RU2533779C2 - Simulation-testing system for radar station - Google Patents

Abstract

FIELD: physics, navigation.

SUBSTANCE: invention relates to radar and simulation-testing systems designed to evaluate properties of radar objects. The simulation-testing system for a radar station comprises a target for creating a full-scale environment in a field of view according to a given fly-by program. On-board the target there is a pilot-navigation system, connected to a satellite navigation system, and a measuring electronic device, both connected to a control station. The target is an unmanned aerial vehicle (UAV). The UAV comprises a wing, a tail unit, a fuselage, an engine and landing gear. The launch apparatus comprises a guide which is mounted with a pusher and a removable extensible stator on the side of the engine propeller. A support is mounted on the fuselage in its lower part on a longitudinal axis, said support being in contact with the end surface of the pusher at take-off. The landing gear of the UAV is installed in a compartment, on the wall of which an opening flap, which is connected to an automatic key, is mounted.

EFFECT: simple tests, improved operation and transportation conditions, enabling investigation of different types of radar stations at deployment sites without the necessary equipment.

6 cl, 5 dwg

Description

The invention relates to radar, can be used in simulation test complexes related to research devices, the most reliable for evaluating the characteristics of radar facilities.

A device for assessing the characteristics of a radar station (Radon A.I. et al. Performance evaluation. M.: Radio and communications. 1990. p.3, 25.), containing a target launched into the radar viewing area along the trajectories, a specified test program and a measuring electronic system containing equipment for recording, processing, storage and analysis of research results associated with the control point.

In this device, to ensure the reliability of measurements, a large number of target launches along the same paths are required, which complicates the research process, is an expensive event.

The prototype is a complex (RF patent No. 2400766, G01S 7/40, November 25, 2008), in which targets — airplanes, helicopters, rockets or satellites — are used to create a full-scale environment in the radar field of view according to a given overflight program. The complex contains a measuring radio-electronic system and a unit for recording, processing, analyzing and transmitting information to a control point for deciding on the test results.

Using this device, instead of reviewing the entire radar coverage area, only the sector is inspected, i.e. The nth part of it, in which a radar situation is created, which, while ensuring the reliability of the tests, reduces the number of launches of the target, however, when using an airplane, a runway is necessary, expensive launch installations are required for satellites or missiles, and high costs are required to maintain the technical resource, fuel, which leads to an increase in cost, complication of the research process, the impossibility of using the complex for testing radars at various places of their dislocation in the absence of and the necessary equipment, which is a disadvantage of the known technical solution.

The objective of the invention is to simplify, reduce the cost of the device, improve operating conditions, transportation, provide the ability to test radars of various types at their locations in the absence of a prepared technical base.

The essence of the invention lies in the fact that the simulation and test complex for radar, containing the goal to create a full-scale environment in the field of view according to a given flight program, in which the flight-navigation system (PNS) connected to the satellite navigation system (SNA), and measuring electronic the device is associated with a control point (PU), differs from the known ones in that in it the purpose for creating a full-scale environment in the field of view according to a given flight program is an unmanned aerial vehicle (UAV) with a wing, the plumage, fuselage, engine and landing gear, equipped with a launcher on which the pusher is mounted and a retractable retractable starter mounted on the side of the engine screw, with an emphasis fixed to the fuselage along its longitudinal axis in contact with the end face of the pusher during takeoff, and the device the landing is installed in the compartment, on the walls of which the opening leaf and the automatic lock are fixed, to which the opening leaf is connected.

The launcher guide mounted on the frame at an angle of 8 to 12 degrees to the horizontal surface is made with a longitudinal through-groove longitudinal along the entire length, formed with the possibility of placing an emphasis in it on the fuselage in contact with the pusher mounted on the lower part of the launcher

The starter is mounted on a rail of a hinged support fixed by loops on the launcher guide.

The pusher comprises a retractable rod placed in the housing with a piston and a shock absorber, in contact with the end surface with an emphasis on the fuselage, the housing being made with a limiter inside and a chamber communicating with the capacity of the compressed air cylinder.

The landing device is formed by parachute laying secured by slings through the eyelet on the platform, attached by means of a spring to the bottom of the compartment, the parachuting laying made in contact with the inner surface of the sash, the lock contains a pin located in the niche of the compartment connected to the solenoid connected to the program control unit, and the flap pivotally mounted on the axis of the wall of the compartment is made from the side of the connection with the bent lock, and an opening for the passage of the pin is formed in this part.

