RU188791U1 - IMPACT MULTICOPTER - Google Patents

Abstract

The invention relates to rotary-wing aircraft with two or more screws and can be used to create military unmanned aerial vehicles. The impact multikopter contains a fuselage with remote beams on which the frames are installed so that they can rotate around an axis of 360 °, means of thrust with rotors placed in annular channels installed in the frames can be rotated through an angle of 360 ° along the axis of the fuselage beams and at least one block of unguided aircraft rockets integrated into the multicopter fuselage and installed perpendicular to its construction horizontal. The technical result is the provision of the possibility of targeting unguided aircraft missiles in an unlimited spatial range and simplifying the design of the aircraft.

Description

The invention relates to rotary-wing aircraft with two or more screws and can be used to create unmanned aerial vehicles for military purposes with an unlimited targeting range of unguided aircraft missiles (NAR).

When creating military aircraft complexes, it is essential to equip them with a wide range of weapons and their constructive placement on an aircraft.

An integral part (type) of weapons of modern combat aircraft, significantly expanding their tactical capabilities and combat properties are the NAR. Also important is the economic component of the conduct of hostilities using NAR, it is known [1] that the cost of guided aircraft rockets is 6 or more times the cost of NAR of a comparable caliber.

Depending on their model, NAR on aircraft is placed separately on special brackets - launchers or in blocks - launchers. The blocks themselves and / or brackets in most cases are installed parallel to the building horizontal of the fuselage outside the aerodynamic contours of the structural elements of the aircraft (fuselage, wing), which significantly impairs its aerodynamic quality by increasing drag, increases its sensitivity to variable atmospheric phenomena (for example, wind gusts variable forces and directions), and degrades other characteristics, including combat survivability. Such an installation of NAR blocks is due to the constructive complexity of organizing the removal of jet stream gases during the launch of rockets when placed in the internal cavities of the fuselage, which has a longitudinal size that is much larger than the longitudinal size of NAR blocks. This refers to aircraft of both aircraft and helicopter type; both to manned and unmanned.

Known technical solutions, in which aviation weapons during transportation are parallel to the constructional horizontal of the fuselage in the intra-fuselage space of the aircraft, for example [2, 3]. They contain a special mechanism by which they are removed from the fuselage for launching missiles, thus the design of the aircraft becomes more complicated and the trigger itself reduces the useful volume of the intra-fuselage space.

Guidance on the goal of the NAR is carried out using the maneuverable capabilities of the aircraft, limited to varying degrees depending on the type (aircraft, helicopter) and the design of the specific aircraft.

Known technical solutions of aircraft aircraft (Messerschmitt Me-163) [4] and helicopter (impact multicopter with a grenade launcher module) [5] types, in which the installation for launching missiles (grenades) are installed vertically. In the first case, the grenade launchers are installed vertically in the root of the wing, the thickness of which corresponds to the length of the tubular launcher and does not require the complexity of the jet exhaust system when firing grenades. In the second case, the grenade launcher is mounted on a bracket outside the multikopter fuselage, which significantly impairs its aerodynamic characteristics.

In terms of targeting missiles to the target, the analogs are limited by the maneuverability of the aircraft, as well as when launching launchers parallel to the horizontal construction of the fuselage.

The closest to the proposed utility model for the purpose and general essential features is the technical solution "Aircraft" [6]. The prototype is a multicopter and contains means of thrust with bearing screws and a fuselage with remote beams on which the frames are installed so that they can rotate around the axis of the beams through an angle of 360 °, and the means of thrust with bearing screws are placed in annular channels installed in frames that can be turned through an angle 360 ° along the axis of the fuselage beams.

The prototype provides the possibility of spatial orientation of the fuselage relative to the direction of thrust of the rotors in an unlimited range, regardless of the trajectory and mode of motion, including modes of take-off, hovering, horizontal and vertical flight, landing. Consequently, the working body of the payload installed in the fuselage has an unlimited range of guidance. However, when performing the prototype fuselage in aerodynamic form, creating lifting force to increase the economy and speed of horizontal flight when moving the multikopter from the base to the place of performing the required work and when using the NAR units integrated into the fuselage, the prototype has disadvantages in terms of necessity Complications of the design with jet exhaust gases during launching of rockets or with the output devices of the NAR from the intra-fuselage space properties.

The technical result of the utility model is to provide the possibility of targeting NAR units integrated into the fuselage in an unlimited spatial range and simplifying the design of the aircraft.

The technical result is achieved by the fact that in the well-known multikopter [6], which by virtue of its distinctive features has the ability to change the spatial orientation of the fuselage in an unlimited range regardless of the trajectory and flight mode and containing the NAR unit, the rocket unit is integrated into the multicopter fuselage and installed perpendicular to its construction plane horizontally.

The essence of the utility model is illustrated by drawings, where in FIG. 1 shows a diagram of the proposed impact multicopter top view; FIG. 2 is a side view in section; in fig. 3a shows the orientation of the means of thrust of the multikopter relative to the fuselage during take-off, landing, horizontal flight “by helicopter” and hovering; in fig. 3b - orientation of the multi-rotor multi-rotor relative to the fuselage during horizontal flight “by plane”; in fig. 4 is a schematic representation of the range of guidance of the NAR of the proposed utility model to the target; FIG. 5 - as an illustration of the practical application of the utility model, an attack of the proposed multikopter on an aerial target is presented.

