RU124020U1 - OPTICAL SYSTEM OF HELICOPTER LANDING ON THE SHIP TAKEOFF AND LANDING AREA - Google Patents

Abstract

1. An optical system for landing a helicopter on a ship landing strip, comprising: a glide path indicator mounted on superstructures of a water vessel with a radiating surface toward the helicopter landing approach, consisting of two blocks of glide path indicator lights based on, for example, LEDs that are placed on a two-axis pendulum suspension one above the other with a shift in the horizontal plane by an angle of the order of 10-15 °, and each of the blocks of lights of the glide path indicator is made of at least three light modules x emitters of different colors, for example red, green and yellow, which are located in the vertical plane so that their rays in space in the vertical plane are adjacent to each other, and the optical axis of the Central module of the light emitters has a tilt angle in the vertical plane equal to the tilt angle helicopter landing glide path, for example 4 °, and the glide path indicator has a mechanical lock of the pendulum suspension inoperative, as well as an input for connecting to the power line and an exit for exchange Info; heading indicator mounted on superstructures of the watercraft with a radiating surface toward the helicopter approaching landing, consisting of two blocks of heading indicator lights, which are placed on a two-coordinate pendulum suspension one above the other with a shift in the horizontal plane by the same angle and in the same direction as and blocks of lights of the indicator of the glide path, and each of the blocks of lights of the indicator of the course consists of at least three modules of light emitters of the same color, for example blue, which are located horizontally

Description

The utility model relates to the field of instrumentation, namely to the technique of marine light-signaling devices, and can be used on ships to provide takeoff and landing of a helicopter or other aircraft (LA) with vertical takeoff and landing, on the take-off and landing site in simple and complex meteorological conditions.

It is known that helicopters are successfully used in navigating ships in the Arctic and Antarctica, on fishing, transport and passenger ships, on ships of the navy. To organize flights on such ships and ships, helicopter runways and runway support facilities are equipped. The effectiveness of the use of helicopters significantly depends on the ability to perform approach and landing on runways at night in difficult weather conditions (SMU). The requirement to ensure landing in SMU makes the profession of a marine pilot one of the most dangerous.

One of the ways to improve the safety of helicopter flights in SMU is the use of lighting equipment to provide a visual method for approaching and landing helicopters on ship runways. At different stages of the flight, various means are used, In the work of Yu.A. Tyapchenko, L.V. Garshin. Means and methods for ensuring the visual landing of helicopters on the deck of ships and ships // Applied Psychology as a Resource of the Socio-Economic Development of Russia in the Conditions of the Global Crisis: Proceedings of the 2nd Interregional Scientific and Practical Conference, Moscow, November 11–13, 2010 Book 2 . - M.: MSU Publishing House, 2010. Pages 10-103 presents 5 stages.

The first stage is the stage of reducing the helicopter along a given glide path. At this stage, indicators of the glide path of the IG and the IR course are used. The main characteristics of these indicators are the number of light sectors of radiation and their color, radiation pattern (aperture angles), the range of visibility and reliable recognition of the color of light rays, and the stabilization of the optical axis of the IG or IR. Using these indicators, the pilot displays the helicopter in the line of sight of the watercraft.

The second stage is the stage of balancing the speed and direction of the aircraft with the movement of the ship. The ship must keep its speed and direction constant. The pilot must occupy a vertical position above the runway height. The main indicators at this stage are the indicator of vertical movement of the center of the runway, the indicator of the true horizon, the roll indicator, means of displaying the direction and speed of the wind in the runway area. The main characteristics of these indicators are the range of visibility and confident recognition of the light elements of the indicators, the light radiation pattern. The pilot must be informed about the nature of the air flow in the landing zone, be able to assess the size of the roll and pitching and vertical movement of the center runway, to maintain the helicopter in the horizon. The danger is associated with possible errors in determining the pitching parameters and, accordingly, taking a position relative to the runway. The pilot should be ready to fend off gusts of wind.

The third stage is the stage of “pushing” the helicopter to a position above the center of the runway and leveling it. The main indicators are the indicators of the second stage. The danger increases significantly, as the nature of the air flow changes and the pilot must fend off its change and at the same time do everything so as not to touch the screws of the ship’s superstructure and to avoid the dangerous approach of the tail of the helicopter from the runway, etc.

