RU2754278C1 - Unmanned aircraft with parachute landing system - Google Patents

Abstract

FIELD: aircrafts.

SUBSTANCE: invention relates to the field of aeroplane-type unmanned aircrafts. The unmanned aircraft is made according to the tailless aerodynamic aeroplane configuration, equipped with two push-type engines, a parachute compartment located in the rear of the fuselage, and an air shock absorber in form of two inflatable bags. In one variant of implementation, the length of the unmanned aircraft is 1.85 m, the wingspan is 5 m, and the takeoff mass is 75 kg.

EFFECT: invention is intended to improve reliability and safety of parachute landing in the presence of high flight characteristics.

8 cl, 4 dwg

Description

Technology area

The invention relates to the development and application of mobile unmanned aerial systems with unmanned aerial vehicles of the aircraft type with parachute landing, intended for air surveillance, reconnaissance, detection, target designation and laser illumination of targets for guided munitions guidance. An unmanned aerial vehicle can be used in civilian areas, for example, when detecting emergencies and eliminating their consequences.

State of the art

In unmanned aerial vehicles, parachute landing systems are used both for the regular landing of unmanned aerial vehicles and for their emergency landing.

Known unmanned aerial vehicle with a parachute landing system according to the patent for the invention of the Russian Federation RU 2456211, published on 20.07.2012. It contains a fuselage, two wing consoles and a parachute landing system that includes an pilot parachute, main parachute, slings and a harness. The parachute system is located inside the fuselage. The lines of the parachute system are laid in a common protective cover, and the lines of the harness system are attached to the end parts of the wing by means of three-degree hinges and holders. Parts of the wing console are made with the possibility of their rotation about an axis parallel to the wing chord, and are equipped with retaining locks. In flight, the harness lines are laid in a channel located to the right and left along the fuselage and along the wing consoles. To land, after stopping the engine, at the command of the ground control station operator, the pilot parachute flaps are opened, the fixing shell is released, the pilot parachute canopy is pushed out with the help of a spring in the direction opposite to the movement of the unmanned aerial vehicle, the canopy of the main parachute is pulled out, which, after opening, slows down the longitudinal movement to zero. speed. At the command of the autopilot, the electric drives of the reducer of the locking locks turn and release the wing consoles, which, when folded, provide a smooth movement of the canopy of the main parachute to the vertical position. Landing an unmanned aerial vehicle with wing consoles folded in a vertical plane avoids their damage under difficult landing conditions and reduces the likelihood of the harness lines and the main parachute lines getting caught in the tail unit when the main parachute transitions from the horizontal position to the vertical position. However, attaching the lines of the suspension system not to the fuselage, but to the wing consoles requires a significant increase in their strength, which, together with the three-degree hinges and holders, significantly complicates the design of the unmanned aerial vehicle, increases its weight and cost, leads to a decrease in the speed and range of flight, as well as limits the mass of the payload.

The known method of parachute landing of an unmanned aircraft and a parachute landing system of an unmanned aircraft according to the patent for the invention of the Russian Federation RU 2592961, published on July 27, 2016. An unmanned aircraft with a parachute landing system contains a parachute with slings and a harness, two wing consoles docked by means of fixed hinge nodes with the ability to rotate relative to the axis parallel to the wing chord and articulated folding of the consoles when they are unlocked. The articulated joints of the wing consoles with the aircraft are made easily detachable when disposable fixation elements are destroyed from the calibrated load after the consoles are turned towards the lower surface of the aircraft, to which the parachute harness is attached, on which the parachute lines detachment lock or parts thereof is installed. The consoles are equipped with flexible rods. The flexible rod of one wing console is connected to the lock locking unit. The method of parachute landing of an unmanned aircraft is characterized by the fact that when the landing parachute is deployed, the aircraft is turned over and the upper surface is lowered, it is landed on one of the wingtips of the wing consoles and the impact energy is absorbed by the work to destroy the fixing element of the hinge node of the console when it is levered from the shock load on tip and separate the console from the aircraft. The group of inventions is aimed at ensuring a reliable fit during operation. The main disadvantage of this technical solution is the need to carry out repairs after each landing to replace the destroyed disposable fixation elements and damaged wingtips from impact when landing on an uneven rocky surface. This complicates and increases the cost of operation.

