Unmanned aerial vehicle (options)

 

The invention relates to aviation. The device contains two fuselage, connected in the rear part of the wing, and in the bow - front horizontal tail, vertical tail, the engines and chassis. The fuselage at the tail end are interconnected by a center section of the wing and does not extend beyond the rear edge of the wing. The canards are made with low aspect ratio. In the second embodiment, the vertical tail is made of two keels, which are mounted on the center section of the wing is inclined to each other. Kili is connected to the fairing. One keel or both of the keel is installed on the center section of the wing hinge can be rotated about an axis parallel to the axis of symmetry of the apparatus, and one fin connected to the fairing with the possibility of the connector. Offer options invention is aimed at providing a circular view in the azimuth of the radar station. 2 c. and 20 C.p. f-crystals, 8 ill.

Group of inventions relates to unmanned aerial vehicles (UAV).

Unmanned aerial vehicles (UAV) can be applied to solve a variety of tasks that manned aircraft due to various reasons narkologicheskii control, air traffic control, control of Maritime navigation, communications and other

When monitoring the airspace, land and water surfaces, depending on the specific tasks can be carried out aerial photography, control hydro-meteorological conditions, atmospheric research, radiometric monitoring disaster areas, seismic monitoring, inspection compliance, control of gas and oil pipelines, power lines, geological observations, subsurface sensing, the study of ice conditions, rough seas.

Interest in UAVS due to their efficiency during operation, eliminating the risk to the lives of the crew, limitations on operational loads, defined human physiological capabilities, the ability to monitor many points in a short period of time.

The peculiarity of UAVS is the possibility of continuous monitoring of surface and air space when a large object is deleted observations using various sensors.

UAVS can be used not only for the above purposes, but also for others, for example, control of the state borders solved in the case of UAVS.

The prior art unmanned aerial vehicle (see RF patent 2065379, CL 64 With 39/02, publ. 20.08.1996). Specified aircraft includes a fuselage, two bearing surfaces, the United ends together, the vertical and horizontal tail, engines. One load-bearing surface mounted in the front of the fuselage, and the other bearing surface is located in the tail section of the aircraft on the vertical tail - fin. Both load-bearing surface mounted inclined to the horizontal plane of the fuselage and connected to each other so that they form the shape of a regular polygon, such as a rhombus, under condition of providing the same resolution in all directions of the pattern. In the joints of the bearing surfaces, there are additional console. The horizontal stabilizer consists of a front and a tail. The canards are placed parallel to the bearing surface, installed in the forward fuselage, and the tail horizontal stabilizer is made of articulated from the bearing surfaces, forming the shape of a closed polygon. The engines are located in the middle part of the fuselage on the pylons can be rotated in the information processing, transmitting and receiving units. Antenna placed inside the wing and horizontal tail and is made of two types - passive, i.e. operating in the reception mode signal, and active. A disadvantage of this scheme is the low bearing capacity of the wing, which does not allow for the required glide ratio and, accordingly, the desired duration of the flight.

Also known unmanned aerial vehicle developed by the company "Northrop Grumman" (see AVIATION WEEK & SPACE TECHNOLOGY, November 20, 2000, page 52). This plane has a wing consisting of two bearing surfaces - the front, mounted in the forward fuselage, and the rear, installed in the rear fuselage of the aircraft. Thus, the wing is made in the form of a rhombus, for the most diagonal which is located in the fuselage with the power plant. In the adjoining bearing surface between a fixed wing. The aircraft has a V-shaped vertical tail surfaces. This unmanned aircraft is equipped with a complex of equipment for monitoring air space, data acquisition, and data communication on the ground. A disadvantage of this scheme is the large sweep of the front and rear bearing surface is on of the motor, reduces the reliability of the aircraft.