The fourth stage is the stage of underlining (landing). At this stage, two landing patterns apply:

a) a scheme based on the use of a deck operator as an element for controlling the actions of pilots when landing a helicopter on runways and mechanical means of coupling and pulling the helicopter to the deck;

b) a scheme based on the use of shipborne means of displaying the true horizon (true vertical), airborne, keel and vertical qualities. In this scheme, maintaining the horizontal position of the helicopter, the pilot must ensure that the runway is caught up in the vertical plane and the helicopter landing gear is pressed to the deck. The fourth stage is the most dangerous. At this stage, various kinds of illusions are possible, which can lead to the buildup of the helicopter and its dumping on deck or overboard.

The fifth stage is the helicopter mooring stage. In the manual scheme for the embedment, the main task of the pilot at this stage is to keep the helicopter in a state pressed to the deck. The pilot monitors the position of the deck using lights such as the pitching indicator or deck lighting lights. For helicopters with a coaxial propeller scheme, the sixth stage should be distinguished - the stage of stopping and untwisting of propellers. At this stage, with certain wind parameters, overlap of the propeller blades and their destruction are possible. Stopping the propellers is prohibited if the vertical component of the resulting air flow is higher than the permissible for this type of helicopter. Therefore, information on wind parameters over the runway is important for the pilot.

On ships of different countries, various types of heading and glide path indicators, indicators of the true horizon or vertical are widely used. Original BPPL lighting systems are used, which help pilots navigate the space above the deck of the ship. However, the authors are not aware of examples of combining all means into a single information system for the pilot at all stages of a visual approach and landing on a ship.

The closest in technical essence and the achieved result is an optical system for landing a ship-based helicopter - OSPV (See Optical landing system for a helicopter OSPV-20380. Operation manual NKUG.461523.001 RE. Ramenskoye, CJSC STC Alfa-M, 2006 .) created by CJSC Scientific and Technical Center Alfa-M Ramenskoye, Moscow Region

OSPV contains:

1. IG glide path indicator, which includes a pendulum suspension, on which are placed two blocks of lights of the BOIG glide path indicator, whose optical axes are offset in the horizontal plane by an angle of 10 ° relative to each other

2. IR heading indicator, which includes a pendulum suspension, on which are placed two blocks of lights of the BOIK heading indicator, the optical axes of which are offset in the horizontal plane by an angle of 10 ° relative to each other

3. Remote control

4. The control unit of the optical landing system of the helicopter BU OSPV, which includes:

4.1. Aircraft control unit calculator

4.2. The control unit for the vertical movement indicator BU IVP The uniaxial biofeedback stabilization unit, in which the reciprocating mechanism is located, on the output shaft of which there is a level indicator plate. The swing-out mechanism and the bar of the true horizon pointer form a pointer to the true horizon. 5 Indicator of vertical movement of the runway. 6. Two blocks of light emitters indicating the roll of a watercraft. In the OSPV there are lines for transmitting information about the state of the blocks of lights of the ship, lines for supplying power to the blocks of lights, lines for transmitting information about the status of blocks of lights for heading and glide path indicators, a line for controlling LEDs for blocks of lights for heading and glide path indicators, and power lines.

The main means of providing a landing in this system are lighting devices: a glide path indicator (IG), a heading indicator (IR), a true horizon indicator (UIG), a vertical, displacement indicator (IWP), and blocks of light emitters to indicate the roll of a water vessel. All these devices emit light rays into space, using which the pilot flies to the ship during approach and landing. All lighting devices are controlled using the control panel (PU).

OSPV has two inputs: on-board power is supplied to one of them from the onboard power bus, and data from the navigation system of the ship (NSC), which contain information about the onboard, keel and vertical rolls, is received on the other via the multiplexed information exchange channel (MKIO). From the remote control, power is supplied to all components of the OSPV. Turning the power on and off is done using the toggle switches, which are located on the control panel.

The true horizon indicator (TIG) is the light bar of the true horizon indicator (PUIG), which is mounted on the output shaft of the uniaxial stabilization unit parallel to the plane of the runway. The TIG provides the pilot with information on the position of the horizon line during onboard rolling of the ship in the earth's coordinate system. In this case, the horizon line is indicated by the luminous PUIG.