Known small unmanned aerial vehicle with an automatically released parachute under US patent for invention US 6685140, published 03.02.2004. The glider is made according to the classic aircraft scheme, containing the fuselage, wing, tail, internal combustion engine, mounted in front of the fuselage and equipped with a pulling propeller. The parachute compartment is located at the rear of the fuselage between the wing and the tail unit. It is equipped with a folded parachute and a parachute ejection device. Upon reaching certain flight conditions: trajectory, altitude and speed, as well as the number of engine revolutions, the microprocessor of the flight control system issues a command to eject the parachute up and back at an acute angle to the direction of flight. The main disadvantages of the technical solution are the possibility of an emergency due to the hooking of the parachute lines to the tail unit and the need to strengthen the strength of the fuselage structure not only in the longitudinal, but also in the transverse direction to resist shock loads when the parachute is ejected at an acute angle.

Known unmanned aerial vehicle with a parachute release device for US patent for invention US 8191831, published 05.06.2012. On the basis of the set of common essential features, the technical solution for the specified patent was chosen as a prototype.

An unmanned aerial vehicle, made according to an aircraft scheme, containing a fuselage, a wing attached to the fuselage and made in the form of a left wing console and a right wing console, equipped with control surfaces symmetrically located on the trailing edge of the wing consoles, a propulsion system including an engine with a push-type propeller attached to the fuselage at the rear of the unmanned aerial vehicle, a navigation system, a flight control system, two-way radio communications with a ground control station, a payload in the form of an electro-optical system installed in the front of the fuselage of an unmanned aerial vehicle, a parachute landing system, including a parachute a compartment installed in the fuselage, a parachute located in the parachute compartment, a parachute compartment flap, a mechanism for opening the parachute compartment flap and ejecting a parachute, a flexible parachute halyard laid along the surface of the rear fuselage, one end of which is attached to the strut memory of the parachute, and the other end is attached to three straps of the harness system for attaching the halyard to the upper part of the fuselage in the area of the center of gravity of the unmanned aerial vehicle, a mechanism for releasing the parachute after landing, an air shock absorber made in the form of an inflatable bag placed on the side of the lower part of the fuselage.

The main disadvantage of the unmanned aerial vehicle of the prototype is low reliability due to the relatively high probability of an emergency under adverse conditions due to the hooking of the harness lines and the lines of the parachute thrown down by the tail unit and the engine propeller, which are located in the aft fuselage behind the parachute compartment.

The essence of the invention

The declared unmanned aerial vehicle with a parachute landing system makes it possible to increase the reliability and safety of a parachute landing, to increase the duration and range of flight.

This positive effect is achieved due to the fact that the unmanned aerial vehicle is made according to the tailless aerodynamic scheme, in which the wing is equipped with a wing center section and control surfaces made in the form of elevons, the propulsion system is equipped with two engines with push-type propellers, the first engine is located on the left rear part wing center section, to which the left wing console is attached, the second engine is located on the right rear part of the wing center section, to which the right wing console is attached, the ratio of the distance between the longitudinal axes of the first engine and the second engine to the fuselage length of the unmanned aerial vehicle is selected in the range from 0.4 to 0.5, the ratio of the distance between the longitudinal axes of the first engine and the second engine to the wing span of the unmanned aerial vehicle is selected in the range from 0.1 to 0.2, the parachute compartment is located in the rear of the fuselage, the parachute compartment flap is made in the form of a truncated sphere ry, adjacent to the rear part of the fuselage and forming a single smooth streamlined surface with it, in the parachute compartment in the central part of the front end partition there is a device for intercepting a flexible parachute halyard, a flexible parachute halyard attached to the device for intercepting a flexible parachute halyard and in the initial position is laid along the upper part the front end bulkhead, the upper inner surface of the parachute compartment and along the upper outer rear part of the fuselage up to the attachment point to the three lines of the harness for attaching the halyard to the upper part of the fuselage in the area of the center of gravity of the unmanned aerial vehicle.