Also known aircraft, containing two fuselage, connected with each other three bearing surfaces. The nasal part of the aircraft is connected canard. In the middle part of the fuselage are connected by a center section of the wing. Before the center section is additional bearing surface. Moreover, the canards, additional bearing surface of the wing and spaced above construction the horizontal direction of the aircraft. The vertical tail is made of two keels that are installed on the tail beams fuselage. The power plant consists of two engines, located on the center section of the wing. Specified aircraft described in the patent of the Russian Federation 2104226, CL 64 With 39/04, publ. 10.02.1998. The disadvantages of this aircraft is to install keels on the tail made the beams, which increases the weight of the structure, and also affects the flutter characteristics of the aircraft.

Closest to the proposed aircraft is an aircraft developed by Boeing (see Technical information TSAGI 24 for 1990). The specified drone you the th surface - at the tail end. The power plant consists of two engines, installed in the tail part of the fuselage for the second bearing surface. At the ends of the second bearing surface limit the aerodynamic surface. The described aircraft has radar with phased array. Perform aircraft dvojpodlazny and the location of the power plant with the clamping screws in the rear of the fuselage improves the radar and provides an overview 240o. The disadvantage of this scheme is that it does not provide circular scan radar, resulting radar can not work effectively enough, takeoff and landing characteristics are degraded, because the angle of attack is limited to small values due to the removal of the tail parts of the fuselage with the engine behind the rear edge of the second bearing surface.

The proposed group of inventions aimed at creating BLAH, having high performance characteristics that satisfy the requirements for the height and duration of the flight. In addition, the aircraft must be piloted remotely and perform a flight under a given program, to carry on Board the complex of the target equipment (block perceiving the space in any weather.

Also variants of the invention (unmanned aerial vehicle) is aimed at creating BLAH, providing all-round view in azimuth for the efficient operation of the target hardware.

In the first embodiment perform the specified technical result is achieved in that the unmanned aerial vehicle contains two fuselage, connected in the rear part of the wing, and the forward part of the front horizontal tail, vertical tail, the engines and chassis. The fuselage at the tail end are interconnected by a center section of the wing and does not extend beyond the rear edge of the wing. The canards are made with low aspect ratio.

The vertical tail is made of two keels that are installed at an angle to the plane of symmetry of the aircraft on the center section of the wing. Kili is installed on the center section of the wing when viewed from the front oblique to each other.

The unmanned aerial vehicle may have a fairing, coupled with Kili. The ratio of maximum transverse size of the fairing to its length is in the range from 0.18 to 0.35.

In one of the modifications of the power plant is located on the center section of the wing between the fins.

The wing is made t eat mechanization rear edge. The canards also has mechanization.

The contour of the cross section of the fuselage is made in the form of a convex polygon. The chassis of the aircraft made four legged. On each fuselage mounted on two supports of the chassis. The front supports are made wheels and the rear ski.

According to the second embodiment technical result is achieved in that the unmanned aerial vehicle contains two fuselage, connected in the rear part of the wing, and the forward part of the front horizontal tail, vertical tail, consisting of two keels, power unit and chassis. The fuselage are connected in the rear part of the wing centre-section. Vertical tail mounted on the wing centre-section and is made of two inclined towards each other keels connected to the fairing. One keel or both of the keel is installed on the center section of the wing hinge can be rotated about an axis parallel to the axis of symmetry of the aircraft. One of the fins connected to the fairing with the possibility of the connector. The canards has a small elongation. The power plant is located on the center section of the wing between the fins.

The wing is installed on ipodnano trapezoid with high aspect ratio, and the wing is set with a positive angle transverse V. Wing has mechanization, located on the rear edge of the wing. Also, the canards are equipped with mechanization.

The ratio of maximum transverse size of the fairing to its length is in the range from 0.18 to 0.35.

The fuselage cross-section is made in the form of a convex polygon.

The chassis of the aircraft made four legged. On each fuselage mounted on two supports of the chassis. The front landing gear wheel made wheel and the rear ski.

Distinctive features of the proposed group of inventions is more detailed in the following description in conjunction with the accompanying drawings.

