RU2270471C1 - Flight vehicle control complex - Google Patents

Abstract

FIELD: instrument engineering, applicable in light vehicle control systems.

SUBSTANCE: a work station of the payload operator is additionally introduced, it has two multifunctional indicators for display of the digital cartographic, television and optoelectronic information, display for pseudovolumetric presentation of the surrounding visual situation and training information, payload control panel and a flight mission forming unit. Additionally installed at the work station of the operator-pilot is a display for visualization of the flight vehicle control process and a landing area target indication modes, information correction and virtual glide path plotting control panel.

EFFECT: expanded functional capabilities.

4 dwg

Description

The invention relates to the field of aviation and can be used to control take-off, route flight, group flight, return and landing of unmanned aerial vehicles (UAVs), to control the movement of a vehicle when delivering an aircraft to a launch point, to ensure ejection take-off and landing using an aerofinisher , as well as for the preparation of a flight task and operator training in the conditions of UAV flight simulation, moreover, control of leading and interacting aircraft can be carried out by operators when placing the structure on a motor vehicle, or separately from it.

A control system for an unmanned aerial vehicle is known, which comprises control equipment for an aircraft located in its body and consisting of several types of passive sensors (infrared, television cameras, etc.), as well as corresponding equipment. The UAV also has a radio navigation equipment system, a radio-electronic control system, an on-board computer, a switching unit for transmitting data from sensors and receiving real-time input control commands, an antenna for receiving control commands and transmitting UAV flight data to the operator’s console.

The operator’s equipment includes a computer (computer) designed to generate control commands and convert them into control signals, in accordance with a predetermined flight program, which are transmitted to the UAV through the communication equipment through the operator’s antenna.

The control signals transmitted from the operator’s control panel are received by the UAV antenna, from which these signals are transmitted to the UAV communication equipment. The control signal from the receiving antenna enters the demodulator / decoder of the UAV communication unit, where it is processed appropriately and enters the UAV's computer and electronic equipment, which process the control signals and generate commands for UAV control elements to perform maneuvers specified by the operator.

The true UAV course is issued by its navigation equipment. True heading data is encoded into the appropriate signals and transmitted to the operator computer.

The system provides UAV flight control using an electronic card. Operator equipment can be both stationary and mobile.

(see RF Patent No. 2145725, Cl. MKI G 05 D 1/10, 1995) is the closest analogue.

As a result of the analysis of the known system, it should be noted that during its operation the safety of approach and landing of the aircraft on unequipped landing sites is not sufficiently ensured, when remote control is complicated due to the lack of a ground course and glide path system and difficult weather conditions, as well as due to of the fact that in the landing mode the operator arises the need for intensive alternate control of flight parameters and the external environment, not provided rational We give the crew (operators) information for the simultaneous perception of the external space (external environment), parametric and signal information.

There are no means of UAV transportation and mechanization of preparations for launching, pre-flight and after-flight operations, there is no system for preparing a flight task and training tools for operators to control UAVs in the conditions of modeling its flight and use. The management of group interaction of UAVs is also not provided.

The objective of this technical solution is to develop an aircraft control complex, which allows to increase accident-free safety and flight efficiency, expand the capabilities of the aviation complex by effectively managing a UAV group in extreme conditions, as well as creating information and control fields for operators that make it possible to simultaneously see the main flight parameters, external environment and hazardous conditions, and allowing the operator to form adequate control operations during high-precision maneuvering in low-altitude flight over difficult terrain, approach and landing at an unequipped airfield in difficult conditions, provide control of the UAV group interaction, provide operational maneuver with the use of UAVs, by integrating the ground control of the aircraft, means of transporting an unmanned aerial vehicle and mechanization of work on the preparation of launches, pre-flight and after-flight operations, as well as the system for the preparation of a flight mission and aircraft TWO operator training in flight simulation and UAV applications.