For transportation, the unmanned aerial vehicle and control center contain vehicles with increased cross-country ability, and the launcher is made with wheels and a trailer.

Using the UAV overflights made with emphasis on the fuselage as a target for creating a full-scale environment in the field of view according to a given program, when pressed by the launcher pusher creates an additional power impulse during take-off, eliminates the need to use the runway, complex expensive equipment, which leads to reduce maintenance costs, fuel. The technical result is to simplify and reduce the cost of testing, improve operating conditions and transportation, provide research of various types of radars at the places of deployment in the absence of the necessary equipment.

The invention is presented in the drawings: in Fig. 1 is a functional diagram of the operation of the device, in Fig. 2 is a top view of a UAV, in Fig. 3 is a launcher, in Fig. 4 is a sectional view of a pusher, in Fig. 5 is a view of UAV on the side.

In the proposed complex, the purpose for creating a full-scale environment in the radar 1 viewing area according to a given flyby program is an UAV, on board of which there are installed PNS 2 (GP535-HVS) PNS 2 and radio electronic measuring device 4 connected to PU 5 connected to the satellite navigation system.

The UAV is a glider with wing 6, empennage 7, fuselage 8 and a reciprocating 2-stroke internal combustion engine KA-125 mounted on a protruding frame, which is part of the structure of the fairing of the fuselage 8. The fuel tank is located in the rear of the fuselage 8. Bodies controls are installed on the plumage 7 and wing 6. PNS 2 is fixed in the middle part of the fuselage 8 under the compartment 10, in which the landing device is located. The measuring system 4 is located in the nose of the fuselage. Antennas for radio equipment are installed in the parts of the fuselage 8, made with a radio-transparent coating.

On the fuselage 8 in the lower part along the longitudinal axis, an emphasis 11 is fixed using epoxy adhesive ABRO, which contacts the pusher of the launcher in the starting position of the UAV.

The glider is made of carbon fiber reinforced plastic - a composite material that provides maximum application rate, manufacturability, minimum weight and cost of construction.

The starting metal installation / product E10P000000.000 / is a frame 12 with a rack 14, on which a guide 13 is mounted, inclined at an angle from 8 to 12 degrees to the horizontal surface. The value of the angle of inclination of the guide 13 is optimal for the take-off of the UAV, which is determined empirically.

The guide 13 is made with a longitudinal groove 15, longitudinal along the entire length, in which the stop 11 is placed in the starting position of the UAV and is in contact with the pusher 19.

On the guide 13 on the side from the side of the screw of the engine 9 with the help of loops 16, a support 17 is mounted in the form of a frame, on the rail (not shown in the drawing) of which the starter 18 is installed.

The pusher consists of a rod 19 with a piston 20 and an amortization spring 21 placed in the housing 22, which is made with a stopper 23 and a chamber 24 in communication with the capacity of the compressed air cylinder (not shown in the drawing). The housing 22 is fixed in the lower part of the guide 13 so that the end surface of the rod 19 is contacted with a stop 11 placed in the groove 15 of the guide 13.

The landing device is a parachute laying 25, mounted in the compartment 10 of the middle upper part of the fuselage 8, in contact with the inner surface of the opening sash 26. The parachute laying 25 is secured by slings 27 through the eye 28 to the platform 29, which is attached to the bottom of the compartment 10 using a spring 30. The shutter 26, pivotally mounted on the axis 31 of the wall of the compartment 10, is connected to a lock mounted on the wall opposite to the fastening of the axis 31. The lock consists of a pin 32 installed in the niche of the compartment, which is connected to the solenoid 33, under connected to the software unit PU 5. The shutter 26 is bent from the connection side with the lock, an opening 34 is formed in this part for the passage of the pin 32.

To move the UAV and PU 5, the complex is equipped with cross-country vehicles (not shown in the drawing).

The transport vehicle for the BLL is made with a tool tray for removable fastening of the object. For transportation of the launcher, its frame is made with wheels 35 and a trailer 36.

The control point 5 is a ground, mobile, its equipment is located in the back of a cross-country vehicle. The control panel of the operator, whose workplace is in the car, is equipped with a personal computer. UAV flight and landing control is carried out by the Risk take-off software unit, made on Spartan 3A-ХС3C 700А3A-ХС3С 700 A. microchips. Prestarting control, engine starting 9 and UAV take-off are carried out remotely by an operator’s command transmitted by telephone or to a radio operator VHF Cylinders of compressed air with a hose are in the body of the vehicle PU 5, pumping is performed from the compressor from the complex (not shown in the drawing).

