RU2523873C1 - Modular drone (versions) and bayonet joint for coupling of modules - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: in compliance with first version, drone is a tailless aircraft and comprises fuselage composed by nose module, central module and tail module, wing composed by left and right outer wings, ailerons, winglets, undercarriage front leg, undercarriage rear legs, engine and push propellers. In compliance with second version, this drone is a twin-boom aircraft. In compliance with both versions, fuselage modules are coupled by bayonet joint including male part, female part, plate spring, seal ring and bolts.

EFFECT: fast-release modules, good protection at rough landing.

4 cl, 4 dwg

Description

The invention relates to the field of aircraft, in particular, relates to the aerodynamic layout of unmanned aerial vehicles (UAVs).

Known modular unmanned aerial vehicle (patent for the invention of the Russian Federation No. 2422327, IPC B64C 3/38, 02/05/10), containing an elongated body with a supporting beam located along the body. Suspension nodes are placed on the carrier beam, while the rear suspension node is combined with the rotary node of the wing of the aircraft. The wing half-span is less than or equal to the distance between the nodes of the suspension.

A modular UAV has the following disadvantages: the central beam located along the entire hull complicates the assembly process of the aircraft, reduces the usable volume, while the beam must be manufactured with a high degree of accuracy to ensure minimum clearance between the modules, and the beam must be highly reliable. A UAV made in this way has a large mass and, therefore, has a low flight range.

A multivariate unmanned aerial vehicle is also known (patent for the invention of the Russian Federation No. 2323850, IPC B64C 7/00, dated June 15, 05), including the fuselage, wing with center wing, tail unit, power plant with fuel tank and airborne systems. The fuselage and wing are made in the form of a set of separate replaceable modules of similar functional purpose. The housing of each module is made in the form of a set of power elements and casing. Each module has the same docking nodes.

The disadvantage of this invention is the low security of the UAV modules and equipment during a hard landing.

The closest in technical essence and the achieved result to the claimed invention is a modular unmanned aerial vehicle (patent for US invention No. 7922115, IPC B64C 3/38 of 04/23/2007), including a fuselage consisting of a nose, tail and central modules, a wing located in the central module, each console of which consists of two modules - external and internal, interchangeable with each other, controls - ailerons located on two wing consoles, tail unit located in the tail mo muzzle of the fuselage, consisting of a rudder, rudders, vertical and horizontal stabilizers, front and rear landing gear, power plant and propeller of a pulling type located in the nose module of the fuselage.

The disadvantage of this invention is the increase in drag of the UAV due to the large number of aerodynamic surfaces, the propeller is unprotected during a hard landing, which can damage other UAV elements, and its functionality is limited due to the complexity of using different diagnostic equipment on the same UAV.

The most flashing in technical essence and the achieved result for a bayonet connection for docking modules is a bayonet connection (patent RU RU2370677, IPC F16B 21/04 of 12/10/2008) containing a girth piece with hermetically seated fingers and a girth piece with grooves made in the form of a hook, and the girth piece is made with a recess having a bevel towards the fingers, an o-ring, a spring installed in the recess of the girth part made with a locking protrusion.

The disadvantage of this invention for a modular UAV is the complexity of disassembling the UAV modules and the high forces acting on the casing of the UAV modules, which can lead to a loss of stability of the casing.

The objective of the present invention is to increase the reliability of an unmanned aerial vehicle during operation, expanding its functionality.

The technical result is a reduction in drag, providing quick-release modules through the use of bayonet-type connections, the protection of modules and equipment during a hard landing.

The problem is solved, and the technical result is achieved according to the first embodiment due to the fact that the unmanned aerial vehicle contains a fuselage consisting of a bow, a tail and a central module, a wing located in the central fuselage module, consisting of left and right consoles, controls are ailerons, located on two wing consoles, front and rear landing gear, power plant and propeller, according to the invention, the power plant and propeller made of a push type They are located in the rear fuselage module, winglets are located at the ends of both wing consoles, while the nose, tail and central fuselage modules are interconnected with bayonet-type locks, the wing consoles are connected to the central fuselage module using a docking unit, and the front landing gear is located in the bow module, near the diagnostic equipment.