In the drawings shown: in Fig.1 is a top view of an unmanned aerial vehicle (1st option); Fig. 2 is a front view of the proposed aircraft (1st option); Fig.3 is the side view of the aircraft (1st option); Fig.4 is a top view of one of the possible modifications of the aircraft of Fig.5 is a top view of an unmanned aerial vehicle (2nd option); Fig.6 is a front view on an aircraft (2nd option); Fig.7 is the side view of the aircraft (2nd option); Fig.8 - MHA of barrierefreie at high altitudes. The aircraft used in the ground control center, communications and information processing.

The unmanned aerial vehicle according to the first embodiment (see Fig. 1, 2) has two fuselage 1. The fuselage 1 is connected between the two bearing surfaces 2 and 3 so that when viewed from above, forms a frame structure in the form of a rectangle.

One of the supporting surfaces 2 is located in the tail section of the aircraft, according to its function, it is a wing.

The other bearing surface 3 is located in front of the aircraft and connects the nose part of the fuselage 1. In their function front bearing surface 3 is a canard.

It should be noted that the fuselage 1, if the pages does not extend beyond the rear edge of the wing 2, located in the tail section of the aircraft.

The described arrangement is a variation of the aerodynamic canard configuration and reduces loss longitudinal balance, improving aerodynamic qualities of the airplane.

The use of front horizontal tail (GIP) 3 increases the stiffness and reduces the loads acting on the fuselage 1.

Constructively longitudinal vertical wall. Compartments 4 are avionics, elements of electrical systems and air cooling. In the outer compartments 5 are antenna radar. Inner compartment 4 of each fuselage 1 has nodes for connection with a canard 3, niches for the placement of the landing gear and fuel tanks. The fuselage 1 may be of various shapes in cross section. The shape of the cross-sections of the fuselage is selected from the conditions for effective work to be installed on the plane of the target hardware. The cross-sectional shape can be made in the form, resembling the shape of a circle, oval, triangle, quadrilateral, right or wrong convex polyhedron. When performing cross sections of the fuselage 1 in the form of a polyhedron its corners rounded, and the edges represent the circular arc of large radius. In the above illustrations the shape of the fuselage 1 in cross sections made in the form of a polygon, resembling a triangle.

Wing 2 (see Fig.1) is located in the tail section of the aircraft and is made of three interconnected operational-technological connectors parts: the centre-section 6 and two arms 7 which m of the center section 6. While the tail part of the fuselage 1 do not extend to the outer contour of the center section 6. Also in the front part of the fuselage 1 does not extend beyond the front edge of the GIP 3, i.e., the location of the fuselage 1, Central wing 6 wing 2 and GIP 3 when viewed from above (see Fig.1) forms a closed contour is a rectangle, which provides all-round visibility for the target equipment (radar), and in addition, a closed form in terms of increases rigidity while reducing its weight.

The connection of the fuselage 1 between the center wing 6 wing 2 allows to partially unload the wing 2 from bending moment acting on it in flight, and, accordingly, to reduce the weight of the wing.

Depending on the modifications of the described layout of the aircraft on the center wing 6 wing 2 can be located nodes mounting the vertical fin 8 (see Fig.4) and the power plant 9. (Graphics, which illustrate the first embodiment (Fig.1-3) shows the layout of the aircraft with the placement of the center wing of the power plant 9. ) Wing 2 is trapezoidal and has a large elongation, which also increases the aerodynamic performance of the aircraft. Console 7 wing 2 is installed in respect of which such controls and mechanization of the wing - the elevators 10, the flaps 11, the ailerons 12. The ailerons 12 can be made drooped working in flight as flaps, as well as fissile, i.e., perform the function of air brakes. The elevators 10 and the flaps 11 may be combined into a single surface. For ease of transport aircraft console 7 wing 2 is made detachable. Terminals are approximately half the magnitude of each console 7.

The canards 3 has a small elongation of the order of 2-3, which increases the safety of aircraft in flight, because when flying at high angles of attack does not occur stall. The relative thickness of the profile is 17-20% that improve the aerodynamic performance. On GIP 3 is aerodynamic body control - rudder 13, which may be made of one or more partitions.

