RU2418267C1 - Information-computer system of unmanned fighter - Google Patents

Abstract

FIELD: instrument making. ^ SUBSTANCE: information-computer system (ICS) of unmanned fighter (UF) includes Doppler speed and drift angle metre (DSDM); inertial and (or) satellite navigation system (NS); gyroscope (GR); accelerometre (ACC); radio detection station (RDS); onboard avionic system (OAS) including range finder (OAS RF), angle indicator (OAS AI) and receiver-transmitter (OAS R/T); optoelectronic system (OES) including range finder (OES RF) and angle indicator (OES AI); receiver of command control radio line (CCRL RCVR) of (UF); onboard computing system (OCS). ^ EFFECT: enlarging functional capabilities. ^ 1 dwg

Description

The invention relates to guidance systems and can be used to control unmanned fighter aircraft.

One of the most promising areas for the development of air defense systems, organically combining the requirements for expanding combat capabilities, increasing combat effectiveness and economical use, is the use of unmanned fighter aircraft (BSI).

To date, there are no developments in this area in our country. Among the foreign developments of the United States can be noted in the framework of two programs for the creation of specialized BSI, designated UCAV (Unmanned Combat Aerial Vehicle).

The most preferred BSI applications are:

- use in high-risk situations (suppression of air defense zones), counteraction to enemy aircraft with superior flight performance and means of destruction, counteraction to hypersonic aircraft (GZLA), etc.), as well as a means of delivery of microwave ) weapons of functional destruction [1] in the battle formations of the enemy;

- use as a strike group when intercepting well-defended air targets (aviation complexes of radar patrol and guidance, communication and control aircraft, relay aircraft, etc.).

Unmanned fighter planes are used, as a rule, in a group of 4, 5 aircraft [2, 3], which in addition to them includes a manned aircraft controlled by a pilot-commander, which manages the drones. Having assessed the situation, the commander assigns an individual goal for each BSI, which he then aims at. If there are several missiles on the BSI, a group of closely located air targets can be assigned.

It should be noted that BSI can be used not only as reusable vehicles for the delivery of weapons to the field of application, but also in the "kamikaze" mode.

Closest to the described system is the information computer system (IVS) of a modern manned fighter aircraft [4, 5]. At the same time, differences in the purpose, conditions and features of the use of BSI, as well as the requirements for its IVS, are largely determined by the absence of a pilot on board. With this in mind, the CHD of unmanned fighter jets should provide:

- information service methods for intercepting all types of targets;

- stable, high-precision functioning of all meters in a wider field of speeds, accelerations, ranges;

- high resolution of sighting systems, providing the possibility of individual guidance on the target in a dense group;

- high noise immunity, guaranteeing effective use in a complex signal-jamming environment and predetermining the need to use different frequency ranges and passive modes of operation of sighting systems;

- the ability to work in conditions of high information uncertainty, including in the conditions of a suppressed airborne radar station (radar);

- the possibility of operational retargeting;

- high speed due to the short reaction time to commands;

- the ability for the commander to intervene at any time in the BSI guidance process.

The logic of the BSI application determines the need for five basic modes of operation of the IVS, providing autonomous guidance, command (long-range) guidance, homing (short-range guidance), the issuance of target designation commands for weapons, as well as combined guidance, which provides, inter alia, the ability of the pilot-commander to to intervene in the guidance processes at any time.

To solve the latter problem, coordination of guidance methods at the stages of far and near guidance is necessary.

It should be noted that the BSI can be used not only to destroy the enemy’s aircraft, but also as a source of additional information for the manned aircraft and command posts (CP) of the Air Force ACS systems. In this regard, it is advisable to have a BSI ICS “call information from its board” (VIB) mode, when using which BSI data and information about its state and information about its state, as well as information, are transmitted to the control unit via the BSI data line transmitter about goals.

In some cases, the use of passive modes of radar and radio intelligence station (SRTR) is due to several reasons:

- the priority for the destruction of jamming aircraft as critical objectives;

- increased efficiency of digital radio suppression systems, which allow simulating the signals of suppressed radars with the highest accuracy, which makes it impossible to create effective means of noise protection;

- the presence on board modern aircraft of a large number of radio-emitting systems;

- an increase in the detection range of sources of radio emission (IRI) by passive methods, in comparison with methods of active radar.

However, it must be emphasized that when using passive radio meters, only the angular coordinates of the IRI can be measured, while for the implementation of modern all-aspect guidance methods, it is necessary to have estimates of the distance and speed of approach [4].