In an unmanned aerial vehicle, the propulsion system is equipped with two electric motors with push-type propellers with folding blades.

In an unmanned aerial vehicle, the mechanism for opening the lid of the parachute compartment and ejecting the parachute is equipped with a controlled electric lock.

In an unmanned aerial vehicle, the parachute release mechanism after landing is equipped with a controlled electric lock.

In an unmanned aerial vehicle, the front end partition of the parachute compartment is made in the form of a conical diaphragm with apex directed towards the center of the fuselage.

In an unmanned aerial vehicle, the inflated air shock absorber is made in the form of two cylindrical inflatable bags, the first inflatable bag is located on the side of the lower part of the fuselage under the left part of the wing center section, the second inflatable bag is located on the side of the lower part of the fuselage under the right side of the wing center section.

Brief Description of Drawings

In the future, the invention is illustrated by specific examples of its implementation with reference to the attached drawing (Figure 1), which presents a general view of an unmanned aerial vehicle, a drawing (Figure 2), which shows a top view of an unmanned aerial vehicle, a figure (Figure 3), which is a longitudinal section of the rear of the unmanned aerial vehicle with a parachute compartment, and a drawing (Figure 4), which shows the unmanned aerial vehicle at the time of landing during parachute landing.

Implementation of the invention

Unmanned aerial vehicle 1 (Figure 1), made according to the tailless aerodynamic aircraft scheme, contains a fuselage 2, a wing 3 attached to the fuselage 2, including a left wing console 4, equipped with control surfaces made in the form of elevons 5, a right wing console 6, equipped with control surfaces made in the form of elevons 7, and the center section of the wing 8. The propulsion system 9 is located in the rear part of the unmanned aerial vehicle 1 and is equipped with two engines with push-type propellers. The first engine 10 with the propeller 11 is located on the left rear part of the wing center section 8, to which the left wing console is attached 4. The second engine 12 with the propeller 13 is located on the right rear part of the wing center section 8, to which the right wing section 6 is attached. The parachute compartment 14 is located in the rear part of the fuselage 2. The flap of the parachute compartment 15 is made in the form of a truncated sphere, adjacent to the rear part of the fuselage 2 and forming a single smooth streamlined surface with it. The payload 16, made in the form of an electro-optical system, is installed in the front of the fuselage 2 of the unmanned aerial vehicle. Such a design of an unmanned aerial vehicle 1 with a parachute compartment in the rear of its fuselage 2 provides, during landing, a reliable and safe release of the parachute in the direction opposite to the direction of flight, the opening and filling of the parachute, as well as its unhindered transfer from the braking horizontal position to the vertical position for a smooth landing. ...

To achieve high flight characteristics of an unmanned aerial vehicle 1 (carrying capacity, speed, controllability, altitude, range and duration of flight), provided that the necessary structural strength and limited mass-dimensional characteristics are provided, (Figure 1 and Figure 2), as well as for optimal placement of aircraft systems and aircraft equipment of the unmanned aerial vehicle and payload means the ratio of the distance between the longitudinal axes of the first engine 10 and the second engine 12 - Рд to the fuselage length 2 - Дф of the unmanned aerial vehicle 1 is selected in the range from 0.4 to 0.5, and the ratio of the distance between the longitudinal the axes of the first engine 10 and the second engine 12 - Рд to the wingspan 3 - Рк of the unmanned aerial vehicle 1 are selected in the range from 0.1 to 0.2.