In the layout (see Fig.1, 2) vertical tail 8 consists of two keels that are installed in the tail section of the aircraft to the fuselage 1. However, this arrangement does not restrict the scope of the claims. Vertical tail 8 may consist of a single fin, but it should be noted that the installation of two fins instead of one suitable p is s parallel to the axis of symmetry of the aircraft. The front and rear edges of the vertical fin 8 are swept. In addition, the location of the vertical fin 8 and the power plant 9 within the rear edge of the wing can increase the angle of attack during landing. The fins 8 are installed rudders 15 (Fig.3).

The fins 8 can also be installed on the center wing 6 wing 2 at an angle to the plane of symmetry of the aircraft. Modification of an unmanned aerial vehicle with this arrangement, the vertical fin is described below.

In case of installation of the fins 8 at an angle to the plane of symmetry of the aircraft, for example, when viewed from the front towards each other, they can be interconnected by a fairing 14 (graphic materials explaining the first variant of the invention, this arrangement is not shown, but it is similar to the layout in Fig.5). In this case, when viewed from the front fins 8 in conjunction with the center wing 6 wing 2 form a closed circuit in the form of a triangle. The location of the fins 8 are inclined to each other and connecting them through the fairing 14 increases the rigidity of the vertical fin. The Radome 14 depending on the type of planned works installed equipment for research. The ratio on the s as the center wing 6 wing 2, and in another place, for example on consoles 7 wing 2 on the side of the fuselage 1. Power unit 9 includes a nacelle and installed with the latest engines. Depending on the type of the assumed tasks the number of engines may be different. Preferred option is to build an aircraft with two engines. The aircraft can be fitted with various types of engines - turbofan, turboprop, piston turbo. Power unit 9 (see Fig.2) is located on the pylon 16 mounted on the center section 6. This arrangement of the power unit 9 provides the minimum unwrapping the moment when the failure of one engine, because the engine is installed as close as possible to the axis of symmetry of the aircraft, which also allows to reduce the area of the vertical fin and its weight. In addition, when the use of aircraft for air traffic control power unit 9 when the described arrangement does not obscure the review radar.

The aircraft is equipped with four legged chassis (see Fig.3). Two supports 17 of the chassis is installed in the nasal parts of the fuselage 1 and the completed wheel. The other two bearings 18 are located in the rear part of the summer retreat in niches, made in the internal compartment of the fuselage of the aircraft.

The above variant of the aircraft, as indicated earlier, can be modified. Layout modification shown in Fig.4. In this arrangement, the aircraft contains two fuselage 1, interconnected by two bearing surfaces 2 (wing) and 3 (canard) in such a way that when viewed from above, forms a frame structure in the form of a rectangle.

Wing 2 is located in the tail section of the aircraft, and the canards 3 connects the nose part of the fuselage 1.

In this modification of the wing 2 in relation to the fuselage 1 may be positioned so that the tail part of the fuselage 1 is not beyond the rear edge of the wing 2. The forward part of the aircraft fuselage 1 also does not extend beyond the front edge of the GIP 3.

Wing 2 (see Fig.4) is made of three interconnected operational-technological connectors parts: the centre-section 6 and two arms 7. The center wing 6 wing 2 connects the tail part of the fuselage 1. The location of the fuselage 1, Central wing 6 wing 2 and GIP 3 when viewed from above (see Fig.4) forms a closed contour is a rectangle that both sporogony nodes mounting the vertical fin 8 and the power plant 9.

Wing 2 is trapezoidal and has a large elongation. Console 7 wing 2 are set in relation to the plane of symmetry of the aircraft with a positive angle transverse V On consoles 7 are aerodynamic controls and mechanization of the wing - the elevators 10, the flaps 11, the ailerons 12. For ease of transport aircraft console 7 wing 2 is made detachable. Terminals are approximately half the magnitude of each console 7.