The solution to this problem is ensured by the fact that in the aircraft control complex, containing the workplace of the pilot-operator with means for setting flight parameters for automatic control of aircraft, manual remote control bodies of the aircraft, flight and navigation indicators, a computer control system, interface units, communication module complex with aircraft to set the leading and interacting aircraft control signals and receive from their information on the fulfillment of a flight mission to ensure takeoff, group flight of two to three aircraft, return and landing, as well as for operator training, the workplace of the payload operator is included, which contains two multifunction indicators for displaying digital cartographic, television and optical-electronic information , a display for pseudo-volume display of the external visual environment and training information, a payload control panel and a flight task formation unit, and n and the pilot-operator’s pilot workstation additionally has a control panel for target designation, information correction, and virtual glide path construction and a display for visualizing the aircraft control process, while the functioning of the computing control system is ensured by the interaction of the aircraft navigation and flight control dispatch control modules for group flight, the reference trajectory control models, geoinformation database, hazard assessment conditions and the formation of information to prevent collisions with the earth's surface and to remove aircraft from dangerous conditions, the formation of an electronic aeronautical map and a topographic map for driving a vehicle, the formation of a flight and training mission, the construction of a virtual glide path for target designation modes of the landing site, correction of flight information and landing by virtual glide path, the formation of a pseudo-volume image of the external visual environment and the training information module, at the same time the time for the delivery of aircraft to the launch point and their technical operation is ensured by the inclusion of a vehicle in the aircraft control complex, in the cabin of which there is a display for displaying a digital topographic map and a satellite navigation system for determining the location, in the kung a power supply system, a display for displaying the functioning vehicle systems and control panel, in the end part of the kung a manipulator for loading and unloading and cargo, and on the trailer - an ejection device and an aerofinisher, while the main components of the ground part of the complex are electrically connected and structurally combined into a single mechanical externally protected mobile structure with the ability to provide joint and separate work of operators to control leading and interacting aircraft as placing the structure on a motor vehicle, or separately from it.

When conducting patent research, no solutions were found that are identical to the claimed one, and therefore, the claimed invention meets the criterion of "novelty."

We believe that the information set forth in the application materials is sufficient for the practical implementation of the technical solution.

The essence of the invention is illustrated by drawings, in which:

- figure 1 presents a block diagram of a control system for aircraft;

- figure 2 presents the information frame of the flight indicator for the modes of trajectory control of the UAV, target designation, approach and landing;

- figure 3 presents the information frame of the aeronautical chart with the symbols of the leading and two interacting UAVs;

- figure 4 presents the information frame of a system for simulating a television image at the stage of landing.

The aircraft control complex contains the operator-pilot's workstation 1, computer control system 2, interface units 3, communication modules 4 and 5 of the ground control point with aircraft 6 and 7 for assigning control signals 6 and interacting 7 aircraft and receiving control signals from them information about the performance of the flight mission, the workplace of the operator of the payload 8; a motor vehicle 9, a manipulator 10 for loading and unloading goods onto a platform or trailer 13; the ejection device 11 used when launching the aircraft, and the aerofinisher 12 used when landing.

The pilot workstation of the pilot-pilot 1 contains means for setting flight parameters 1 g for automatic control of aircraft, manual remote control units 1A, remote control for targeting, information correction and building virtual glide path 1e, flight indicator 1a, navigation indicator 1c and a display for visualization of the control process of the aircraft 1b, which are connected with the computing control system and communication modules 4 and 5 through the interface blocks 3.

LA 1d manual remote controls include:

- a control knob that generates signals along the pitch and roll channels, and located under the right hand of the operator;

- pedals that generate signals along the yaw channel (course);

- an engine control knob located under the operator’s left hand.

Instead of a two-channel control knob and pedals, a three-stage (three-channel) control knob can be used. Mode 1e control panel contains:

- target mode button;

- a potentiometric or tensometric joystick located on the control handle under the thumb of the right hand, the signals of which provide movement of the aiming mark;

- a button for binding to the landing site (landmark) located on the remote control;

- heading unit for virtual VHS (potentiometric or digital).

Computing control system 2 contains program modules: airborne navigation 2a, reference model of trajectory control 2b, database of geoinformation data 2c, assessment of hazardous conditions and output of aircraft from hazardous conditions 2g, generation of electronic aeronautical and topographic map 2d, formation of flight and training task 2e, construction of a virtual glide path 2zh, the formation of a pseudo-volume display of the external environment 2h and the training information module 2i.

The functioning of the system is ensured by the interaction of the aircraft navigation and flight control dispatching software modules for group flight 2a, the reference model of trajectory control 2b, the database of geoinformation data 2c, the assessment of hazardous conditions and the withdrawal of aircraft from hazardous conditions 2g, the formation of an electronic aeronautical map and topographic map 2d, flight preparation and training task 2e, building a virtual glide path 2zh, correcting flight information and landing on a virtual glide path e, the formation of a pseudo-volume display of the external environment 2h and the training information module 2i.