In the parachute compartment 14 (Figure 3), located in the rear part of the fuselage 2 and covered from the rear by the flap 15, the canopy and lines of the parachute 17 are placed in the folded state, and the front end partition 18 is also installed, in the central part of which is mounted the device for the transfer 19 of the flexible halyard 20 parachute 17, equipped with an electromechanical lock 21. In the initial position, the flexible rope 20 of the parachute 17 is attached to the device for intercepting the flexible rope of the parachute 19 and is laid along the upper part of the front end partition 18, the upper inner surface of the parachute compartment 14 and along the upper outer surface of the rear part of the fuselage 2 to attachment point 22 to three slings 23 of the harness for attaching the flexible halyard to the upper part of the fuselage 2 in the area of the center of gravity of the unmanned aerial vehicle, at an equidistant distance from it. When the parachute 17 is released, the detachable flap 15, attached by a sling to the folded parachute 17, performs the function of the pilot parachute. After opening the electromechanical lock 24, it is separated from the fuselage 2 forcibly by means of three springs and pulls the parachute 17 behind it. The unmanned aerial vehicle 1 continues its horizontal flight with stopped engines and folded propeller blades. The parachute 17 under the influence of the incoming air flow gradually opens and pulls the flexible halyard 20 attached to the interceptor 19 with an electromechanical lock 21. When the canopy of the parachute 17 is fully opened, the maximum overload acts along the longitudinal axis and is normally perceived by the design of the unmanned aerial vehicle 1. When the speed of the unmanned aerial vehicle decreases of the aircraft, the trajectory of its flight smoothly changes from horizontal to inclined ballistic, and then to vertical under the influence of gravity. After a certain time of reducing the flight speed, the flexible halyard 20 of the parachute 17 is interlocked from the electromechanical lock 21 to the front end partition 18 inside the fuselage to an attachment on the outer surface of the fuselage to give the unmanned aerial vehicle a horizontal position upon landing.

To reduce the shock loads acting on the unmanned aerial vehicle 1 and on the means of its payload 16 when touching the earth's surface, an air shock absorber is installed, in an inflated state made in the form of two cylindrical inflatable bags (Figure 4). The first inflatable bag 25 in the inflated state is placed on the side of the lower part of the fuselage 2 under the left part of the wing center section 8. The second inflatable bag 26 in the inflated state is located on the side of the lower part of the fuselage 2 under the right side of the wing center section 8. The inflatable bags before landing at the command of the automatic control or operator are filled with air from a small cylinder in which he is under pressure. When it touches the earth's surface, air is smoothly released through special holes in the inflatable bags. This eliminates the impact of the unmanned aerial vehicle on the earth's surface and rebound from it. Thus, the landing is softened and the shock loads are significantly reduced to preserve the design of the unmanned aerial vehicle and the payload.

Due to the modular design of the unmanned aerial vehicle, it is possible to use the payload and power plant with different weight and size characteristics within the same structural framework.

Pushing propellers during operation do not negatively affect the performance of the payload sensors in the front hemisphere.

The design of the airframe of the unmanned aerial vehicle is mainly made of polymer composite materials, which make it possible to obtain well-streamlined surfaces of double curvature during the manufacturing process. In one embodiment, the length of the unmanned aerial vehicle is 1.85 m, the wingspan is 5 m, and the take-off weight is 75 kg.

The design of the unmanned aerial vehicle has the necessary rigidity and strength to carry out ejection launch and parachute landing during long-term trouble-free operation. The use of an inflatable air cushion at the time of landing allows to significantly reduce shock loads on the unmanned aerial vehicle itself and its payload.

The unmanned aerial vehicle, in comparison with the prototype, has a high reliability and safety of parachute landing in the presence of high flight characteristics in relation to the duration, range and controllability of the flight. For takeoff and landing, it does not require an airfield infrastructure.