Thus, we can conclude that the unmanned aerial vehicle is made according to the "tailless" scheme

The problem is solved, and the technical result is achieved according to the second embodiment due to the fact that the unmanned aerial vehicle contains a fuselage consisting of a bow, a tail and a central module, a wing located in the central fuselage module, consisting of left and right consoles, controls are ailerons, located on two wing consoles, tail unit located in the rear fuselage module, consisting of a rudder, rudders, vertical and horizontal stabilizers, front and rear landing gear, propulsion system and propeller, according to the invention, the propulsion system and propeller made of a push type are located in the rear fuselage module, the tail unit is attached to the wing consoles using two beams, while the nose, tail and central fuselage modules are interconnected bayonet-type locks, with the wing consoles connected to the central fuselage module using a docking unit, and the front landing gear is located in the nose module near the diagnostic equipment.

In addition, according to the invention, winglets are located at the ends of both wing consoles.

Thus, we can conclude that the unmanned aerial vehicle is made according to a two-beam scheme.

The problem is solved, and the technical result is also achieved through the use of a bayonet coupling for joining the fuselage modules with each other, containing a girth piece with hermetically set fingers and a girth piece with grooves made in the form of a hook, an o-ring, a spring, according to the invention, girth and girth parts are connected in one plane around the circumference, and the o-ring and the spring, made of a disk type, are located between the grasping and grasping th items wherein the bow and bow further detail elements fastened releasable connections, such as bolts, arranged on a circle.

The invention is illustrated by the following drawings:

Figure 1 - unmanned aerial vehicle (1 option), made according to the scheme "tailless".

Figure 2 - unmanned aerial vehicle (option 2), made according to the two-beam scheme.

Figure 3 - docking node.

4 is a bayonet connection.

The first unmanned aerial vehicle according to the first embodiment contains a fuselage consisting of a nose module 1, where interchangeable diagnostic equipment is installed, a central module 2, a tail module 3, a wing consisting of left 4 and right 5 consoles, left 6 and right 7 ailerons located on the consoles wings 4 and 5, left 8 and right 9 winglets located at the ends of both wing consoles 4 and 5, the front landing gear 10 located in the nose module 1, the rear landing gear 11 located in the central module 2, the power plant 12 and the propeller pusher type 13 located in the tail module 3 (figure 1, figure 2).

The unmanned aerial vehicle according to the second embodiment is characterized by the presence of beams 14 for attaching the tail unit to the wing consoles 4 and 5, the tail unit, consisting of a horizontal stabilizer 15, left 16 and right 17 vertical stabilizers, left 18 and right 19 rudders (figure 2) .

In both versions, the wing consoles 4 and 5 are connected to the central module of the fuselage 2 using the docking unit 20, in which the docking elements 21 and the squib 22 are located (Fig. 3).

In both versions, the fuselage modules 1-3 are interconnected by means of a bayonet connection containing frames, one of which is a girth piece 23, and the other is a girth part 24, and fingers 25, a disk-shaped spring 26 and an o-ring are sealed on the grounded part 23 27, arranged in series between the girth 23 and the girth 24 parts, which are fastened by elements of detachable connections, for example, bolts 28 located on one circle (figure 4).

The UAV operates as follows: the propeller 13 located in the module 3 is driven by a power plant 12 (which can be an internal combustion engine or an electric motor) and creates a useful traction that gives acceleration to the UAV.

On the wing consoles 4 and 5, most of the lifting force is created and, at a certain speed, when the lifting force exceeds the weight of the UAV, the climb begins. The UAV pitch control according to the first embodiment is carried out by ailerons 6 and 7, the change in flight direction is carried out by turning the winglets 8 and 9.

The UAV pitch control according to the second embodiment is carried out by ailerons 6 and 7 and the elevator 15, the flight direction is changed by turning the rudders 18 and 19.