Vertical tail 8 (see Fig.4) consists of two keels that are installed on the center wing 6 wing 2 in the area of the connecting nodes with the fuselage 1. The fins 8 are installed to the plane of symmetry of the aircraft at an angle. As shown in the drawing, the fins 8 are tilted at the sight in front of each other about the plane of symmetry of the aircraft. The front and rear edges of the vertical fin 8 are swept. The fins 8 are installed rudders 15 (Fig.4). The latter can be used as organs of longitudinal control. For example, direct control of the lifting force is carried out with the simultaneous deviation of the surface height of the wing 2 and GIP 3. In this case, the use of rudders 15 vertical OPE 8 may be interconnected by a fairing 14 (in the illustration, explaining a modification of the first variant of the proposed invention, this arrangement is not shown, but it is similar to the layout of the second variant of the invention according to Fig.5). In this case, when viewed from the front fins 8 in conjunction with the center wing 6 wing 2 form a closed circuit in the form of a triangle. The Radome 14 depending on the type of planned works installed equipment for research. The ratio of the diameter of the fairing 14 and its length is in the range from 0.18 to 0.35.

On the center wing 6 wing 2 are the attachment points of the power unit 9. Power unit 9 includes a nacelle and installed with the latest engines. Preferred option is to build a power plant with two engines. The power unit 9 is located on the pylon mounted on the center section 6 between the fins 8. This arrangement of the power unit 9 provides the minimum unwrapping the moment when the failure of one engine, and also reduces the area of the vertical fin and its weight. When using the aircraft for air traffic control power unit 9 when the described arrangement does not obscure the review radar.

The second option proposed unmanned l is Rostami 2 and 3 thus, when the top view is formed frame construction in the form of a rectangle.

Structurally, each fuselage 1 consists of two longitudinal compartments - inner 4 and outer 5, is divided by a longitudinal vertical wall. Compartments 4 are avionics, elements of electrical systems and air cooling. In the outer compartments 5 are antenna radar. Inner compartment 4 of each fuselage 1 has niches for the placement of the landing gear and fuel tanks. The fuselage 1 may be of various shapes in cross section. The shape of the cross-sections of the fuselage is selected from the conditions for effective work to be installed on the plane of the target hardware. The cross-sectional shape can be made in the form, resembling the shape of a circle, oval, triangle, quadrilateral, right or wrong convex polyhedron. When performing cross sections of the fuselage 1 in the form of a polyhedron its corners rounded, and the edges represent the circular arc of large radius. In the above illustrations the shape of the fuselage 1 in cross sections made in the form of a polygon, resembling a triangle.

One of the supporting surfaces a part of the aircraft and connects the nose part of the fuselage 1. To connect with her inner compartments 4 of the fuselage 1 is provided by the nodes of the dock. In their function front bearing surface 3 is a canard.

This arrangement is a variation of the aerodynamic canard configuration and reduces loss longitudinal balance, improving aerodynamic qualities of the airplane.

The use of front horizontal tail (GIP) 3 increases the stiffness and reduces the loads acting on the fuselage 1.

Bearing surface 2 (see Fig.5) is located in the tail section of the aircraft and is made of three interconnected operational-technological connectors parts: the centre-section 6 and two arms 7. The function of the caudal bearing surface 2 is the wing. The center wing 6 wing 2 connects the tail part of the fuselage 1. Knots for joining fuselage 1 are arranged on the ends of the center section 6. While the tail part of the fuselage 1 do not extend to the outer contour of the center section 6. Also in the front part of the fuselage 1 does not extend beyond the front edge of the GIP 3, i.e., the location of the fuselage 1, Central wing 6 wing 2 and GIP 3 when viewed from above (see Fig.5) forms a closed contour is a rectangle, which ensure the plan increases the rigidity of the structure, while allowing to reduce its weight.

On the centre-section 6 are also the sites of attachment of the vertical fin 8 and the power plant 9. The connection of the fuselage 1 between the center wing 6 wing 2 allows to partially unload the wing 2 from bending moment acting on it in flight, and, accordingly, to reduce the weight of the wing.