Managed object 6 and interacting aircraft 7 contain communication modules 6a and 7a with ground control center and on-board equipment, communication modules 6g and 7g with interacting aircraft, a television system and an optical-electronic sighting device 6b and 7b, an automatic control system with on-board sensors and navigation module 6c and 7c.

The workplace of the payload operator 8 and operator training control contains two multifunctional indicators 8a and 8b for displaying digital cartographic, television and optical-electronic information, a display 8b for pseudo-volume display of the external visual environment and training information, a payload control panel 8g and a flight formation unit tasks 8d.

The motor vehicle 9 includes a display for displaying a digital topographic map 9a and a satellite navigation system 9b installed in the cabin, an electric power supply system 9c, a display of the functioning of the vehicle 9g systems and an auxiliary tool control panel 9d located in the kung, a manipulator 10 installed in the end part of the kung , the ejection device 11 and the aerofinisher 12 placed on the trailer 13.

The mnemo frame of the flight information command-leader information displays the flight and navigation flight parameters generated by the aircraft navigation module 2a, information about the position of the virtual glide path, target designation of the landing place and landmark (geo-point), information correction, as well as course and glide path information generated by the virtual glide path module 2zh in landing and landing modes on a low-equipped airfield.

The course and glide path information for landing along the virtual glide path is displayed on the multifunctional indicator 1a.

To form a glide path, the indicator additionally displays an aiming mark, a glide path symbol, a virtual runway (runway) symbol and a current speed vector symbol. The aiming mark is combined by the operator-pilot with the start of the runway, observed with the help of a television or optical-electronic sighting device in the interests of obtaining additional information, which is used in the computer control system to form a virtual glide path. When piloting with a velocity vector aiming at the landing stage, the aiming mark is combined with the start of the landing strip.

The location and form of presentation of information on the indicator provides the most rational conditions for the perception of the extra-cabin environment, parametric and signal information, correction of the parameters of the trajectory movement and the formation of the flight image, in accordance with which the pilot exercises control actions.

The information frame shown in figure 2 contains:

flight horizon - item 14;

the silhouette of the aircraft - pos.15;

the symbol of the "leader" - pos.16;

roll scale - pos.17;

pitch counter - pos. 18;

vertical speed scale - item 19;

overload counter - pos.20;

altimeter - item 21;

speed indicator - item 22;

an indicator of the operation of the steering drives of the automatic control system - pos.23;

wind speed and direction indicator - pos.24;

group of counters of the VOR system - item 25;

flight and navigation device - item 26;

symbol of the operation of the aircraft radio compass system - pos. 27;

the symbol of the runway (runway) - pos. 28;

glide path symbol - pos. 29.

The runway symbol (pos. 28) is formed as a trapezoid, the vertices of which are projections onto the frontal plane of the dimensional points of the selected airport during the target designation or calculated. The width of the aerodrome in the calculation is 45 (40) meters, the length depends on the current configuration of the aircraft. Under the condition that the length of the estimated airfield does not exceed the actual (visually visible), landing is possible.

The glide path symbol (pos. 29) is a line connecting the estimated landing place (the touchdown point of the calculated runway) with the current point of entry into the glide path (continuation of the runway axis from the cut-off point with the angle of inclination), but not further than the fourth turn point at long ranges. The size of the crosshair corresponds to the size of the slice of the course-glide zone at this range. With the capture of radio equipment of the airfield (if any), course and glide path frames appear, respectively.

The aircraft control complex operates as follows.

UAV flight control is carried out from operator workstations. From the control panel:

- task of the UAV flight mission;

- adjustment of the flight mission;

- adjustment of flight modes (course, path angle, altitude, flight speed, etc.);

- adjustment of the current management task;

- target allocation;

- management of a UAV group;

- recognition and target binding, etc .;

- control of the UAV trajectory movement;

- UAV payload management;

- control of the interacting UAV;

- control of the approach and landing at an unequipped operational landing site in difficult conditions by targeting the landing site, forming the parameters of the landing strip and the virtual glide path.

The control actions on the UAV are set from the workplace of the pilot-operator 1 to the computer control system 2, where they are processed, entered into the control program and transmitted via the communication equipment 5 and 6a to the UAV 6 to the control system 6c. The received control signals are processed by the control system 6c and the corresponding control signals are transmitted to the control elements of the aircraft, which control their position in accordance with the received control signals. The flight parameters of aircraft are constantly determined by sensors. The signals from the sensors are transmitted to the control system 6c, located on the UAV, are processed and through communication equipment 6a and 5 through the interface module 3 are transmitted to the computer control system 2, processed and transmitted to the workplace of the pilot-operator 1, as well as to the operator’s workplace load 8.

