RU2567867C1 - Helicopter-borne radar system - Google Patents

Abstract

FIELD: radio engineering, communication.

SUBSTANCE: helicopter-borne radar system comprises on-board radar as part of an antenna-transceiving device with a phased antenna array, an on-board processor, an on-board operator workstation, an on-board part of a broadband link, which includes an antenna and communication equipment, and an on-board part of a narrow-band link, as well as a ground-based station as part of operator workstations, a ground-based part of the broadband link, which includes a directional antenna mounted on a telescopic mast, and communication equipment, a ground-based part of the narrow-band link, an orientation and topographic precise positioning system, a ground-based processor and a power generator with corresponding links; the system also includes an orientation and navigation system as part of a strapdown inertial reference system integrated into the phased antenna array, a navigation signal receiver and a computer, as well as a life support and maintenance module as part of a habitable module, a second power generator and a maintenance compartment with corresponding links. Furthermore, the software of the on-board processor includes a program for detecting shell bursts, based on characteristics of the Doppler spectrum of signals reflected therefrom; the dimensions of the phased antenna array are larger; the antenna of the on-board part of the broadband link is in the form of four directional antennae mounted on-board the helicopter, and the directional antenna of the ground-based part of the broadband link is the reference reflector of the helicopter-borne radar system.

EFFECT: improved performance.

1 dwg

Description

The present invention relates to the field of radar and can be used in helicopters, airships and other aircraft to detect ground objects.

Known radar station (radar) for a helicopter (patent No. 2256939 G01S 13/04, 13/90, publ. 07/20/2005), operating in the L range of radio waves, designed to detect ground and air objects. In this radar, helicopter blades with linear antenna arrays located in them are used as scanning antennas. Its disadvantage is the large magnitude of the beam pattern (AF) of the scanning antenna array in the elevation plane, which does not allow the selection of ground and air targets, as well as insufficient resolution in azimuth and radial velocity.

Also known is a mobile radar all-round view for a helicopter (patent No. 2289825 G01S 13/90, publ. 04/20/2006), also operating in the L band of radio waves, designed to detect air and surface objects in the sector of 360 degrees. In this radar, the antenna is made in the form of a 6 × 1 m phased array placed under the fuselage of the helicopter and rotating in the azimuth plane at a speed of 6 rpm. The disadvantages of this radar are low accuracy characteristics, resolution and speed of data output, as well as the inability to detect ground low-speed targets.

Closest to the proposed invention in terms of purpose, construction and technical characteristics is the Horizon helicopter radar complex (RLC) (France) [1, 2], which is designed to monitor the war zone on land and at sea.

The complex consists of an airborne radar (radar), ground post (NP), broadband and narrowband communication lines (HLS) and (ULS). The composition of the radar includes a phased antenna array (PAR) measuring 3.5 × 0.5 m, a receiving and transmitting device, an on-board processor (PB), and an operator’s workstation (RMO).

The composition of the NP includes a ground processor (PN), operator workstations (RMO), an orientation and topographic location system (COT), and a power generator (GM).

SLS is located both on the radar as part of a circular antenna mechanically connected to the axis of rotation of the headlamp and on-board communication equipment, and on the NP as part of a directional antenna and ground-based communication equipment, and serves for two-way transmission of radar, navigation and flight information.

ULS is a radio equipment for communication of NP with a helicopter, radar and command.

The radar operates in the X range of radio waves in two modes: as a Doppler radar with selection of moving targets (SDC) and the determination of their coordinates and speed in scanning mode (mechanical and electronic) within 360 degrees. and in the mode of synthesized aperture (SAR) with the determination of the coordinates of stationary and inactive targets.

To orient the radar in space, information is used coming from the flight-navigation complex (PNK) of a helicopter with satellite navigation connection.