Blocks of light emitters of an indication of the roll of a water vessel are installed on the superstructure of the vessel in line with the PUIG bar parallel to the horizontal plane of the runway stationary at a certain distance from the ends of the bar. During pitching, the PUIG remains in a horizontal position, and the blocks of light emitters of the roll indication swing in a vertical plane relative to the PUIG, thereby providing the pilot with information about the direction, roll pitch and position of the runway relative to the true horizon. The indicator of vertical movement of the runway is designed to indicate the position of the take-off and landing platform (runway) of the ship in a vertical plane relative to the unperturbed surface of the water, which is displayed using the base unit of lights. The IWP has six upper and six lower blocks of scale lights and an indication of the runway position relative to the unperturbed surface of the water. In each block of lights there are four green elements of light radiation to indicate the current position of the runway and one yellow to indicate the runway scale, which is located to the right of the green light emitter. The blocks of lights, being assembled at the application, form the vertical movement indicator itself, in which green light emitters form a vertical line to indicate the current position of the runway, and yellow - the scale of the indicator of vertical movement of the runway relative to the unperturbed surface of the water.

The glide path indicator (IG) forms in the space behind the stern of the ship yellow (above the glide path), green (on the glide path) and red (below the glide path) three light fluxes adjacent to each other, located in a vertical plane.

The heading indicator (IR) forms in the space behind the stern of the ship three blue light fluxes adjacent to each other in the horizontal plane. The right and left light streams are switched on in a pulsed mode with different frequencies.

After turning on the OSPV, the control unit calculator, which is part of the uniaxial stabilization unit, receives data from the navigation system and converts them into control signals:

- for the electric drive of the uniaxial stabilization unit, on the shaft of which is fixed the bar of the true horizon indicator (PUIG); PUIG turns at an angle equal to the angle of the ship;

- to turn on green light elements in one of the blocks of lights indicating the position of the runway relative to the unperturbed surface of the water ..

The light element is switched on in the light blocks of the IWP using the control unit of the vertical displacement indicator, which generates eleven signals arriving at the IWP. Of these, 7 lines for the targeted selection of one of the light blocks of the IVP and 4 lines for the selection of a light element inside the selected block. In addition, 12 test signals intended for checking the operability of the IVP are fed through the wired communication line from the control panel to the control unit of the IWP. On the other hand, from the IWP to the remote control via a wired communication line the signal “IWF Serviceability” is received, which controls the “IWT Serviceability” signaling device on the remote control.

There are similar connections between the remote control and the control unit for testing the electric drive of the uniaxial stabilization unit. On the control panel in the “BOS Test” mode, 3 signals are generated to turn the PUIG to one of the three angles set from the control panel. At the same time, the calculator of the control unit is disconnected from the electric drive of the biofeedback and data does not enter it.

The control unit calculator transmits a “Serviceability” signal to the console via separate lines.

Signals of serviceability of the PUIG, blocks of light indication of the roll of the ship enter the console through separate communication lines.

Separate communication lines in the IR and IG from the remote control are supplied brightness control signals (three signals for three fixed brightness values). In the opposite direction, from the IR and IG to the remote control the signal “Serviceability” is received.

The disadvantages of this OSPV are:

1. Multi-wire cable system

2. A large number of signaling devices and controls on the control panel do not allow creating an operator workstation with a convenient ergonomic interface. The specified remote control, by its design, fundamentally does not meet the requirements of embedding it in the remote control panel, integrated on the basis of modern information and computer technologies

3. The lack of brightness control of the light emitters in the display units of the roll of the watercraft, in the level indicator of the true horizon and the light blocks of the indicator of vertical movement

4. In the heading and glide path indicators, a manual control circuit for the device for fixing the pendulums in the idle state is used, which does not allow it to be used in real operating conditions, since these indicators are usually located in places difficult for ship crews

5. The indicator of vertical movement is made in the form of separate light blocks that are assembled together in a single indicator directly at the place of its installation on the ship, which increases the complexity of work directly on the ship in difficult weather conditions

6. The formation of the directions of radiation of the light fluxes of the heading and glide path indicators is carried out on a pendulum suspension, which during assembly causes great difficulties

7. In general, the system adopted an irrational layout of the computing device, control units of the vertical displacement indicator, uniaxial stabilization unit of the true horizon indicator, etc.

The technical result of the solution is to increase the safety of helicopter landing by increasing the technical and operational characteristics of the OSPV