In terms of its flight and operational characteristics, as well as the composition of the payload, an unmanned aerial vehicle can be effectively used in a weapon aiming system for searching, detecting, tracking, determining coordinates and laser illumination of single and group targets for firing weapons that use unguided ammunition. and guided ammunition with semi-active laser guidance.

Claims (32)

1. Unmanned aerial vehicle, made according to the aircraft scheme, containing - fuselage, - a wing attached to the fuselage and made in the form of a left wing console and a right wing console, equipped with control surfaces symmetrically located on the trailing edge of the wing consoles, - a propulsion system comprising a push-type propeller engine attached to the fuselage at the rear of the unmanned aerial vehicle, - navigation system, - flight control system, - means of two-way radio communication with a ground control point, - a payload in the form of an electro-optical system installed in the front of the fuselage of an unmanned aerial vehicle, - parachute landing system, including - a parachute compartment installed in the fuselage, - a parachute placed in the parachute compartment, - a flap of the parachute compartment, - a mechanism for opening the sash of the parachute compartment and ejection of the parachute, - a flexible parachute halyard, laid along the surface of the rear part of the fuselage, one end of which is attached to the parachute lines, and the other end is attached to three straps for attaching the halyard to the upper part of the fuselage in the area of the center of gravity of the unmanned aerial vehicle, - parachute release mechanism after landing, - an air shock absorber made in the form of an inflatable bag located on the side of the lower part of the fuselage, characterized in that in order to increase the reliability of the parachute landing - the unmanned aerial vehicle is made according to the tailless aerodynamic scheme, in which the wing is equipped with a wing center section and control surfaces made in the form of elevons, - the propulsion system is equipped with two engines with push-type propellers, - the first engine is located on the left rear part of the wing center section, to which the left wing console is attached, - the second engine is located on the right rear part of the wing center section, to which the right wing console is attached, - the parachute compartment is located at the rear of the fuselage, - the wing of the parachute compartment is made in the form of a truncated sphere, adjacent to the rear of the fuselage and forming a single smooth streamlined surface with it, - in the parachute compartment in the central part of the front end bulkhead there is a device for intercepting a flexible parachute halyard, - the flexible parachute halyard is attached to the flexible parachute halyard and in the initial position is laid along the upper part of the front end bulkhead, the upper inner surface of the parachute compartment and along the upper outer rear part of the fuselage up to the attachment point to three straps of the harness for attaching the halyard to the upper part of the fuselage in the area of the center of gravity of the unmanned aerial vehicle. 2. The unmanned aerial vehicle according to claim 1, in which the ratio of the distance between the longitudinal axes of the first engine and the second engine to the length of the fuselage of the unmanned aerial vehicle is selected in the range from 0.4 to 0.5. 3. The unmanned aerial vehicle according to claim 1, in which the ratio of the distance between the longitudinal axes of the first engine and the second engine to the wingspan of the unmanned aerial vehicle is selected in the range from 0.1 to 0.2. 4. The unmanned aerial vehicle of claim. 1, wherein the propulsion system is equipped with two electric motors with push-type propellers with folding blades. 5. The unmanned aerial vehicle according to claim 1, wherein the mechanism for opening the lid of the parachute compartment and ejecting the parachute is provided with a controlled electric lock. 6. The unmanned aerial vehicle according to claim 1, wherein the parachute release mechanism after landing is provided with a controlled electric lock. 7. The unmanned aerial vehicle according to claim 1, in which the front end partition of the parachute compartment is made in the form of a conical diaphragm with apex directed towards the center of the fuselage. 8. The unmanned aerial vehicle according to claim 1, in which the air shock absorber in the inflated state is made in the form of two cylindrical inflatable bags, the first inflatable bag is located on the side of the lower part of the fuselage under the left part of the wing center section, the second inflatable bag is located on the side of the lower part of the fuselage under the right wing center section.

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