Wing 2 is trapezoidal and has a large elongation, which also increases the aerodynamic performance of the aircraft. Console 7 wing 2 are set in relation to the plane of symmetry of the aircraft with a positive angle transverse V On consoles 7 are aerodynamic controls and mechanization of the wing - the elevators 10, the flaps 11, the ailerons 12. The ailerons 12 can be made drooped working in flight as flaps, as well as fissile, i.e., perform the function of air brakes. The elevators 10 and the flaps 11 may be combined into a single surface. For ease of transport aircraft console 7 wing 2 is made detachable. Terminals are approximately half the magnitude of each console 7.

The canards 3 has a small elongation of the order of 2-3, which increases the safety of the flying apparatis is 17-20%, that improve the aerodynamic performance. On GIP 3 is aerodynamic body control - rudder 13, which may be made of one or more partitions.

Vertical tail 8 (see Fig.5, 6) consists of two keels that are installed on the center wing 6 wing 2 in the area of the connecting nodes with the fuselage 1. The fins 8 are tilted to each other about the plane of symmetry of the aircraft and connected. Thus, when viewed from the front fins 8 in conjunction with the center wing 6 wing 2 form a closed circuit in the form of a triangle. At the junction of the fins 8 to each other can be mounted fairing 14 (Fig.6, 7). The front and rear edges of the vertical fin 8 are swept. Installation of two keels 8 instead of one suitable for weight characteristics. The location of the fins 8 are inclined to each other and connecting them through the fairing 14 increases the rigidity of the vertical fin. In addition, the location of the vertical fin 8 and the power plant 9 on the center wing 6 wing 2 within its rear edge allows you to increase the angle of attack during landing.

One keel 8 or both of the fin can be mounted on the center section 6 of the hinge, so that when ground handling one of them Il is reported in Fig.8.) The fins 8 are installed rudders 15 (Fig. 7). The latter can be used as organs of longitudinal control. For example, direct control of the lifting force is carried out with the simultaneous deviation of the surface height of the wing 2 and GIP 3. In this case, the use of rudders 15 vertical plane 8 will make it easier, with less effort to implement a longitudinal balance of the aircraft.

Fairing 14 (Fig.7, 8) with a single fin 8 is connected rigidly and the other using connectors, allowing routine maintenance to disconnect one of the keel and rotate it without wasting much time. The Radome 14 depending on the type of planned works installed equipment for research. The ratio of the diameter of the fairing 14 and its length is in the range from 0.18 to 0.35.

As mentioned, the center wing 6 wing 2 are the attachment points of the power unit 9. Power unit 9 includes a nacelle and installed with the latest engines. Depending on the type of the proposed tasks, the number of engines may be different. Preferred option is to build an aircraft with two engines. The aircraft can be fitted with various types of engines - turbojet 16, mounted on the center section 6 between the fins 8. This arrangement of the power unit 9 provides the minimum unwrapping the moment when the failure of one engine, because the engine is installed as close as possible to the axis of symmetry of the aircraft, which also allows to reduce the area of the vertical fin and its weight. In addition, when the use of aircraft for air traffic control power unit 9 when the described arrangement does not obscure the review radar.

The aircraft is equipped with four legged chassis (see Fig.7). Two supports 17 chassis installed with the nasal parts of the fuselage and made wheel. The other two bearings 18 are located in the tail section of the aircraft on each fuselage and made ski. Landing gear to reduce drag in flight are cleaned in a niche made in the internal compartment of the fuselage of the aircraft.

The internal compartments of the aircraft and in the first embodiment and the second embodiment are used to accommodate different flight and target hardware.

For any of the proposed aircraft target hardware typically includes any passive receiving device such as the device, such as radio equipment, radar station, radar side-view and so on,

The composition of the flight equipment also includes navigation equipment, on-Board computer, flight management system, the equipment for receiving and transmitting information intended for broadcast data received perceiving device in real time, and to receive control commands, Registrar information, on-Board power supply, air cooling system, anti-icing system.