The technical result is achieved by the fact that the optical system for landing a helicopter on a ship landing strip, which contains:

a) the glide path indicator installed on superstructures of the watercraft with the radiating surface towards the helicopter landing approach, consisting of two blocks of glide path indicator lights based on, for example, LEDs that are mounted on a two-axis pendulum suspension one above the other with a horizontal shift of an angle of about 10 ° -15 ° hail, and each of the blocks of lights of the glide path indicator is made of at least three modules of light emitters of different colors, for example, red, green and yellow, which are located in the vertical plane so that their rays in space in the vertical plane are adjacent to each other and the optical axis of the central module of the light emitters has an angle of inclination in the vertical plane equal to the angle of inclination of the helicopter landing glide path for example 4 °, and the indicator of the glide path has a mechanical lock of the swingarm inoperative, as well as an input for connecting to a power line and an output for exchanging information;

b) the heading indicator installed on the superstructure of the watercraft with the radiating surface toward the helicopter approaching the landing, consisting of two blocks of heading indicator lights, which are placed on a two-coordinate pendulum suspension one above the other with a shift in the horizontal plane by the same angle and in the same direction , like the lights of the glide path indicator, and each of the lights of the heading indicator consists of at least three modules of light emitters of the same color, for example, blue, which are located in horizontal so that their rays in space in the horizontal plane are adjacent to each other and the optical axis of the central module of light emitters is parallel to the optical axis of the central module of light emitters of the glide path indicator, the heading indicator has a mechanical lock of the pendulum suspension inoperative and an input for connection to the power line and output for the exchange of information;

c) the indicator of the true horizon, which is installed on the superstructure of the ship in the visibility range of the pilot when approaching the watercraft, when the aircraft hangs over the center of the runway and on the landing site of the aircraft on the runway containing a luminous bar about 1.5 in length -2.5 m with a swing center in the middle, in which light emitters such as LEDs are placed, a uniaxial stabilization unit for the position of the bar along the roll in the range of pitch angles of the order of 10 ° -18 °, to the output shaft of which mounted on the luminous strip indicator true horizon, and uniaxial stabilization unit has a first input for connection to a power supply bus and a second connection line to the control unit uniaxial propeller stabilization and strip - a first input for connection to the power bus and an output for information exchange;

d) at least two blocks of light emitters indicating the pitching of the vessel with light characteristics similar to the light characteristics of the light emitters of the true horizon indicator strip, which are usually installed in line with the true horizon indicator strip at a distance from the edges of the strip of at least 0.5 m and having an input for connecting to power buses and an output for exchanging information;

e) an indicator of vertical movement of the center of the helicopter take-off and landing site, containing light emitters to indicate the indicator scale with a zero mark in the middle and light emitters to display the current position of the center of the runway relative to the level of the undisturbed surface of the water and having an input for connecting to the power buses and electrical inputs and outputs for information exchange with the control unit;

f) the control unit of the optical helicopter landing system, which includes a computer that has a multiplexed information exchange channel with the ship navigation system and interacts informatively with the uniaxial stabilization unit of the true horizon indicator, the indicator of the true horizon indicator, light emitting blocks of the ship’s rolling indicator, indicators course and glide path, remote control;

g) a control panel for the operating modes of the optical helicopter landing system having an input for connecting to power buses and electrical communication inputs and outputs with external devices;

h) cable network for connecting all components of the optical helicopter landing system to the power supply buses, control unit and remote control,

characterized in that:

a) the cable network in terms of ensuring the information interaction of all the components of the optical landing system is made on the basis of multiplexed information exchange channels using, for example, an RS-485 interface;

b) the blocks of light emitters of the glide path and course indicators are made in the form of finished blocks with the given angles of relative position of the modules of the light emitters and the tilt angles of the optical axes of the blocks, which are assembled installed on the pendulum suspensions of the glide path indicator and, accordingly, of the course indicator;

c) interface devices are introduced into all the components of the optical helicopter landing system, the inputs of which are connected to the multiplex channels of information exchange of the system’s cable network, and the outputs are connected to the inputs of the components of the optical helicopter landing system;

d) devices for adjusting the brightness of light-emitting elements, the inputs of which are connected to the outputs of the interface information exchange devices, and the outputs to the light emitters of the indicator bar of the true horizon, are introduced into the bar of the indicator of the true horizon, blocks of lights of the indicators of the glide path and course, blocks of light emitters of the indication of the pitching of the water vessel and an indicator of vertical movement, as well as blocks of light emitters indicating the roll of a watercraft and blocks of lights of indicators for heading and glide path;

d) the control panel is made on the basis of a computer panel station (based on an industrial personal computer);

f) the indicator of vertical movement is made in the form of a single monoblock, which includes the information field of the light emitters to display the position of the runway relative to the line of the unperturbed level of the water surface and the information field to display the indicator scale, the inputs of which are connected to the outputs of the devices for adjusting the brightness of light emitters ;

g) an integrated control unit is introduced into the helicopter landing optical system, into which interface devices are integrated, a control unit calculator, the outputs of which are connected to the inputs of the interface devices, as well as to the inputs of the switching and power protection unit, the outputs of which are in turn connected to the composite power lines parts of the helicopter landing optical system;

