RU2258639C1 - Method of air start of unmanned flying vehicle and external suspension system for realization of this method - Google Patents

Abstract

FIELD: aeronautical engineering; air start of unmanned flying vehicles.

SUBSTANCE: air start of unmanned flying vehicle includes surface preflight preparation of flying vehicle, connection of external suspension system to carrier helicopter and unmanned flying vehicle and transportation to air start position, pre-start monitoring and drop. Connection of unmanned flying vehicle to carrier helicopter is performed by means of external suspension system with flexible cable. Start of cruising engine of unmanned flying vehicle is performed before its transportation to start point and drop is performed when cruising engine is operating in minimum thrust (power) mode. External suspension system is provided with cargo sling for performing air start; one end of this sling is secured on helicopter and other end is connected with cargo suspension beam; system is also provided with cargo aerodynamic stabilization unit made in form of vertical fins located symmetrically relative to plane of symmetry of cargo behind center of mass. It is provided with electric cable and monitoring panel showing state of on-board systems and air start control system on upper end and umbilical connector plug on lower end, fuel replenishing system with fuel tank and fuel hose with electric valve, device for cutting-off the cable and cargo sling. All above-mentioned devices are secured on cable by means of clamps but for electric fuel valve and umbilical connector plug which are connected with beam of suspension and control panel connected with upper free end of electric cable. Cargo suspension beam is made in form of hollow box with electric lock of cargo suspension, umbilical connector plug and fuel electric valve located in its center part. Lateral sides of beam ends are provided with two pairs of adjustable stops for mutual rigid locking of beam with cargo. Fins of cargo aerodynamic stabilization unit are located on rear end of longitudinal rod which is secured on rear part of cargo suspension beam. Fins may be deflected to opposite sides relative to vertical axis by means of two cables connected with spring-loaded lever which is secured on rear end of beam.

EFFECT: simplified arrangement of on-board equipment.

3 cl, 6 dwg

Description

The invention relates to aircraft and can be used to provide an air launch for unmanned aerial vehicles, mainly air targets, with marching gas turbine engines or internal combustion engines.

A known method of air launch of unmanned aerial vehicles by dumping in flight from a rigid suspension of a carrier aircraft, followed by starting the main engine of the starting object after it is separated from the aircraft, for example, starting an AQM-81 (USA) air target from an F-4 “Phantom II” aircraft ( see "JANE's ALL THE WORLD's AIRCRAFT", 1986-87, s. 853-854- Jane's Handbook "All World Aviation" for 1986-87, pp. 853-854), or the launch of the AS-2 cruise missile (USSR ) with a rigid suspension from a Tu-16 aircraft (see "JANE's.ALL THE WORLD's AIRCRAFT", 1986-87, s. 864-865 -Jane's Handbook "All Aviation of the World" for 1986-87, pp. 864-865 )

With this method, an unmanned aerial vehicle is attached before flight on a rigid suspension of the carrier aircraft and then transported by the aircraft to a predetermined launch point, in which the on-board systems of the unmanned aerial vehicle are checked for serviceability using special control equipment of the carrier aircraft and then the unmanned vehicle is launched by uncoupling from the suspension. In this case, the main engine starts either immediately before the start or starts automatically after the start.

The disadvantage of this method is that for its implementation is required, as a rule, a carrier aircraft of large dimension (up to 2-4-engine), even to ensure air launch of light unmanned objects, because the choice of an aircraft is determined not by its carrying capacity, but by the need to freely place an object with certain dimensions on a rigid suspension without interfering with the operation of the units and systems of the carrier aircraft (retractable landing gear, flaps, flaps, engines, radio systems, etc.) in all areas the flight of the aircraft from take-off to the start of the object. Accordingly, to base such aircraft, specially equipped airfields are required.

Closest to the proposed invention is a method of air launch of unmanned aerial targets from the helicopter’s rigid suspension with the launch of the mid-flight engine immediately before uncoupling - the launch of the Mirach-100s air target (Italy) from the Augusta A 109 helicopter (see "JANE's ALL THE WORLD's AIRCRAFT", 1986 -87, s.822-883 - Jane's Handbook “All Aviation of the World”, pp. 822-883).