The disadvantages of the prototype are:

- low accuracy characteristics due to orientation errors in the space between the helicopter and the headlamp during the movement of the helicopter and rotation of the headlamp;

- low resolution in angular coordinates due to the small size of the headlamp;

- low noise protection of the HLS due to the circular orientation of the onboard antenna of the HLS;

- the inability to adjust artillery fire, because prototype does not detect bursts of shells;

- deterioration of the technical characteristics of the prototype in unstable satellite navigation communications, leading to a disruption in the orientation of the helicopter;

- the inability to quickly eliminate the equipment malfunction, including power generator ground station;

- lack of comfortable living conditions for staff, which complicates the operation of the complex.

The technical result of the invention is to improve the technical and operational characteristics of a helicopter radar.

The specified technical result is achieved due to the fact that in a known helicopter radar containing radar as part of an antenna-transceiver device with a headlamp, on-board processor and operator’s workstation, a ground post (NP) as part of the ground processor, operator’s workstations, orientation and topographic location systems and a power generator, broadband and narrowband communication lines, an additional orientation and navigation system, as well as a life support and maintenance module as part of the living compartment, a second general ora power and maintenance compartment. In addition, the dimensions of the headlamps are increased, a special program for detecting shell ruptures is introduced into the onboard processor software, the antenna of the onboard part of the broadband communication line is made in the form of four directional antennas located on the sides of the front and rear parts of the helicopter fuselage, each of which has a beam pattern width in the azimuthal plane, 100 deg., and the directional antenna of the ground part of the broadband communication line is the reference reflector of the helicopter radar.

The figure shows a structural diagram of the proposed helicopter radar, where indicated:

1 - airborne radar station (radar);

2 - antenna transceiver device (APPU);

3 - on-board processor (PB);

4 - on-board operator workplace (RMOB);

5 - orientation and navigation system (SLE);

6 - broadband communication line, airborne part (ШЛСБ);

7 - narrow-band communication line, airborne part (ULSB);

8 - ground post (NP);

9 - workplaces of ground operators (RMON);

10 - broadband communication line, terrestrial part (SHLSN);

11 - narrow-band communication line, terrestrial part (ULSN);

12 - orientation system and topographic location (COT);

13 - ground processor (PN);

14 - power generator (GM);

15 - module life support and maintenance (MZhTO);

16 - living compartment (coolant);

17 - the second power generator (GM);

18 - maintenance compartment (GTR).

The proposed helicopter radar consists of airborne radar radar 1, ground post NP 8 and the module life support and maintenance of MZhTO 15.

The composition of the radar 1 includes APPU 2, PB 3, RMOB 4, SON 5, SHLSB 6 and ULSB 7, the composition of the NP 8 - RMON 9, ShLSN 10, ULSN 11, SOT 12, PN 13 and GM 14, and the structure of MZhTO 15 - coolant 16, the second GM 17 and GR 18.

In this case, the first input of the PB 3 is connected to the output of the helicopter's PNA, the second input is connected to the output of the СОН 5, the first and second inputs and outputs of the PB 3 are connected respectively to the inputs and outputs of the APPU 2 and RMOB 4, and its third and fourth inputs and outputs, respectively, with the first inputs and outputs of ULSB 7 and ShLSB 6, the second inputs and outputs of which are connected via a radio link respectively to the first inputs and outputs of ULSN 11 and ShLSN 10, the second inputs and outputs of which are connected respectively with the third and second inputs and outputs PN 13, the first input-output of PN 13 is connected to input-output of PMON 9, p rvy input - with the output of the COT 12 and the output is the output of the helicopter RFCs. The first output of the GM 14 is connected to the inputs of the ULSN 11, SHLSN 10, RMON 9, COT 12 and the second input of the PN 13, and its second output is connected to the input of the MZhTO 15. The first and second outputs of the GM 17 are connected respectively to the inputs of the OZh 16 and GTR 18, and its third entrance is with the entrance of NP 8.

For simplicity, the figure does not show communications on synchronization signals and communications on power supply in radar (radar is powered from the primary sources of electric power of the helicopter).