In the proposed complex, tests to assess the radar characteristics are carried out as follows: UAVs, PU 5 and a launcher are transported to the selected site. At the command of the operator, transmitted by telephone, the staff install the UAV on the guide 13, and the emphasis 11 on the fuselage 8 is in the groove 15 of the guide, and the support 17 of the starter 18, pivotally hinged to the side near the engine screw 9, is in a vertical position on the guide 13. the next next command of the operator, the staff move the starter 18 along the rail of the support 17, connecting it mechanically to the motor shaft. After starting the engine 9, the starter 18 is disconnected from operation, it is pushed along the rail of the support 17 to its original position, then the support 17 is turned down to release the guide 13. After warming up the engine 9, the engine is turned on at the command of the operator in the speed increase mode necessary for the UAV to take off. After the appearance on the computer of information about the obtained number of revolutions necessary for takeoff, the operator gives a command to actuate the launcher pusher. The housing 22 through the fitting and the hose is connected to a cylinder of compressed air, upon receipt of which into the chamber 24 the rod 19 moves under pressure. When the rod 19 is pressed against the stop 11 in take-off mode, an additional power impulse is created. At a given height, according to the test program, the engine is switched to cruising mode. In the radar field of view, UAV movement is carried out along the trajectory corresponding to a given flight program.

UAV landing is performed in the automatic mode of the program unit by transmitting a signal to the solenoid 33, when compressed, the pin 32 moves to the niche of the compartment 10, freeing the hole 34. The released leaf 26 begins to open due to the air flow. When the sash is opened, the platform 29, pressed by the spring 30, pushes the parachute stowage 10, under the pressure of which the sash 26 completely opens. After the deployment of the small and main parachutes, the UAV lands at a given site, taking into account wind drift.

After completing the fly-by in a given sector of elevation angles, the data of the actual UAV coordinates and by radar signals are sent to a measuring device 4, in which information is processed, compared and stored, transmitted to control point 5 to make a decision on assessing the characteristics of the object under study.

Simplified design using an unmanned aerial vehicle, ease of operation and transportation make it possible to use the proposed complex for research, providing highly accurate and reliable information when measuring the characteristics of radar equipment.

Claims (6)

1. A simulation and testing complex for a radar station, containing a goal to create a full-scale environment in the field of view according to a predetermined flyby program, on board of which a flight navigation system and a radio electronic measuring device connected to the control center are installed, characterized in that that the goal for creating a full-scale environment in the field of view according to a given flight program is made in the form of an unmanned aerial vehicle with a wing, plumage, fuselage, and two a retractor and landing gear equipped with a launcher, on the guide of which there is a pusher and a retractable retractable starter mounted on the side of the engine screw, and on the fuselage in its lower part along the longitudinal axis there is a stop contact in contact with the end surface of the push rod, and the landing gear is installed in compartment, on the wall of which an opening sash is connected, connected to an automatic lock. 2. The simulation and testing complex according to claim 1, characterized in that the launcher guide mounted on the frame at an angle in the range of 8-12 degrees to the horizontal surface is made with a longitudinal groove longitudinal along the entire length, formed with the possibility of placing a stop in it on the fuselage in contact with the pusher mounted on the bottom of the launcher. 3. The simulation and test complex according to claim 1, characterized in that the starter is mounted on a support rail fixed with loops on the launcher guide. 4. The simulation and testing complex according to claim 1, characterized in that the pusher is made in the form of a retractable rod with a piston and a spring of depreciation, placed in the housing in contact with the end surface with an emphasis on the fuselage, the housing formed with a limiter inside and a camera in communication with capacity of a cylinder of compressed air. 5. The simulation and testing complex according to claim 1, characterized in that the landing device is formed by parachute laying in contact with the surface of the sash, secured with slings through the eyelet on the platform, attached with a spring to the bottom of the compartment, the lock consisting of a pin compartment located in a niche connected to the solenoid connected to the program control unit, and the shutter pivotally mounted on the axis of the compartment wall is made from the connection side with the bent lock, and an opening for passage is formed in this part denia pin. 6. The simulation and testing complex according to claim 1, characterized in that for transportation the control point and the unmanned aerial vehicle are equipped with off-road vehicles, and the launcher is made with wheels and a trailer.

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