With this method, an unmanned aerial vehicle is also attached to the rigid suspension of the carrier helicopter before the flight, representing a special metal structure attached to the side surface of the fuselage of the helicopter converted for the air carrier of a specific type of unmanned aerial vehicle. At a given starting point, the serviceability of all onboard systems of the target is checked and its marching engine is launched - all using special means of the carrier helicopter.

The disadvantage of all these known methods, except for the restrictions imposed by the dimensions of the unmanned objects used on the dimension of the air carrier, is that the system for starting the main engine of an unmanned object (energy sources, engine shaft spinning devices, automatic start, etc.) is partially either completely, or as part of the onboard equipment of the air carrier (in the case of starting the engine before uncoupling), or as part of the onboard equipment of the unmanned object itself (in the case of starting the engine spruce after uncoupling). Also, the equipment for monitoring the state of on-board systems of an unmanned vehicle should be introduced into the air carrier.

The re-equipment of the base aircraft in air carrier requires a large amount of work performed in the factory, i.e. production of a special version of the air carrier is required.

In addition, if the unmanned object’s main engine starts after its uncoupling, the launch system, which is part of the object, is subsequently parasitic mass, leading to an increase in the flight mass of the object, its cost, deterioration in its flight characteristics, and the probability of its failure leads to a decrease in reliability air launch.

All this significantly increases the complexity and cost of using unmanned objects.

Closest to the proposed system is an external suspension of a container-type cargo to a helicopter, comprising a cargo cable fixed at one end to a helicopter and connected at the other end to the load, a device for aerodynamic stabilization of cargo, made in the form of vertical keels attached to the cargo and arranged symmetrically relative to the longitudinal the axis behind the center of mass of the load (see copyright certificate No. 1832097, IPC B 64 C 1/22, 1993).

A disadvantage of the known device is the absence of remotely controlled from the helicopter board - carrier of a lock for dumping (or uncoupling) cargo in emergency situations, duplicating a regular helicopter lock for dumping the external load suspension system, as well as information devices for interaction of the helicopter operator with towed cargo systems.

The proposed inventions solve the problem of improving the reliability and safety of the air launch of unmanned aerial vehicles and the possibility of their discharge in emergency situations using a flexible system of external load and helicopter suspension as a universal air carrier, with minimal organizational and material costs.

To obtain such a technical result in the proposed method for the air start of unmanned aerial vehicles, including ground preliminary preparation of an unmanned aerial vehicle, attaching an external suspension system to a carrier helicopter, transportation to a launch point, pre-flight control, launching a mid-flight engine and resetting an unmanned aerial vehicle, while attaching the unmanned vehicle to the carrier helicopter is carried out using an external suspension system with a flexible cable, launching a march about the engine of the unmanned vehicle is carried out before its transportation to the starting point, and the discharge of the unmanned aerial vehicle is performed when the main engine is operating in the mode of its minimum thrust (power).

Distinctive features of the proposed method are the connection of the external suspension system of the unmanned vehicle with a cable to the carrier helicopter, the launch of the main engine of the unmanned vehicle before transporting it to the starting point and the reset of the unmanned aerial vehicle when the main engine is operating in the mode of its minimum thrust (power).

This increases the reliability and safety of the air launch of unmanned aerial vehicles, and also reduces the complexity and cost of their use due to the use of any type of helicopter equipped in the field as an air carrier.

The possibility of feeding the unmanned vehicle with fuel from the fuel tank of the external suspension system compensates for its consumption by the main engine during transportation to the starting point.