The formation of such estimates with acceptable accuracy in single-position passive systems is possible only when the BSI performs a sufficiently long maneuver [9], which is not always feasible in modern maneuverable combat. A more sophisticated method of forming estimates of the range and approach speed by angular measurements is the use of on-off radar [10].

This feature makes it possible to assume that in an IVS it is necessary to have a mode of collaboration with other BSI [11]. In addition, multi-position guidance systems provide an opportunity to get a number of advantages, providing increased survivability and combat effectiveness of the system as a whole.

The main requirements for BSI guidance methods are:

- universality, providing the possibility of all-round interception of all types of aircraft - from balloons and hovering helicopters to hypersonic aircraft and missiles;

- a combination of command and homing methods, providing a transition from one mode to another without significant transient processes;

- ensuring the maximum possible range of interception with minimal energy consumption spent on management;

- application at the stage of command guidance of a standard set of commands according to the course, altitude and speed used in existing command radio control lines [6].

One of the possible guidance methods that satisfy these requirements is the formation of the required lateral acceleration according to the law:

when using which the mismatch parameter is calculated according to the rule

In the relations (1) and (2):

- indices "G" and "B" correspond to horizontal and vertical planes;

- φ _T and ω _T are the required values of the side bearing and angular velocity of the line of sight, determined by the problem to be solved, the conditions of use, the operating modes of the sighting systems and the weapons used;

- j _{cg, in} - lateral acceleration of the target;

- текущие значения оценок бортового пеленга, угловой скорости линии визирования и поперечного ускорения;-

- current values of estimates of the side bearing, angular velocity of the line of sight and lateral acceleration;

- оценки дальности от БСИ до цели и скорости ее изменения;-

- estimates of the distance from the BSI to the target and the speed of its change;

- q _φ and q _ω - penalties for the accuracy of control in angle and angular velocity;

- k _j - penalty for the value of the control signal, depending on the maximum permissible value j _{tg, in} .

Analysis (1), (2) allows us to draw the following conclusions:

- the method is all-altitude, since the control error signal is generated not by the difference between the required and current positions of the rudders, the effectiveness of which depends on the height, but on the difference in accelerations;

- the method is multifaceted, since for different conditions the direction of flight is taken into account by the magnitude and sign of j _{tg, v} , φ _{tg, v} and ω _{tg, v} ;

- the method takes into account the maneuver of the target;

- the trajectory control algorithm (1), (2) provides good controllability both at large distances due to the first term in (1) and at small distances, guaranteeing high accuracy by taking into account the second term [6].

In this case, the choice of the coefficients q _φ and q _ω provides automatic control redistribution from the prevailing influence of the error in the angle at large distances to the prevailing effect of the error in the angular speed at short distances, thereby minimizing the miss [4]

Where

D - range from the BSI to the target;

ω is the angular velocity of the line of sight "BSI-target";

V is the speed of approach of the BSI with the target.

It is necessary to emphasize that (1), (2) make it possible to ensure a good pairing of homing and command control by taking into account the relationship between the derivative course and lateral acceleration [4]

- производная требуемого курса; j_т,г - требуемое ускорение в горизонтальной плоскости, рассчитываемое по (1); V_ГБСИ - горизонтальная составляющая скорости БСИ.Where

- derivative of the required rate; j _{t, g} - the required acceleration in the horizontal plane, calculated by (1); V _GBSI - horizontal component of the BSI speed.

According to relation (4), quite simply, at the kth time instants, the required course values are formed according to the rule

and the discrepancy parameters on the BSI’s board - according to the discrepancy

- оценка текущего значения курса БСИ.where T is the transmission interval of commands;

- assessment of the current value of the BSI rate.

For the implementation of (1), (2) and (5), (6), the BSI's IVS should include meters (algorithms for generating estimates) of distance, approach speed for the purpose, components of own speed, side bearings and angular velocities of the line of sight in horizontal and vertical planes, transverse accelerations of the target and BSI and its course.

It should be noted that estimates of all these phase coordinates must also be formed in the IVS of a manned aircraft.

The above features of the use of BSI, the requirements for its IVS and the guidance methods used in it necessitate the use of the following operating modes:

- search and capture targets on tracking;

- multi-purpose and single target tracking;

- target recognition;

- short-term and long-term forecast of the evolution of the goal;

- permission goals in a dense group;

- intellectual decision support;

- formation of decisions;

- integrated processing of information from sensors of various physical nature;

- the use of passive meters, including as part of a radar and a radio intelligence station;

- multi-hypothesis forecast;

- exchange of information with a manned aircraft and with other BSI.