Compartments of aircraft, which is equipped with electronic equipment, made of a radiotransparent material.

The following is an example of the application of the aircraft, executed in the first embodiment of the layout. The use of the aircraft, made on the second version of the composition, and its mission is carried out like the first option.

Flight is as follows.

On the ground before you start carrying out necessary maintenance: checks and refueling aircraft systems, enter the necessary data into on-Board computer, ready to work avionics.

Totally what I set on the trolley starting device, then the engines are displayed in the maximum mode. (A takeoff and landing can be rejected not only the flaps, but all the controls that are installed on the wing - elevators, flaps and ailerons. Further with the launch of the device, the plane accelerated to takeoff speed, he comes down from the rack and begins to climb.

During launch and flight of 17 hours, 18 chassis for drag reduction tucked away in the niches of the fuselage 1. Control of aircraft is carried out according to the program incorporated into on-Board computer before you start. If intervention is required in the flight program management can be performed remotely with the command post control. The control signals are received in electronic vehicle management system, which converts them into commands to the actuators of an aerodynamic control surface, height 10, 13, direction 15, the flaps 11, ailerons 12.

Balancing and management in the longitudinal channel are carried out simultaneously by the elevators 10, mounted on the center wing 6 wing 2, and elevators 13 located on the front of the bearing surface 3. These elevators are also used for direct control of the lifting force.

Ground condition the outer wings 2, and for the second variant of the aircraft and alsothe imagery of the vertical fin 8.

Management in the side channel is the rudder 15 (for the second version of the aircraft with rudders 15) located on the vertical tail 8 and fissile ailerons 12, located at the ends of the cantilevers 7 wing 2.

As controls in the transverse channel, use the ailerons 12. The required characteristics of the dynamics of the device are provided with automatic control system.

After takeoff the aircraft flying in the area of the job, at which it starts to work the target hardware. In the area of job the plane flies along a certain path-dependent tasks. For example, in aerial photography trajectory is located above the interests of the locality. The nature of the information collected is installed on the aircraft equipment, is determined by the airborne complex of the target hardware and scope of a particular aircraft.

At the end of the calculated time of flight of the aircraft produces a decrease to home, and then landing. Landing assests plane at height, allow them to roll wheels or skis aircrafts. Rope through a pulley system attached to the two platforms on a truck chassis. When boarding the plane crosses strung rope passing through them wheels and skis chassis, and caught one of the cables released in advance by the SJC, located behind the center of gravity of the aircraft. The cable transmits the force to the platforms that are moving on the ground, slow down the plane. The whole process of planting is in automatic mode. If necessary, it is possible to switch to manual control with the remote on the ground.

After planting is required post-flight maintenance of the aircraft.

The use of any option described aircraft allows multispectral monitoring of the airspace, land and water surfaces in real time.

Both the layout of the aircraft is compact, economical to operate and maintain, more secure in flight, and have high performance characteristics. To deploy the system does not require a large area, the aircraft mobile deployment.

The described implementation of the invention is a private figure. There are each the Asti equipment.


Claims

1. Unmanned aerial vehicle containing two fuselage, connected in the rear part of the wing, and in the bow - front horizontal tail, vertical tail, the engines and chassis, characterized in that the fuselage at the tail end are interconnected by a center section of the wing and the fuselage does not extend beyond the rear edge of the wing, and the canards are made with low aspect ratio.

2. Unmanned aerial vehicle under item 1, characterized in that the vertical tail is made of two keels that are installed at an angle to the plane of symmetry of the aircraft on the center section of the wing.

3. Unmanned aerial vehicle under item 2, characterized in that the fins are installed on the center section of the wing when viewed from the front oblique to each other.

4. Unmanned aerial vehicle under item 3, characterized in that it is equipped with fairing connected to the fins.

5. Unmanned aerial vehicle under item 4, characterized in that the ratio of maximum transverse size of the fairing to its length is in the range of 0.18 - 0.35 in.