APPU 2 consists of a phased antenna array (PAR) 5.5 × 0.8 m in size, located under the fuselage of the helicopter, transmitter, receiver, rotation drive, providing mechanical rotation of the PAR, and a beam-forming device that provides electronic scanning. In the working position, the headlamp is deployed, and when taking off and landing the helicopter is folded along the axis of the fuselage. The increase in the size of the headlamps compared with the dimensions of the headlamp prototype allows you to increase the resolution of radar in angular coordinates.

СОН 5 includes a strapdown inertial navigation system (SINS) located in the HEADLIGHT, a computer and a navigation receiver of GLONASS / NAVSTAR systems [3, 4] and serves to accurately determine the direction of the HEADLIGHT beam, which improves the accuracy of determining the coordinates of targets and eliminates errors orientation arising between the helicopter and the HEADLIGHT during the movement of the helicopter.

ШЛС (as part of ШЛСБ and ШЛСН) is designed to provide two-way exchange of information between radar 1 and NP 8. Radar, navigation and flight information is transmitted from radar 1 to NP 8. From NP 8 to the radar 1 information is transmitted on the coordinates of the assigned zones of the radar. Antenna SHLSB 6 is four directional antennas located on the sides of the front and rear of the fuselage of the helicopter so that (with a beam width in the azimuthal plane of each antenna 100 deg.), Overlap all directions within 360 deg. In contrast to the prototype, where an onboard circular antenna antenna is used, this allows to increase the noise protection of the anti-aircraft system.

The SHLSN 10 ground antenna is a directional antenna located on a telescopic mast with a height of ~ 8 m and can be installed with the help of electric drives in the direction of the helicopter, the coordinates of which are received from the helicopter's PNA via PB 3 to PN 13 via ULSB 7 and ULSN 11.

COT 12, which contains the navigation equipment of GLONASS / GPS consumers with the goniometer channel [5], serves for orientation and topographic location of the NP 8 and determines the coordinates of the NP 8. Moreover, the SHLSN antenna 10 in the wavelength range of the radar 1 is an ideal reference reflector. The presence of a reference reflector with known coordinates allows you to maintain high accuracy characteristics of the radar in case of disruption in the functioning of CAP 5.

ULS (consisting of ULSB 7 and ULSN 11) is a radio equipment for communication of NP 8 with a helicopter, radar 1 and command and is intended to control the operation of radar 1 using commands sent from RMON 9 and the command post, and receive response receipts, for example commands to turn on, release the antenna, turn on the radiation, set the operating frequency, operating modes and others. In addition, the coordinates of the reference point of NP 8 for transmitting them to PB 3, which in this case is the reference point of the coordinates of the detected targets and is displayed on the RMOB 4 screen, and from the radar 1 receives information about the location of the helicopter which is displayed on the PMON 9 screen.

When operating a helicopter radar, an important role is played by the life support conditions of the personnel and maintenance of the radar. To create these conditions, MZhTO 15 with a living room for comfortable living conditions (recreation and food) of personnel (coolant compartment 16), a technical workshop for repair and maintenance of equipment (compartment for maintenance of OTO 18) and a power source GM 17 , which supplies electricity to MZhTO 15, and also serves as a reserve for power supply to NP 8. MZhTO 15, if necessary, receives electricity from GM 14 NP 8.

Radar 1, like the prototype, operates in the X range of radio waves in two modes: as a Doppler radar with the selection of moving targets (SDC) and the determination of their coordinates and speed in the scanning mode of the PAR (mechanical and electronic) within 360 degrees. and in the mode of synthesized aperture (SAR) with the determination of the coordinates of stationary and inactive targets.

When operating in FDC mode, the RLC helicopter complex can detect missile breaks due to the introduction of a special program based on the features of the Doppler spectrum of signals reflected from missile breakdowns in the software 3 of the software. The simultaneous detection of targets for which firing is carried out, and shell explosions allows you to adjust artillery firing.