The structural diagram of an ischemic heart disease that implements these modes is shown in the drawing, in which the inputs are indicated by numbers and the outputs by numbers in square brackets.

The system includes: Doppler speed and drift angle meter (DISS) 1, (NS) inertial and (or) satellite navigation system (NS) 2, on-board computer system (BVS) 3, on-board radar system (BRLS) 4, optoelectronic system (ECO) 5, the receiver of the command radio control line of an unmanned fighter aircraft (PRM KRU BSI) 6, the transmitter of the data line of an unmanned fighter airplane (PRD LPD BSI) 7, the information and computer system of the command post (IVS KP) 8, the gyroscope (GR ) 9, accelerometer (AKS) 10, station for technical intelligence (SRTR) 11, long-term prediction system (TIS) 12, a system of short-term prediction (UPC) 13, making formation system (FIS) 14.

The technical result that can be obtained from the implementation of the proposed technical solution lies in the fact that the information-computing system based on it provides effective all-angular management of BLI at any flight altitude and makes it possible to increase the survivability and efficiency of guidance systems and reduce the loss of flight personnel and expensive manned aircraft in warfare.

The specified technical result is achieved by the fact that in the information-computing system BSI containing DISS; National Assembly, GR; AKC; CPTR; Radar as part of a rangefinder (DM radar), goniometer (UM radar) and transceiver (PRM-PRD); OES as a part of a range finder (DM OES) and a goniometer (UM OES); receiver command radio control line (PPR KRU) (BSI), BVS, with the first output of the DISS connected to the first input of the NS, the second output of the DISS connected to the first input of the BVS, the second input of the BVS connected to the output of the NS, the third input of the BVS to the output of the ACS, the fourth BVS input - with GR output, the fifth BVS input - with SRTR output, the sixth BVS input - with the first output of the DM OES, the seventh BVS input - with the first output of the UM OES, the eighth BVS input - with the first output of the DM radar, the ninth BVS input - with the first output of the UM radar, the tenth input of the BVS - with the first output of the PF switchgear BSI, the first output of the BVS - with the second input NS house, the second BVS output is connected to the BSI control system (US), into which the mismatch parameter is received, the BSI data line transmitter (PDD) is additionally introduced; information and computing system of the command post (IVS KP) as part of the receiver of the data line of the command post (PFP LDP KP), the transmitter of the command radio link control command post (KPP KPU) and decision-making system (DSS), as well as a long-term forecast system (SDP ), a short-term forecasting system (SKP) and a decision-making system (SFR), with the third output of the BVS being the input of the PDP LPD BSI, the output of which is the input of the PRM LPD KP, the output of the PRM LPD KP is connected to the input of the SPPR, the output of the SPPR is connected to the input of the PRD KRU KP, in the output of which is the input of the PF switchgear BSI. The second output of the PF switchgear BSI is connected to the third input of the SFR, the first input of which is the first output of the SDP, and the second input is the second output of the SKP. The first output of the SFR is connected to the fifth input of the SDP, the second output of the SFR to the sixth input of the SKP, the third output of the SFR to the twelfth input of the BVS. The first inputs of the SDP and SKP are connected to the second output of the DM radar, the second inputs of the SDP and SKP are connected to the second output of the UM radar, and the third inputs of the SDP and SKP are connected to the first output of the PRM-PRD, the third output of the SKP is the fourth input of the SDP. The first output of the UPC is the eleventh input of the BVS, from the second output of which an error signal is supplied to the input of the BLI control system.

The functional purpose shown in the drawing is a block diagram of the BSI's IVS, which consists in converting measurements (estimates) of the phase coordinates of the absolute and relative motion of the target and the induced BSI into the mismatch parameters, which are the input actions of the BSI control system (US) [4] and provide a targeted change in its spatial provisions in accordance with (1) and (2).

The system operates as follows.

In the autonomous guidance mode, BSIs are displayed in the area of space in which they are confidently taken into control by the pilot of a manned fighter or the operator of the aircraft complex of radar patrol and guidance [7]. The flight to this area is based on information from the ANN, calculating the eigen coordinates x _BSI , z _BSI (with initial values x ₀ , z ₀ ) and measurements of the components of the own speed V _BSI coming from the DISS. To solve this problem, the SNA can also be used. The calculated coordinates are transmitted to the BVS, in which, according to one or another method of autonomous guidance [6], a mismatch parameter Δ is generated, which arrives at the control unit. Under the action of Δ, the control system deflects the rudders, causing the required changes in the spatial position of the BSI.