To achieve the named technical result, an external suspension system for unmanned aerial vehicles for the implementation of an air launch is proposed, the closest of which is the well-known author. testimonial. No. 1832097, IPC В 64 С 1/22, for 1993, which contains a freight cable fixed at one end on a helicopter and connected at the other end to the load, a device for aerodynamic stabilization of cargo, made in the form of vertical keels arranged symmetrically relative to its longitudinal axis behind the center of mass, according to the invention it is additionally equipped with an electric cable with a remote control for monitoring the state of onboard systems and controlling the start of unmanned aerial vehicles at the upper end and a plug for the tear-off electrical connector at its lower end tse, a load suspension beam, a fuel system for feeding the fuel system of the cargo, including a fuel tank and a fuel hose with an electrovalve, a device for cutting the cable and cable, while all of the above devices are fixed to the cable with clamps, with the exception of the fuel electrovalve and electric plug of the cable connected to the suspension beam and the control panel connected to the upper free end of the electric cable, and the cargo suspension beam is made in the form of a hollow box, in the central lower part of which an electric lock of the load suspension, a plug of the tear-off electrical connector and a fuel solenoid valve are arranged, and on the sides of the ends of the beam two pairs of adjustable stops are fixed for mutual rigid fixation of the beam with the load, while the keels of the device for aerodynamic stabilization of cargo are located on the rear end of the longitudinal rod, and the rod itself is fixed on the rear of the load suspension beam, and the keels are made to deflect in different directions relative to the vertical axis, with the load suspended, by means of two cables in, connected to a spring-loaded lever mounted on the rear end of the beam.

The invention is illustrated by drawings, which depict:

figure 1 - diagram of the suspension of the object to the helicopter carrier;

figure 2 - system for external suspension of cargo (object);

figure 3 - node A, suspension beam;

figure 4 - node B, vertical keels of the aerodynamic stabilizing device;

figure 5 - View In, the scheme of operation of the aerodynamic stabilizing device, figure 4;

figure 6 - lateral stops of the suspension beam along the cross-section GG, figure 3.

The proposed method is carried out in the following sequence: an unmanned object previously prepared for air launch is installed on a transport and technological trolley located in the immediate vicinity of the carrier helicopter prepared for flight, and connected to the helicopter by an external suspension system.

The transport and technological trolley ensures the placement of an unmanned object prepared for flight, the pre-flight monitoring of the health of its on-board systems and the launch of its main engine from ground-based launch vehicles.

Then a helicopter with an object mounted on the external suspension system rises into the air and flies to a predetermined launch point, as shown in figure 1.

During the entire transportation flight, the propulsion engine of the facility operates at minimum thrust.

After the helicopter exits to the specified starting point, the operator, using the control and launch panel, which is part of the external suspension system and located in the helicopter cabin, performs pre-launch control of the object and carries out its uncoupling, thereby ensuring its air start.

After the start, the object enters into a dive with a set of flight speed, the main engine automatically switches to the maximum power (traction) mode, and, upon reaching the required flight speed, the object is converted into horizontal flight by the on-board automation system, being controlled further in the normal mode, as with other ways to start.

The proposed external suspension system of unmanned aerial vehicles (figure 2) contains a cargo cable 4 and an electric cable 5, one end of each of which is mounted on a helicopter 3, and the other end is connected to a suspension beam, the body of which 7 (figure 3) is made in in the form of a hollow box with an electric lock 8 located in its middle lower part, two pairs of stop brackets 9 with adjustable stops 10 located in the front and rear parts of the beam, an aerodynamic stabilizer, consisting of a tubular shaft fixed to the rear of the beam tangs 11 and vertical keels 12, pivotally mounted on the vertical axis of the rod 11 and having the ability to deviate in different directions when the load is suspended from the action of the spring lever 13, mounted on the rear end of the beam, through cables or rods 14.

In this case, the upper end of the electric cable 5 has a control and start control panel 15 (Fig. 2), and the lower end has a plug of the tear-off electrical connector 16, fixed at the bottom of the beam 7 and connected to the reciprocal electrical outlet (not shown) of the load when it is on beam 7.

In addition, on the cargo cable 4 (FIG. 2), there is a fuel system for fueling the fuel system of the cargo during transportation with the main engine running to the starting point, including a fuel tank 17, a fuel hose 18 with an electrovalve 19 (FIG. 3), and a device for cutting off the electric cable and cable 20 in emergency situations, made, for example, in the form of a guillotine device, while all of the above elements are fixed to the cable by means of clamps 6, with the exception of the electric valve, structurally connected to the suspension beam.

The fuel recharge system can be either a forced fuel supply, for example, displacing it with gas or other known systems, or with a fuel supply by gravity, for which the fuel tank 17 is attached to the support cable 4, within its length, at a height h (Fig. 2 ), providing the necessary excess pressure of the fuel due to the creation of a hydraulic column.