The radar information obtained during the location of the earth’s surface, taking into account the data from SON 5, undergoes primary processing in PB 3 and is issued to RMOB 4 and NP 8 according to SHLSB 6 and SHLSN 10. At the same time, the ground antenna SHLSN 10 using electric drives in azimuth and angle location is set in the direction of the helicopter, the coordinates of which are constantly transmitted to NP 8 from the helicopter's PNA through PB 3 and PN 13 via ULS, and radar and other information is transmitted to NP 8 and received from NP 8 via HLS of one of the four ShLSB 6 antennas, turned into side NP 8 regardless of helicopter orientation. The radar information received by NP 8 via the HLS passes through secondary processing in PN 13 and is transmitted to RMON 9 and to the output of the entire RLC for use by subscribers and the command.

Thus, the introduction of a well-known helicopter radar, containing radar with APPU, PB, RMOB, NP with RMON, SOT, PN and GM, as well as broadband and narrowband communication lines, in addition SON, SINS which is built into the headlamp, MZhTO as part of the coolant, the second GM and GTR, a new special program for detecting shell ruptures in the onboard processor software, as well as increasing the size of the headlamps, making the onboard SLS antenna in the form of four directional antennas located on the sides of the front and rear parts of the helicopter fuselage, and using the directional ground antenna enny SHLS as the reference reflector eliminates the prior art disadvantages mentioned above and thereby improve the technical-operational characteristics of the helicopter proposed radar system.

Information sources

1. Advertising brochure HORIZON (firms EUROCOPTER and THOMSON-CSF, France), 1998.

2. JANE′S AVIONICS 2001-2002, DATE: 2001 JAN 15, FRANCE, “Horizon battlefield surveillance radar”.

3. Babich O.A. Information processing in navigation systems. M., Engineering, 1991.

4. A device for determining the direction of the beam, coordinates and speed of the radar antenna. RF patent No. 127502, s. No. 2012152239, priority dated December 4, 2012, IPC G08C 19/00.

5. Global satellite radio navigation system “GLONASS” edited by V.N. Kharisova, A.I. Petrova, V.A. Boldina, Moscow, IMPR, 1998.

Claims (1)

Helicopter radar complex (RLC), containing an airborne radar station (RLS) as part of an antenna transceiver device (APPU) with a phased array antenna (PAR), an on-board processor (PB), an on-board operator workstation (RMOB), an onboard part of a broadband communication line (ШЛСБ), which includes the antenna and communication equipment, and the airborne part of the narrow-band communication line (ULSB), as well as the ground post (NP) as part of the operator’s workplaces (RMON), the ground part of the ШЛСБ (ШЛСН), including the directional antenna located on the phone an escopic mast, and communication equipment, the ground part of the ULS (ULSN), the orientation and topographic location system (SOT), the ground processor (PN) and the power generator (GM), while the first input of the PB is connected to the output of the flight-navigation complex (PNK) of the helicopter , the first and second inputs and outputs of the PB are connected respectively with the inputs and outputs of the APPU and RMOB, and the third and fourth, respectively, with the first inputs and outputs of the ULSB and ShLSB, the second inputs and outputs of which are connected by radio channel respectively with the first inputs and outputs of the ULSN and ShLSN second inputs the odes of which are connected respectively to the third and second PN input-outputs, the first PN input-output is connected to the PMON input-output, the first input is to the COT output, and the output is the output of a helicopter radar, in addition, the first GM output is connected to the ULSN inputs, SHLSN, RMON, SOT and the second PN input, characterized in that it includes an orientation and navigation system (SON) as part of a strapdown inertial system (SINS) built into the headlight, computer and navigation signal receiver, as well as a life support and maintenance module (AML) in the composition of the living compartment (ОЖ), the second GM and the maintenance compartment (GR), while the СОН output is connected to the second PB input, the second GM output is connected to the МЖТО input, the first and second outputs of the second ГМ are connected to the ОЖ and ОTO inputs, respectively, and its third output is with the NP input, in addition, a program for detecting missile ruptures based on the features of the Doppler spectrum of the signals reflected from them is introduced into the PB software, the dimensions of the headlamps are increased, the HLSB antenna is made in the form of four directional antennas, located data on the sides of the helicopter, and the SLSN directional antenna is a reference reflector of the helicopter radar.