When using a stand-alone ANN during flight, errors are calculated for the coordinates x _BSI , z _BSI , which are corrected by the signals x _k , z _k generated in the BVS according to the estimates of the components of the DISS speed, or according to the estimates of the distance D _or and the direction-finding bearing φ _or to the previously planned radar Landmark coming from radar.

It should be noted that in stand-alone mode in the BSI on the switchgear can receive commands to redirect and change the operating mode of the IVS.

Command guidance mode has two varieties. In the first case, control commands in the form of the required course values Ψ _{T of} height H _T and speed V _{T are} formed at the command post or aviation complex of the radar patrol and guidance (AK RLDN). According to these commands, the BSI is taken to the area where it is taken over for control by a pilot of a manned aircraft, or by an operator of another AK RLDN. In its intended purpose, this mode is adequate to autonomous guidance.

The second type of command guidance is used to withdraw the BSI to the target capture area to be followed by sighting systems. In this case, the required values of Ψ _T , H _T, and V _T are formed either on the manned fighter or on the AC RLD. In this case, the required course values should be formed according to the law (5), which provides good pairing with the homing method (1), or according to one of the known methods of command guidance [6]. When the BSI is used in a group in the process of aiming at one target (group of targets), the values of Ψ _T , H _T and V _T for each object can be formed according to various laws that ensure the implementation of the plan of the pilot-commander or operator of guidance of the AC RLDN in the process of protecting it from fighters and enemy missiles.

When approaching a target at a certain distance through the PFP switchgear, a command is received to turn on its radar (ECO) and organize the search for a target according to a specific program for viewing the space. The command guidance stage ends with the capture of the radar or ECO target and taking it for auto-tracking in range, approach speed, airborne bearings and angular velocities of the line of sight, after which the IVS goes into homing mode.

, в угломерном -

, а оценки собственного курса

и конкретных ускорений

поступают от гироскопа и акселерометров (чертеж).In the homing mode, the required flight path is formed according to the law (1), and the mismatch parameter - according to the rule (2). For their information support in the radar station (ECO) BSI in the rangefinder channel, estimates are formed

, in goniometric -

, and assess your own course

and specific accelerations

come from a gyroscope and accelerometers (drawing).

For individual destruction of targets designated by the pilot-commander (guidance operator), in a dense group, the algorithm of the so-called trajectory control of observation is used. In this case, the required values of the side bearing and φ _{T of the} angular velocity ω _T in (1) are calculated according to special rules [8], when using which the resolution according to angular coordinates is determined not by the width of the radiation pattern, but by the resolution according to the Doppler frequency, leading to Doppler sharpening of the beam when flying along a special trajectory.

It should be noted that radar and ECO work according to well-known algorithms [4, 5].

If the BLS is used as a source of additional information for the manned aircraft and the CP of the ACS systems of the Air Force in the “information recall” (VIB) mode, then the BSI transmitters transmit the estimates of the relative and absolute motion of the BSI, its status and information about the targets to the CP.

In the absence of command radio control (KRU), for example, due to its suppression by the enemy, prediction of the trajectory evolution of the target and autonomous formation of decisions on aiming at the target in the IVS BSI provides SFR, and in the IVS KP - a decision support system (DSS). In this case, the forecast of enemy behavior should have two features. One is due to the need for a short-term forecast of the spatial position of the enemy, the duration of which is limited by the lifetime of the motion hypothesis, which forms the basis of the forecast. This forecast is implemented in the short-term forecast system (UPC). The second one predetermines the need for a long-term forecast based on knowledge of the tactics of actions and typical methods of adversary actions [12], which is implemented in the long-term forecast system (SDP). These features lead to the use of an apparatus of fuzzy logic of multihypothesis tracking with the estimation of high derivatives of range and angles and synthesis of systems based on the concept of systems with variable structure.

LITERATURE

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2. Khripunov S.P., Makarov A.V. Unmanned fighters in aerial combat. // Aerospace review. - 2003. - No. 6.

3. Levitsky S.V., Kiselev M.A., Stupak Yu.V., Shumsky A.V. The concept of creating a combat aviation complex based on an unmanned fighter aircraft. // Bulletin of the Academy of Aviation and Aeronautics. - 2003. - No. 2.