3) light emitters of three colors are introduced into the blocks of light emitters for indicating the pitching of a watercraft to indicate a heel value of less than 10% of the maximum in green, close to or equal to the maximum in yellow and above the maximum in red.

i) the design of the glide path and course indicators is made taking into account the possibility of their installation directly on the foundation of the ship's superstructure;

j) remotely controlled pendulum clamps are introduced into the design of the glide path and course indicators;

The essence of the technical solution is the use of radial two-wire digital communications, for example RS485, the use of a vertical displacement indicator and blocks of lights of course and glide path indicators as single monoblocks, the introduction of remotely controlled latches in the course and glide path indicators, as well as color coding for the indication of the ship's pitching depending on its magnitude, the use of a control panel based on a computer panel station, the introduction of brightness control of the light elements of the IVP, PUIG, blocks with etovyh emitters watercraft roll display that allows improving ergonomics and performance OSPV.

Comparison of the proposed solution with the known technical solutions shows that it has a new set of essential features that, together with the known features, can successfully achieve the goal.

Figure 1 shows the structural diagram of the proposed optical landing system of the helicopter with the following notation

1. The indicator of the glide path of the IG

2. PC course indicator

3. Pointer of the true horizon of the UIG

3.1. PUIG True Horizon Plank

3.2. Block of uniaxial stabilization of BOS

3.3. Uniaxial stabilization output shaft

4. The block of light emitters indicating the pitching of the watercraft No. 1, referred to in the text as the lights of the bank of the order (OKZ)

5. The block of light emitters indicating the pitching of the watercraft No. 2, referred to in the text as the lights of the bank of the order (OKZ)

6. Indicator of vertical movement of the runway

7. Control unit BU

7.1. Aircraft control unit calculator

7.2. IU device interface

7.3. Block switching and power protection BZPK

8. The control panel

9. Navigation system ship NSC

10. Multiplex communication channels ICIE

11. Power bus

12. Protected power lines for components of an optical helicopter landing system

13. Power management lines of components of an optical helicopter landing system

Figure 2 shows the structural diagram of the glide path indicator with the following notation:

1. The indicator of the glide path of the IG

1.1, 1.2. Blocks of lights of the glide path indicator No. 1, 2

1.1.1, 1.2.1 Modules of light emitters of the first color, for example, yellow.

1.1.2, 1.2.2 Modules of light emitters of the second color, for example, green

1.1.3, 1.2.3 Modules of light emitters of the third color, for example, red

1.1.4. 1.2.4 Control unit and brightness control of light emitters

1.1.5. 1.2.5, 1.4 Interface devices

1.3 pendulum latch.

Figure 3 presents the structural diagram of the indicator of the course with the following notation:

2. IR rate indicator

2.1, 2.2. Blocks of lights of the indicator of the course No. 1, 2

2.1.1, 2.2.1 Modules of blue light emitters operating in a pulsed mode with a frequency f ₁

2.1.2, 2.2.2 Modules of blue light emitters operating in continuous mode 2.1.3, 2.2.3 Modules of blue light emitters operating in pulse mode with a frequency f ₂

2.1.4. 2.2.4 - control unit and adjust the brightness of the light emitters

2.1.5. 2.2.5, 2.4 - interface devices

2.3 - pendulum lock control unit

Figure 4 shows a structural diagram of a block of light emitters display roll of a watercraft with the following notation:

4. The block of light emitters indicating the pitching of the watercraft

4.1, 4.2, 4.3. Light emitters, respectively green, yellow and red

4.4 Control unit and brightness control of light emitters

4.5 Interface devices.

In Fig. 5, the color structure of the information field of the block of light emitters of the pitching indication of a watercraft is staged with the following notation:

4.1, 4.2, 4.3. Light emitters, respectively, green, yellow and red.

In Fig.6 recreated structural diagram of the indicator of vertical movement of the ship's landing strip with the following notation:

6. Vertical movement indicator

6.1. Runway position information field

6.2. TTI scale information field

6.3. Control unit and brightness control of the light elements of the IVP

6.4. Interface device

In Fig.7 fixed color structure of the front panel of the vertical displacement indicator with the following notation:

6. Vertical movement indicator

6.1. Runway position information field

6.1.1 Vertical rows of red color of the light elements of the information field for indicating the position of the IWP

6.1.2. Vertical rows of green color of light elements of the information field of the indication of the position of the IVP

6.2. TTI scale information field

6.2.1. Yellow light elements to form the IVP scale

6.3. Information field indicating undisturbed water level

As shown in figure 1, the composition of the OSPV includes lighting devices: glide path indicators (IG) 1 and course (IR) 2, true horizon indicator (UIG) 3, two blocks of light emitters indicating the pitching of the ship 4, 5, hereinafter referred to as like order roll lights (OKZ) and vertical movement indicator 6.