In the case of a hard landing of the UAV, wing consoles 4 and 5 are fired at the docking elements 21 using the squib 22 installed in the docking assembly 20, as a result of which the kinetic energy of the fuselage is extinguished, and the remaining kinetic energy is dissipated in the fuselage skin. Thus, the safety of equipment located inside the fuselage is achieved. The front landing gear 10 is located next to the fuselage target load module 1 and, in the case of a rigid landing of the fuselage on the nose, the front landing gear 10 will protect the target load (diagnostic equipment) from damage.

The fuselage modules 1-3 are interconnected using bayonet-type quick couplers, and the wing consoles 4-5 are joined to the fuselage central module 2 along the docking elements 21 using the docking station 20. The bayonet connection for the fuselage modules is possible due to the fact that all fuselage loads are transmitted through the power elements to the skin.

The bayonet joint works as follows: during assembly, the girth piece 23, belonging, for example, to the nose module of the fuselage 1, is inserted into the grooves of the girth part 24, belonging to the central module 2, until it stops, while the Belleville spring 26 is compressed, and the ring 27 seals the joint, after whereby the central 2 and the bow 1 of the fuselage modules are rotated relative to each other, for example, clockwise, while the fingers 25 go into the grooves of the girth piece 24. During the operation of the bayonet connection, girth 23 and girth with 24 parts working in compression, bending and stretching, but at the same time there is no loss of stability of the skin of the fuselage models 1-3, fingers 25 work in tension. In order to prevent the fuselage modules 1-3 from being unscrewed with respect to each other, the axial dimensions of the cup spring 26 and the sealing ring 27 are selected so that when the bayonet joint works on the working surfaces of the girth 23 and girth 24 parts, friction forces are created to prevent unscrewing. To prevent unscrewing of the fuselage modules 1-3 relative to each other, detachable connections are also provided, for example, bolts 28 located on the same circle connecting the girth 23 and girth 24 of the bayonet coupling part.

Such a modular design will ensure high reliability of the UAV during operation, expand its functionality due to various interchangeable diagnostic equipment located in the nose module 1, and allow UAV assembly using a minimum set of tools.

So, the claimed invention allows to increase the reliability of the UAV during operation, to expand its functionality, and also provides a reduction in drag, quick-detachable modules through the use of bayonet-type connections, the security of the modules and equipment during a hard landing.

Claims (4)

1. A modular unmanned aerial vehicle containing the fuselage, consisting of the nose, tail and central modules, a wing located in the central module, consisting of left and right consoles, controls - ailerons located on two wing consoles, front and rear landing gear, power plant and propeller, characterized in that the unmanned aerial vehicle is made according to the "tailless" scheme, power plant and propeller made of a push type, located in the tail module of the fusel Well, at the ends of both wing consoles there are winglets, while the nose, tail and central fuselage modules are interconnected by bayonet-type locks, with the wing consoles connected to the central fuselage module using a docking unit, and the front landing gear is located in the nose module near the diagnostic equipment . 2. A modular unmanned aerial vehicle containing a fuselage consisting of a bow, a tail and a central module, a wing located in the central module, consisting of left and right consoles, controls - ailerons located on two wing consoles, a tail unit located in the tail fuselage module, consisting of elevator, rudder, vertical and horizontal stabilizers, front and rear landing gear, power plant and propeller, characterized in that the unmanned aerial vehicle the apparatus is made according to the two-beam scheme, the power plant and the propeller made of the pushing type are located in the rear fuselage module, the tail unit is attached to the wing consoles using two beams, while the nose, tail and central fuselage modules are interconnected by bayonet-type locks, moreover, the wing consoles are connected to the central fuselage module by means of a docking unit, and the front landing gear is located in the nose module near the diagnostic equipment. 3. The modular unmanned aerial vehicle according to claim 2, characterized in that there are winglets at the ends of both wing consoles. 4. A bayonet connection comprising a girth piece with hermetically seated fingers and a girth piece with hook-shaped grooves, an o-ring, a spring, characterized in that the girth and girth parts are connected in the same plane around the circumference, and the o-ring and spring, made dish type, located between the girth and girth parts, and girth and girth parts are additionally fastened by elements of detachable connections, such as bolts, decomposition on a circle.

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