6. The unmanned aerial vehicle according to any one of paragraphs. 2-5, characterized in that the propulsion unit of resuscita fact, that the wing is made of a trapezoid with high aspect ratio, and wing set with a positive angle transverse V.

8. The unmanned aerial vehicle according to any one of paragraphs. 1-7, characterized in that the wing is equipped with mechanization.

9. The unmanned aerial vehicle according to any one of paragraphs. 1-8, characterized in that the canards are equipped with mechanization.

10. The unmanned aerial vehicle according to any one of paragraphs. 1-9, characterized in that the contour of the cross section of the fuselage is made in the form of a convex polygon.

11. The unmanned aerial vehicle according to any one of paragraphs. 1-10, characterized in that the chassis is made four legged.

12. The unmanned aerial vehicle according to p. 11, characterized in that the front landing gear wheel made wheel and the rear ski.

13. Unmanned aerial vehicle containing two fuselage, connected in the rear part of the wing, and in the bow - front horizontal tail, vertical tail, consisting of two keels, power unit and chassis, characterized in that the fuselage are connected in the rear part of the wing centre-section, which is inclined to each other is set Keeley, United with the fairing, and tallelei the axis of symmetry of the aircraft, and one fin connected to the fairing with the possibility of the connector, the canards are made with low aspect ratio.

14. Unmanned aerial vehicle under item 13, wherein the power plant is located on the center section of the wing between the fins.

15. Unmanned aerial vehicle under item 13 or 14, characterized in that the wing is set relative to the fuselage so that the tail part of the fuselage does not extend beyond the rear edge of the wing.

16. The unmanned aerial vehicle according to any one of paragraphs. 13-15, characterized in that the wing is made of a trapezoid with high aspect ratio, and wing set with a positive angle transverse V.

17. The unmanned aerial vehicle according to any one of paragraphs. 13-16, characterized in that the wing is equipped with mechanization.

18. The unmanned aerial vehicle according to any one of paragraphs. 13-17, characterized in that the canards are equipped with mechanization.

19. The unmanned aerial vehicle according to any one of paragraphs. 13-18, characterized in that the ratio of maximum transverse size of the fairing to its length is in the range of 0.18 - 0.35 in.

20. The unmanned aerial vehicle according to any one of paragraphs. 13-19, characterized in that the contour of the cross-section of fusel trichosis fact, what chassis is made four legged.

22. The unmanned aerial vehicle according to p. 21, characterized in that the front landing gear wheel made wheel and the rear ski.

 

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The invention relates to an aircraft, in particular for aircraft having multiple fuselages

The invention relates to aircraft, in particular to ultra long-haul aircraft for non-stop round-the-world flight without refueling in the air

The plane // 2087384
The invention relates to aircraft and can be used in lightweight single-engine multirole aircraft

The invention relates to aviation, in particular for aircraft, namely the aircraft for the carriage of passengers on airlines with a length of up to 1000 - 1500 km, where the passenger traffic is constantly increasing

The invention relates to aviation, and in particular to the field of aircraft construction, and is intended to improve the characteristics of the longitudinal stability and controllability of the aircraft at high angles of attack

The invention relates to marine aircraft and for creation of rescue aircraft with vertical take-offs and landings

Flying saucer // 2175627
The invention relates to the field of aviation

The invention relates to aviation

Assault suit // 2166897
The invention relates to clothing designed to protect against, as well as aircraft heavier than air

The plane (options) // 2148534
The invention relates to aviation and can be used to create a passenger cargo and Combi aircraft, the fuselage of the aircraft has a non-circular shape, formed by four segments of circles in the upper, lower and lateral parts, joined in the area of the main compartment

The plane // 2134649
The invention relates to the field of engineering

The invention relates to unmanned aerial vehicles (UAV) vertical takeoff and landing (GDP) and, in particular, to BLAH with toroidal fuselage and a pair of coaxial main rotors rotating in opposite directions in the annular channel formed by the fuselage, and providing the capability of vertical takeoff and landing
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