IR and IG are designed to inform the pilot about the position of the helicopter relative to a given trajectory during approach.

The true horizon indicator, together with the OKZ, is intended to inform the pilot of the direction and magnitude of the side rolling and the pilot to evaluate the helicopter position in the horizontal plane or the position of the helicopter relative to the runway plane.

The vertical position indicator is intended for the pilot to evaluate the size and direction of runway movement in the vertical plane.

All lighting devices are combined into a single information and control system using a cable network based on direct connections via power supply circuits 12 and multiplexed information exchange channels (MKIO) 10 with a control unit 7.

All lighting products have the same structural diagram, some of which are shown in figure 2, 3, 4, 6, which consists of light elements, control units and brightness control of light elements and interface devices. The basis of all control units and brightness control of light elements of lighting devices are programmable microcontrollers and means for interfacing microcontrollers with light elements.

The basis of the control unit 7 is the calculator of the control unit 7.1, which is connected to the ICIE via interface devices. The exchange of information with lighting devices occurs in accordance with the specified protocols of information interaction.

The calculator converts the ship’s pitching information coming from the navigation system 9 into control signals, in accordance with which the light elements 6.1.1 or 6.1.2 (see Fig. 7) of the runway 6.1 position information display field are controlled and the uniaxial unit is controlled stabilization 3.2 of the true horizon indicator 3 shown in figure 1.

The device 7.3, located in the control unit 7, is designed to turn on / off the power supply of lighting products and the uniaxial stabilization unit 3.2.

The control panel 8 is a panel station based on a personal computer, as a rule, with a touch method for issuing commands.

The control panel 8 interacts with the calculator of the control unit 7.1. It has a friendly human-computer interface with appropriate display formats and operation logic. The optical helicopter landing system operates as follows. On-board power supply voltages and signals from NSC 9, which contain information about the angle of heel and trim of the ship, their rate of change, and also the magnitude of its vertical displacement, are received at the OSPS inputs.

The control commands from the remote control 8 via the bidirectional MKIO 10 are transmitted via interface devices 7.2 to the calculator of the control unit 7.1 which controls the operation of the system components. Each component of the OSPV (IVP 6, UIG 3, OKZ 4, 5, IG 1 and IK 2) is associated with a calculator of the control unit 7.1 radial bidirectional MKIO. So, in blocks 6, 3, 4, 5, 1 and 2 from the calculator of the control unit 7.1 control commands for lighting devices included in their composition are received, and in BOS 3.2, on the shaft 3.3 of which PUIG 3.1 is fixed, - the angle of heel of the ship from NSK 9 In addition, the value of the current and forecasted position of the center of the runway, determined by the calculator 7.1, taking into account the location of the center of the runway, is supplied to the runway 6. At the same time, a green bar graph when the runway is moving down and red when the runway is moving up is turned on at the runway 6. When the runway moves down, the top of the chart is the current position of the runway, and the bottom is the calculated predicted lower position of the runway. When the runway moves up, the bottom of the chart is the current position of the runway, and the top is the calculated predicted top position of the runway. The program provides the ability to display only the current position of the runway in the form of movable horizontal rows of red light elements when the runway moves up and green when the runway moves down.

The marking of the scale in the information field 6.2 of the IVP 6 (see Fig. 7) is carried out programmatically in the form of large and small pictures. The marking of the scale depends on the magnitude of the displayed vertical movement of the runway. Accordingly, the error of the indication of vertical displacement also depends on this. Indication of the vertical movement of the center of the runway is relative to the line of LEDs of the information field indicating the unperturbed water level 6.3, shown in Fig.7.

The uniaxial stabilization block 3.2 monitors changes in the roll angle of the ship and turns the bar of the true horizon indicator (PUIG) 3.1 by the corresponding angle, holding it in a horizontal position.

PUIG 3.1 allows the pilot to hold the helicopter in a horizontal position during landing.

In the opposite direction, at the request of the calculator 7.1, blocks 6, 3, 4, 5, 1, and 2 send it health signals, which are then transmitted to the console 8 for presentation to the operator.

All components of the OSPV include interface devices through which they interact with interface devices 7.2 of the control unit 7.