4. Merkulov V.I., Drogalin V.V., Bogachev A.S. and other Aviation systems of radio control. T.2. Electronic homing systems. / Ed. Kanaschenkova A.I. and Merkulova V.I. - M.: Radio Engineering, 2003.

5. Antipov V.N., Isaev S.A., Lavrov A.A., Merkulov V.I. Multifunctional fighter radar systems. / Ed. Kondratenkova V.S. - M.: Military Publishing House, 1994.

6. Merkulov V.I., Chernov V.S., Drogalin V.V. and other Aviation systems of radio control. T.3. Command radio control systems. Autonomous and combined guidance systems. / Ed. Kanaschenkova A.I. and Merkulova V.I. - M .: Radio engineering, 2004.

7. Willow V.S. Aviation complexes of radar patrol and guidance. Status and development trends. - M.: Radio Engineering, 2008.

8. Merkulov V.I. Improving the resolution of the onboard radar system in the angle by means of trajectory control of observation. // Radio engineering. - 2003. - No. 1.

9. Drogalin V.V., Merkulov V.I., Chernov V.S. and others. Determination of coordinates and parameters of motion of radio emission sources from the goniometer data in single-position onboard radar systems. // Foreign radio electronics. Successes of modern radio electronics. - 2002. - No. 3.

10. Drogalin V.V., Efimov V.A., Merkulov V.I. et al. Algorithms for estimating coordinates and motion parameters of radio-emitting targets in goniometric on-off airborne radar systems. // Information-measuring and control systems. - 2003. - No. 1.

11. Merkulov V.I., Chernov B.C., Yurchik I.A. Aircraft multi-position radio control systems. // Successes of modern radio electronics. - 2006. - No. 12.

12. Khripunov S.P., Demin A.N. Algorithms for predicting enemy tactics in group aerial combat. Proceedings of VVIA them. prof. N.E. Zhukovsky. - M .: Radio engineering, No. 2, t.80, 2008.

Claims (1)

Information and computing system (IHD) of an unmanned fighter aircraft (BSI), containing a Doppler speed and drift angle meter (DISS), an inertial and (or) satellite navigation system (NS), a gyroscope (GR), an accelerometer (ACS), and a radio engineering station intelligence (SRTR), airborne electronic system (BRLS), including a rangefinder (DM BRLS), an angle meter (UM BRLS) and a transceiver (PPD BRLS); optoelectronic system (OES), including a range finder (DM OES) and a goniometer (UM OES); receiver command radio control line (PFP KRU) (BSI), on-board computer system (BVS), while the first output of the DISS is connected to the first input of the NS, the second output of the DISS is connected to the first input of the BVS, the second input of the BVS is connected to the output of the NS, the third input of the BVS - with ACS output, the fourth BVS input - with GR output, the fifth BVS input - with SRTR output, the sixth BVS input - with the first output of the DM OES, the seventh BVS input - with the first output of the UM OES, the eighth BVS input - with the first output of the DM radar , the ninth input of the BVS - with the first output of the UM radar, the tenth entrance of the BVS - with the first output of the PF KRU BS And, the first BVS output is with the second NS input, the second BVS output is the input of the BSI control system (US), to which the mismatch parameter Δ is received, characterized in that the BSI data line transmitter (PDD) is additionally introduced into it; information and computer system of the command post (IHD KP) as a part of the receiver of the data line of the command post (PFP LPD KP), the transmitter of the command radio control line of the command post (KPP KPU) and decision-making system (DSS); long-term forecast system (SDP), short-term forecast system (SKP), decision-making system (SFR), while the third output of the BVS is the input of the PDD of the BSI, the output of the PDD of the BSI is the input of the PDM of the PDP, at which the output is connected to the input of the DSS, the output of which is connected to the input of the switchgear switchgear switchgear KP, whose output is the input of the switchgear switchgear switchgear BSI, the second output of the switchgear switchgear switchgear BSI is connected to the third input of the SFR, the first input of the SFR is connected to the output of the SDP, and the second input to the second output of the control switch with the fifth input of the SDP, the second output of the SFR - with the sixth input SKP house, the third SFR output - with the twelfth input of the BWS, the first inputs of the SDP and SKP are connected to the second output of the DM radar, the second inputs of the SDP SKP are connected to the second output of the UM radar, and the third inputs of the SDP and SKP are connected to the first output of the PRM-PRD of the radar, the fourth input of the UPC is the second output of the DM OES, the fifth input of the UPC is the second output of the UM of the OES, the first output is the eleventh input of the BVS, and the third output is connected to the fourth input of the SDP.