion engine, a gearbox having an input shaft and two output shafts, each of which is connected to a corresponding propeller.

A constant-area wing is configured to launch guided missile shells.

The invention is illustrated by drawings.

Figure 1. UAV when moving in water. Front view.

Figure 2. UAV when moving in air with a wing of maximum scope.

Figure 3. UAV when moving in the air. Side view.

Figure 4. UAV when moving in air with front horizontal tail. Top view in figure 2.

Figure 5. UAV when moving in water with front horizontal tail. View from below.

6. UAV when moving in air above the surface of the water in the mode of creating a screen effect by a wing of constant scope.

7. The UAV mechanism during the extension of the wing, which is variable to the position of the sweep of the reverse sweep.

Fig. 8. The UAV mechanism with the folded wing position of the variable span of the reverse sweep

Fig.9. Kinematic diagram of the propeller drive from the power plant. The bottom view in figure 3.

Figure 10. The mechanism of the retractable sections with the rolling guides of the wing of a variable span of the reverse sweep.

11. Kinematic diagram of the wing mechanism of a variable swing sweep.

The list of positions in the drawings:

1 - fuselage

2 - wing variable area reverse sweep,

3 - lifting-marching turbojet engine having an electric motor for starting and an electric generator for powering the control system and electrical equipment,

4 - stabilizer front horizontal tail,

5 - wing of a constant area of direct sweep with elevons,

6 - nuclear warhead,

7 - radar guidance system,

8 - rocket accelerator,

9 - the first valve, made with a forced breakthrough membrane from the pyrodrive and located in the air intake of the engine 3,

10 - the second valve, made with a forced breakthrough membrane from the pyrodrive and located in the nozzle of the engine 3,

11 - the lower part of the fuselage 1, made in the form of a boat,

12 - propeller,

13 - mechanical transmission,

14 - internal combustion engine,

15 - tank with gasoline,

16 - cylinder with a mixture of oxygen and nitrogen,

17 - alternator for starting engines 3,

18 - wing drive electric motor 2,

20 - drive (winch), including an electric motor 18 and gears 19 of the transmission mechanism for changing the area of the wing 2,

21 is a drum in the form of a coil,

22 - cable

23 - movie

24 - guide sliding section with rollers 23 of the actuator 20,

25 - the moving part of the wing 2,

26 - guided missile projectile.

The unmanned aerial vehicle contains (Figs. 1-4) a fuselage 1, a wing 2 of a variable area of reverse sweep, two lift-march turbojet engines 3, a stabilized stabilizer 4 of the front horizontal tail, a wing 5 of a constant area of direct sweep with elevons, a nuclear warhead 6, a radar targeting system 7 and rocket accelerator 8.

The unmanned aerial vehicle is made with two vertical keels, each of which has a rudder and is mounted above the wing 5 in the middle part.

Each engine 3 is installed above the wing 5 between the corresponding vertical keel and the fuselage 1 in the rear.

Each engine 3 has an electric motor for starting and an electric generator for powering the control system and the electric equipment of the UAV.

Each engine 3 includes an air intake in which the first valve 9 with a forced breakthrough membrane from the pyrodrive is located, and a nozzle in which the second valve 10 with a forced breakthrough membrane from the pyrodrive is located.

The first valve 9 and the second valve 10 ensure the tightness of the cavity of each engine 3 when immersed to a depth of 100 m.

A control system for the forced breakthrough membrane of both the first valve 9 and the second valve 10 is provided, including a sensor for the output of engines 3 into the air flow and an air flow velocity sensor, as well as a time relay.

In the lower part 11 of the fuselage 1 are located (Figure 5) two propellers 12.

Each propeller 12 is connected (Figure 9) to the output shaft of a mechanical transmission 13, the input shaft of which is connected to an internal combustion engine 14 of a power plant, including a tank 15 with gasoline as fuel and a cylinder 16 with a mixture of nitrogen and oxygen gases at a ratio of 60: 40 as an oxidizing agent.

The motor shaft 14 is connected to an alternator 17, which is electrically connected to electric motors designed to start turbojet engines 3.