To switch power from the power bus 11 to all components, a power switching and protection unit 7.3 is used. This unit operates under the control of the calculator 7.1, which gives commands to turn the power on and off on line 13. From the outputs of the switching and power protection block 7.3, on lines 12, power is supplied to all OSPV products.

The structure of IG 1 (figure 2) includes two identical actuators - blocks of lights 1.1 and 1.2, rotated relative to each other at an angle of 10 ° -15 ° in the horizontal plane. The optical axes of both blocks are inclined to the horizon by an angle equal to the angle of inclination of the helicopter landing glide path for example 4 °. The presence of two blocks 2.2 allows you to designate two independent glide paths, rotated one relative to the other at an angle of 10 ° -15 ° degrees along the course.

Blocks of lights attached to the pendulum suspension, which stabilizes them when the ship is rocking. Each of the blocks of lights contains interface devices 1.1.5, 1.2.5 for communication with the control unit 7 and three modules of multi-colored LEDs (so the block of lights 1.1 contains modules in yellow 1.1.1, red 1.1.3 and green 1.1.2) . Block 1.1.4 controls the brightness of modules 1.1.1, 1.1.2 and 1.1.3 by commands from the remote 8. In addition, IG 1 includes a pendulum lock 1.3, which receives commands through an interface device 1.4 and converts them into arresting control signals a device that fixes the pendulum suspension when OSPV is not in working condition.

The composition of the heading indicator (figure 3) includes two identical blocks of lights 2.1 and 2.2, rotated relative to each other at an angle of 10 ° -15 ° in the horizontal plane. The optical axes of both blocks are inclined to the horizon by an angle equal to the angle of inclination of the helicopter landing glide path, for example, 4 °. The presence of two blocks allows you to designate two independent courses, rotated one relative to the other at an angle of 10 ° -15 ° along the course.

Blocks of lights attached to the pendulum suspension, which stabilizes them when the ship is rocking. Each of the blocks of lights contains interface devices 2.1.5, 2.2.5 for communication with the control unit 7 and three modules of blue light emitters. Blocks 2.1.4 and 2.2.4 control the brightness of modules 2.1.1, 2.1.2 and 2.1.3 and, respectively, modules 2.2.1, 2.2.2 and 2.2.3 by commands from the remote 8. In addition, IR 2 includes pendulum lock 2.3, which receives commands through the interface device 2.4 and converts them into control signals for the locking device securing the pendulum suspension when the OSPV is not in working condition.

The technical and economic effect of the proposed solution is to increase the safety of helicopter landing by increasing the technical and operational characteristics of the OSPV.

Depending on the size of water vessels, their scope, tactics of using helicopters, the level of equipment of helicopters with means for providing helicopter landing, it is possible to use optical landing systems in a reduced configuration. So, for example, it is possible to use the OSPV without a heading indicator, since this task can be solved using the glide path indicator. If helicopters are used only during the day, then it is possible to use OSPV without an indicator of vertical use, etc. Obviously, OSPV, which should include a true horizon indicator, bank tilt lights, a control panel and a power protection, switching and control unit, can be recommended as a minimum configuration. . At the same time, the structural scheme of the OSPV is changed only by excluding from this scheme the corresponding components and the supply lines and ICIP lines that are suitable for them.

Thus, the described version of the proposed system does not exhaust all their diversity, which can be implemented in accordance with the proposed technical solution formula.

Claims (4)