During the flight, information about the flight parameters is received by the pilot operator from the multifunction indicators 1a and 1b, and the payload operator from the multifunction indicators 8a and 8b.

Information about the flight parameters of the UAV is displayed on a color liquid crystal display monitor 1a and 8a.

Information on the navigation parameters of the UAV, digital cartographic, television and optoelectronic information is displayed on the color LCD monitors indicators 1v and 8v. Television and optoelectronic information comes from the television and optoelectronic sighting devices 6b installed on the UAV 6, through communication equipment 6a and 5 through the interface module 3.

The formation of the horizon horizon and fragments of the indication of aerobatic parameters, as well as the formation of a pseudo-volume image of the dangerous states of the trajectory maneuvering, is performed based on the signals of the real UAV position, the given values of the aerobatic parameters and the dangerous states of the trajectory maneuvering.

On the navigation indicator 8B from the computing control system 2, the data of the electronic map, the navigation situation and the position of the dangerous states when the UAV is near the ground are transmitted. The operator receives visualized information about the given flight path, the real path associated with the electronic map, as well as information about the location of the UAV relative to the ground.

Thus, the aircraft control complex contains:

- workplace of the operator-pilot,

- workplace of the payload operator,

- computing control system,

- interface units,

- communication modules of the ground control point with aircraft,

- unmanned aerial vehicles,

- a vehicle.

In the cab of the vehicle are installed:

- display for displaying a digital topographic map

- satellite navigation system for determining the location,

and in the kung:

- power supply system,

- a display indicator of the functioning of vehicle systems,

- control panel for auxiliary devices, a manipulator is installed in the end part of the kung for loading and unloading goods onto a platform or trailer. On the trailer are:

- ejection device used at launch;

- The aerofinisher used during landing.

The main components of the ground part of the complex:

- workplace of the operator-pilot,

- workplace of the payload operator,

- computing control system,

- interface units,

- communication modules of the ground control point with aircraft,

they are electrically interconnected and structurally combined into a single mechanical externally protected mobile structure with the possibility of ensuring joint and separate operation of operators to control leading and interacting aircraft, both when placing the structure on a motor vehicle or separately from it.

This technical solution allows you to:

- increase accident-free safety and flight efficiency,

- expand the capabilities of the aviation complex,

- provide management of group interaction of UAVs,

- provide operational maneuver with the use of UAVs,

- conduct training for operators without UAV launches.

Using the materials of this proposal, modeling was carried out on an interactive modeling stand and positive results were obtained confirming the feasibility of the proposed invention.

Claims (1)

Aircraft control system (Aircraft), containing the workplace of a pilot-operator with means for setting flight parameters for automatic control of aircraft, manual remote control bodies of an aircraft, flight indicator and navigation indicator, computer control system, interface units, communication module of the complex with aircraft for assigning control signals to the leading and interacting aircraft and receiving information from them about the flight Adania, characterized in that it includes the workplace of the payload operator, containing two multifunctional indicators for displaying digital cartographic, television and optoelectronic information, a display for pseudo-volume display of the external visual environment and training information, a payload control panel and a formation unit flight mission, and at the workplace of the operator-pilot an additional display is installed to visualize the control process of the aircraft and the pool control the modes of target designation of the landing site, correcting information and constructing a virtual glide path, while the functioning of the computational control system ensures the interaction of program modules for aircraft navigation and dispatching control of aircraft during group flight, a reference model of trajectory control, a base of geo-information data, assessment of dangerous conditions, and the formation of information for preventing collisions with the earth's surface and the withdrawal of aircraft from dangerous loyalty, the formation of an electronic aeronautical map with a tactical setting and a topographic map for driving a vehicle, preparing a flight and training task, building a virtual glide path for target designation modes, correcting flight information and landing along the glide path, forming a pseudo-volume display of the external visual situation and the training information module, and Also included is a motor vehicle in the cab of which a display is installed to display a digital topographic mouths and a satellite navigation system for determining the location, in the kung - the power supply system, a display for displaying the functioning of the vehicle systems and a control panel, in the end of the kung - a manipulator for loading and unloading goods, and on the trailer - an ejection device and an aerofinisher, while the main the components of the ground part of the complex are electrically interconnected and structurally combined into a single mechanical externally protected mobile structure with the possibility of providing Noah and the split of the operators to manage the driving and interacting with the aircraft as the placement of the design on the vehicle or separate from it.

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