Before lifting into the air, the object 1 is attached to the suspension beam 7 so that the plug of the tear-off electrical connector 16 and the fuel solenoid valve 19 enter the reciprocal sockets of the object 1, and the transport eyebolt 21 of the object 1 (Figs. 3 and 6) is caught by the electric lock hook 8 then the adjustable stops 10 select the gaps between the suspension beam 7 and the object 1.

When installing the object 1 on the beam, the lever 13 (Fig. 3), overcoming the resistance of the spring (not indicated in the drawing), turns clockwise, deflecting the vertical keels 12 in different directions by rods or cables 14 at a given angle (Fig. 5).

The deflected vertical keels 12 in flight, when transporting object 1 to the starting point, create an aerodynamic drag force that partially compensates the traction force of the marching engine and increases, in comparison with non-deflected keels, stabilizing the aerodynamic moment in the horizontal plane, orienting the towed object in the direction of the flight speed vector .

The suspension system works as follows:

when the operator starts the “Start” command (by pressing the corresponding button on the control and start panel), voltage is applied to the electric lock 8 and removed from the electrical elements of the fuel solenoid valve 19.

In this case, the electric lock 8 opens, freeing the object 1 from the suspension beam 7, and the electrovalve 19 shuts off the fuel supply to feed the cargo fuel system.

Under the influence of gravity, the object 1 moves away from the suspension beam 7, the plug of the electrical connector 16 and the solenoid valve 19 are disconnected from the reciprocal sockets of the object 1, and the lever 13, turning counterclockwise by the action of the spring, weakens the tension of the cables 14, which hold the vertical keels in a deflected position, which leads to their folding from the influence of aerodynamic forces, thereby reducing the overall aerodynamic drag of the suspension beam and, thereby, the tendency to toss it up.

In case of emergency during transportation of the object to the starting point, the device for cutting the cable and cable 20 is turned on, after which the object 1 with the remaining lower part of the suspension system is separated from the helicopter carrier 3.

Thus, the proposed method for the air start of unmanned aerial vehicles and an external suspension system for its implementation allows for air transportation, to increase the reliability and safety of the air start, to simplify the composition of the onboard equipment of unmanned objects while reducing the cost of air launch due to the universality of the use of the said method and suspension system.

Claims (2)

1. The method of air start of unmanned aerial vehicles, including ground preflight preparation of an unmanned aerial vehicle, connecting the external suspension system of an unmanned aerial vehicle to a carrier helicopter and an unmanned aerial vehicle, transportation to a launch point, pre-launch control and reset of an unmanned aerial vehicle, characterized in that the unmanned aerial vehicle is connected to the helicopter carrier is carried out using an external suspension system with a flexible cable, launching the main engine of an unmanned aerial vehicle The new apparatus is carried out before its transportation to the starting point, and the discharge is carried out with the marching engine running in the mode of its minimum thrust (power). 2. The external suspension system of unmanned aerial vehicles to a helicopter for an air launch, comprising a cargo cable fixed at one end to a helicopter and connected at the other end to a load suspension beam (unmanned aerial vehicle), a device for aerodynamic stabilization of cargo, made in the form of vertical keels, located symmetrically relative to its plane of symmetry behind the center of mass, characterized in that it is additionally equipped with an electric cable with a remote control new systems and control the start of unmanned aerial vehicles at the upper end and the plug of the tear-off electrical connector at its lower end, the fuel system of fueling the fuel system of the cargo, including the fuel tank and the fuel hose with an electrovalve, a device for cutting off the cable and the cargo cable, all of the above devices are fixed to the cable with clamps, with the exception of the fuel solenoid valve and the plug of the cable electrical connector, connected to the suspension beam, and the control panel connected to the upper free con the electric cable, and the load suspension beam is made in the form of a hollow box, in the central lower part of which there is a load suspension electric lock, a tear-off plug plug and a fuel solenoid valve, and on the sides of the beam ends two pairs of adjustable stops are rigidly fixed for mutual rigid fixation of the beam with the load, while the keels of the device for aerodynamic stabilization of the load are located at the rear end of the longitudinal rod, and the rod itself is mounted on the rear of the load suspension beam, and the keels are made with possible the deviation in different directions relative to the vertical axis when the load is suspended by means of two cables connected to a spring-loaded lever mounted on the rear end of the beam.

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