1. An optical system for landing a helicopter on a ship landing strip, comprising: a glide path indicator mounted on superstructures of a water vessel with a radiating surface toward the helicopter landing approach, consisting of two blocks of glide path indicator lights based on, for example, LEDs that are placed on a two-axis pendulum suspension one above the other with a shift in the horizontal plane by an angle of the order of 10-15 °, and each of the blocks of lights of the glide path indicator is made of at least three light modules x emitters of different colors, for example red, green and yellow, which are located in the vertical plane so that their rays in space in the vertical plane are adjacent to each other, and the optical axis of the Central module of the light emitters has a tilt angle in the vertical plane equal to the tilt angle helicopter landing glide path, for example 4 °, and the glide path indicator has a mechanical lock of the pendulum suspension inoperative, as well as an input for connecting to the power line and an exit for exchange Info; heading indicator mounted on superstructures of the watercraft with a radiating surface toward the helicopter approaching landing, consisting of two blocks of heading indicator lights, which are placed on a two-coordinate pendulum suspension one above the other with a shift in the horizontal plane by the same angle and in the same direction as and blocks of lights of the indicator of the glide path, and each of the blocks of lights of the indicator of the course consists of at least three modules of light emitters of the same color, for example blue, which are located in a horizontal plane speed in such a way that their rays in space in the horizontal plane are adjacent to each other, and the optical axis of the central module of light emitters is parallel to the optical axis of the central module of light emitters of the glide path indicator, and the heading indicator has a mechanical lock of the pendulum suspension inoperative and also an input for connections to the power line and an exit for information exchange, a true horizon indicator, installed on the superstructures of the ship in the visibility range of the pilot when approaching to the bottom of the vessel, when the aircraft hovering over the center of the runway and on the landing site of the aircraft on the runway containing a luminous bar about 1.5-2.5 m long with a center of swing in which light emitters are placed, for example LEDs, a uniaxial stabilization unit for the position of the bar along the roll in the range of pitch angles of the order of 10-18 °, on the output shaft of which a luminous bar of the true horizon indicator is installed, and the uniaxial stabilization unit has a first input for connecting to the power bus, and the second to connect the uniaxial stabilization unit to the control line of the propeller, and the bar - the first input for connecting to the power bus and an output for exchanging information, at least two blocks of light emitters indicating the ship’s pitching with light characteristics similar the light characteristics of the light emitters of the plank of the indicator of the true horizon, which are installed, as a rule, in line with the bar of the indicator of the true horizon at a distance from the edges of the plank at least 0.5 m, and having an input for connecting to power buses and an output for exchanging information, an indicator of vertical movement of the center of the helicopter take-off and landing area, containing light emitters to indicate the indicator scale with a zero mark in the middle and light emitters to display the current position the center of the runway relative to the level of the unperturbed surface of the water and having an input for connecting to power buses and electrical inputs and outputs for information exchange with the unit management; the control unit of the optical helicopter landing system, which includes a computer having a multiplexed information exchange channel with the ship navigation system, and interacts informatively with the uniaxial stabilization unit of the true horizon indicator, the indicator of the true horizon indicator, blocks of light emitters of the onboard rolling indicator of the ship, heading indicators and glide path, remote control; a control panel for operating modes of an optical helicopter landing system having an input for connecting to power buses and electrical communication inputs / outputs with external devices, a cable network for connecting all components of an optical helicopter landing system to power buses, a control unit and a remote control, characterized in that cable network in terms of ensuring information interaction of all the components of the optical landing system is based on multiplexed information exchange channels using By calling, for example, an RS-485 type interface, the blocks of light emitters of the glide path and heading indicators are made in the form of finished blocks with the given angles of relative position of the modules of the light emitters and the tilt angles of the optical axes of the blocks, which are assembled to be installed on the platforms of the pendulum suspensions of the glide path indicator and, accordingly, course indicator; all the components of the optical helicopter landing system have interface devices, the inputs of which are connected to the multiplex channels of the cable system’s information exchange, and the outputs are connected to the inputs of the components of the helicopter optical landing system, the indicator of the true horizon, the lights of the glide path and course indicators, blocks of light emitters of the indication of the side rolling of the watercraft introduced devices for adjusting the brightness of light-emitting elements, the inputs of which are connected to the outputs of the interface of information exchange devices, and the outputs - to the light emitters of the plank of the indicator of the true horizon and the indicator of vertical movement, as well as to the blocks of light emitters of the roll indication of the watercraft and the blocks of lights of the heading and glide path indicators, the control panel is made on the basis of a computer panel station, the indicator of vertical movement is made in the form of a single monoblock, which includes the information field of light emitters to display the position of the runway relative to the line n the e-perturbed level of the water surface and the information field for displaying the indicator scale, the inputs of which are connected to the outputs of the brightness control devices of the light emitters, an integrated control unit with integrated interface devices, a calculator of the control unit, the outputs of which are connected to the inputs of the interface are integrated into the optical helicopter landing system devices, as well as to the inputs of the switching and power protection unit, the outputs of which, in turn, are connected to the power lines of the optical components tion helicopter landing system. 2. The optical helicopter landing system according to claim 1, characterized in that light emitters of three colors are introduced into the light emitter display blocks of the ship’s ship for indicating a roll value of less than 10% of the limit in green, close to or equal to the limit in yellow and above the limit - in red. 3. The optical helicopter landing system according to claim 1, characterized in that the design of the glide path and course indicators is made taking into account the possibility of their installation directly on the foundation of the superstructure of the vessel. 4. The optical helicopter landing system according to claim 1, characterized in that remotely controlled pendulum latches are introduced into the design of the glide path and course indicators.

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