Impact multikopter contains the fuselage 1, made in an aerodynamic form, creating a lifting force, with remote beams 2, on which are fixed the frame 3 with the possibility of rotation around the axis of the beams at an angle of 360 °; thrust means with bearing screws 4 placed in annular channels 5 installed in frames 3 so that they can be rotated through 360 ° along the axis of the beams 2 of the fuselage 1; integrated into the fuselage 1 multikopter and installed perpendicular to the plane of its building horizontal block 6 NAR with missiles 7 placed in tubular guides 8. The arrows indicate the direction of aiming at the target NAR.

The multirotor also contains the corresponding drives and command systems for controlling them (not shown) for coordinated joint or separate control of the position of the annular channels 5 with the thrust means 4 and frames 3 relative to the fuselage 1, which are well-known technical means used in existing aircraft structures [7, 8, 9, 10].

Impact multikopter works as follows.

The take-off (landing) is carried out vertically “by helicopter” (the orientation of the means of thrust 4 relative to the fuselage 1 is shown in Figs. 1, 2, 3a) with the benefits of rotary-wing aircraft resulting from this. In the same way, horizontal flight and hovering of the multicopter can be carried out.

Moving from the base to the point of impact can be carried out "by aircraft" with the orientation of the means of thrust relative to the fuselage, as shown in FIG. 3b, while taking advantage of the aircraft’s airplanes in terms of speed and efficiency of flight, and the intra-body placement of the NAR unit 6 does not adversely affect its aerodynamic characteristics.

When arriving at the location of the target, the multikopter, using the maneuverable capabilities of the prototype [6], performs the necessary manipulations with the spatial position of the fuselage for aiming the NAR unit 6 at the target. In this case, the point of view of the NAR can be located anywhere in an imaginary sphere, in the center of which is a shock multicopter (Fig. 4), that is, in an unlimited range in any flight mode or hovering multicopter.

With alternate or salvo launch of missiles 7, there is no need for a mechanism for removing the missiles from the intra-fuselage space and for removing the gases of the jet streams of the missiles, which greatly simplifies the design of the aircraft and eliminates the recoil effect that occurs invariably when using the mechanism for removing gases by extinguishing or changing the direction, affecting the accuracy of targeting.

FIG. 5 shows an example of the practical application of the proposed impact multikopter when aiming NAR at an air target.

The set of distinctive features of the proposed utility model, namely, intrabody vertical placement in the multicopter of the NUR unit and essential features of the known aircraft [6] ensures the achievement of the stated technical result - the possibility of targeting the NAR target in an unlimited spatial range and simplifying the design of the aircraft. The achieved technical result allows the claimed impact multicopter to be used as an effective means of supporting military units in direct contact with the enemy when performing antiterrorist operations in forest, mountain and urban conditions when solving problems of struggle in low-intensity conflicts with poorly armed formations.

Information sources

1. Aircraft missile munitions. Appointment, composition and classification of NAR.

URL: https://studopedia.su/6_44017_neupravlyaemie-aviatsionnie-raketi-kak-sredstva-porazheniya.html. The date of appeal is 09/18/2018.

2. Rotary launcher system for aircraft (Rotary launcher system for an aircraft). U.S. Patent No. 4,637,229A. IPC B64D 7/08. 01.20.1987.

3. Intra-vent multi-position starter. Patent of the Russian Federation for useful model №119453. IPC F41F 3/06. 08/20/2012.

4. Me 163 Luftwaffe fighter jet. Tests of new weapons. URL: http://arsenal-info.ru/b/book/2744958222/2#. The date of the appeal is 09/09/2018.

5. Russian shock multikopter.

URL: https://news.softodrom.ru/ap/b24217.shtml. The date of the appeal is 09/09/2018.

6. Aircraft. RF patent for the invention №2656932. IPC В64С 27/08, В64С 27/28. 07.06.2018.

7. Airplane vertical takeoff and landing. US patent No. 3037721 A, IPC WC64 29/00. 06/05/1962.

8. The helicopter. RF patent for invention №2263049. IPC VS64 27/52. 10.27.2005

9. Bogdanov, Yu.S., Mikheev, R.L. The design of the helicopters. M .: Mashinostroenie, 1990; URL: http://xaribda.ru/node/68. The date of the appeal is 09/27/2018.

10. Ruzhinsky E.I. American vertical take-off aircraft URL: http: //coolib.eom/b/128556/read. The date of the appeal is 09/27/2018.

Claims (1)

An impact multikopter containing a fuselage with remote beams on which the frames are installed can be rotated around an axis of 360 °, means of thrust with bearing screws placed in annular channels installed in the frames can be rotated by an angle of 360 ° along the axis of the fuselage beams and at least one block of unguided aircraft rockets, characterized in that the block of unguided aircraft rockets is integrated into the multikopter fuselage and mounted perpendicular to its building horizontal.

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