To change the area, the wing 2 of the reverse sweep has (Fig. 8, 10) an electric motor 18 and gears of the transmission mechanism of the winch 20 with drums 21 for cables 22.

The wing 2 includes rollers 23 on the guides 24 of the telescopically extendable sections 25.

On each console wing 5 of a constant area installed (Fig.6) two guided missile shells 26 of the air-to-air class to destroy aircraft of the enemy air defense systems.

The unmanned aerial vehicle is configured to deliver a submarine to the launch site under water at a depth of 100 m when the wing 2 is set to the minimum area.

To control an unmanned aerial vehicle with a nuclear warhead, an on-board computer is provided.

UAV operation procedure.

Before starting, start the power plant, the engine 14 of which rotates the generator 17 and the propellers 12.

Then launch a rocket accelerator 8, under the influence of the thrust of which the aircraft departs from the submarine.

The stabilizer 4 of the front horizontal tail and wing 5 with elevons provide the creation of lifting force for the ascent of the aircraft to the surface of the water.

The control system according to the signals of the sensor about the output of the engines 3 into the air flow and the speed sensor of the incoming air flow issues a command to the pyrodrive of the first valve 9 in the air intakes and with a time delay, which is set using the time relay, to the pyrodrive of the second valve 10 in the nozzles for breaking membranes.

Then, sequentially from the generator 17 of the internal combustion engine 14, the turbojet engines 3 are sequentially automatically started sequentially in the automatic mode using the corresponding electric motors.

An unmanned aerial vehicle with a nuclear warhead starts flying using thrust of engines 3 and wing 5 of a constant area near the surface of the water, taking into account the effect of the screen at a speed of up to 400 km / h.

The generator of each engine 3 generates electricity, which is necessary for the operation of the radar system 7 and other electrical equipment of the aircraft.

Then, from the engine generators 3, electric power is supplied to the electric motor 18 of the multi-sectional drive 20 of the retractable sections 24 of the wing 2 of the reverse sweep.

The multi-sectional drive 20 of each wing console 2 includes (Figure 10) drums 21 with corresponding cables 22 of the retractable sections 24.

In this case, some drums 21 unwind the cable 22, and other drums 21 wind the cable 22, which pulls the guides through the rollers 23 in the sliding sections 24.

The movable parts 25 of the wing 2 of the reverse sweep move (11) in the direction from the fuselage 1 and occupy a position corresponding to the largest area.

The wing 2 of the reverse sweep and wing 5 of the constant area of direct sweep allows you to obtain aerodynamic lift for the flight of an unmanned aerial vehicle with a nuclear warhead at an altitude of up to 100 m above the water surface and the earth's surface at a speed of 400 ÷ 600 km / h to the target on the territory of the enemy.

Radar system 1 allows you to detect air defense of the enemy and provide guidance guided missile projectile 26 for their destruction.

The flight time of an unmanned aerial vehicle with a nuclear warhead can last several hours

Claims (6)

1. An unmanned aerial vehicle containing a fuselage, a warhead, a fixed-wing wing, a variable-wing wing, at least one turbojet engine and a rocket accelerator, characterized in that it is equipped with a power plant having two propellers that are located outside on the lower rear the fuselage, the variable-area wing is made of reverse sweep of telescopically extendable parts, and the constant-area wing is made of direct sweep with elevons. 2. The apparatus according to claim 1, characterized in that it is configured to start from a submarine. 3. The apparatus according to claim 1, characterized in that it has two lift-march turbojet engines, each of which is equipped with a breakthrough membrane located in the air intake, and a breakthrough membrane located in the nozzle. 4. The apparatus according to claim 1, characterized in that the power plant includes a tank with liquid hydrocarbon fuel, a cylinder with an oxygen-containing oxidizing agent, an internal combustion engine, a gearbox having an input shaft and two output shafts, each of which is connected to a corresponding propeller. 5. The apparatus according to claim 1, characterized in that the wing of a constant area is configured to launch guided missile shells. 6. The apparatus according to claim 1, characterized in that it contains a nuclear warhead.

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