RU2692456C1 - Device for semi-actual simulation of aircraft control system with active homing heads - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: invention relates to devices for semi-real-time simulation of control system (CS) with homing heads (HH) of air and space aircrafts (SA), performance of tests and studies of operability and controllability of homing heads, as well as for debugging of program-algorithmic support of on-board digital computers (PC), which are part of CS and SA HH. Device comprises a flat active phased antenna array - APAA (14), which is a set of emitting elements (1), (2), (3), (6), (12), having a square or triangular shape on the plane of array (14), from which segments are formed, which imitates reflected signals from target (15), signals of noise interference (16) and signals of relay interference (18). Emissions of each of segments (15), (16), (18) are always directed towards the active self-guidance homing head - ASGHH (7), which together with the inertial control system (8) is installed on the dynamic rotary bench (5), which input is connected to the first output of computational-simulating unit (4), to the input of which signals from the inertial control system (8) are received. Second, third and fifth outputs of computing-simulating unit (4) are connected to second input of target simulation unit (9), to input of noise interference simulation unit (10) and with second input of relaying interference simulation unit (21), from which outputs signals are transmitted to first, second and third inputs of switching unit of radiating elements (13), output of which is connected to radiating elements (1), (2), (3), (6), (12). Fourth and sixth outputs of computing-simulating unit (4) are connected to fourth input of switching element of radiating elements (13) and to second input of signal receiving and processing unit (20), first input of which is connected to ASGHH (7) output, and the output is connected to the relay imitation unit (21) second input and to the target simulation unit (9) second input. Device comprises a signal receiving and processing unit (20), an input signal power meter unit, an attenuator unit, as well as a unit for simulating relay interference (21) with a unit for receiving pulse or continuous signals, a unit for modulating signals by amplitude, phase, frequency, a signal delay unit, a radiation control unit, a relay transmitting signal transmitting unit. First input of signal reception and processing unit is connected to ASGHH (7) output, second input is connected to sixth output of computation-modeling unit (4), output is connected to the first input of the target simulation unit (9) and to the first input of the relaying interference simulating unit (21). First input of the relaying interference simulation unit (21) is connected to the output of the signal receiving and processing unit (20). Second input is connected to fifth output of computation-simulating unit (4). Output is connected to the third input of the switching element of radiating elements (13).EFFECT: possibility of performing works on debugging, testing, research, semi-real-time simulation of control and homing systems of space aircraft with AIGS, and also to imitate relay interference.1 cl, 2 dwg

Description

SUBSTANCE: invention relates to devices for semi-natural modeling of a control system (SU) with homing heads (GOS) of air and spacecraft (LA), conducting tests and studies of the performance and controllability of aircraft homing heads, as well as for debugging software and algorithmic support of on-board digital computers (BTsVM), members of the SU LA and GOS LA.

The device for semi-natural modeling of control systems and aircraft homing allows to work out the interaction of all onboard aircraft systems involved in the operation of control systems and homing aircraft, debugging software and algorithmic support of onboard passive, semi-active, active hf in real-time over the entire range of angular velocities of the sight line "LA-target" and the angles of rotation of the GOS without distorting the dynamics of the contour of the homing system of the aircraft, with imitation of radio-noise environment, including with imitation of retro power interference.

An analogue of the device can serve as the invention EN 2263869, F41G 3/26, G09B 9/08. 2005.

As a prototype of the device, an application for invention No. 2015137623 dated 03/04/2015 g “Method for semi-natural modeling of an aircraft homing system and device for its implementation”, containing (FIG. 1) flat active phased array antenna (AFAR) 14, representing a set of radiating elements 12, having a square or triangular shape on the lattice plane, from which segments are formed: one segment 15 — forming a useful signal and other segments forming signals of a radio noise environment. FIG. 1 shows one of these segments 16. The radiation 17 and 11 of each of the segments are always directed towards the GSN 7, which, together with the inertial control system 8, is installed on a dynamic rotary stand 5, the input of which is connected to the first output of the computing and modeling unit 4, to the input which receives signals from the inertial control system 8. The second and third outputs of the computing and modeling unit 4 are connected to the imitation inputs of the target 9 and the noise interference simulation unit 10, from the outputs of which the signals are transmitted to the first and second the inputs of the switching unit radiating elements 13, which, under the control of the computing and modeling unit 4, the fourth output of which is connected to the third input of the switching device radiating elements 13, distributes the signals to the radiating elements 12, which is shown conventionally.

In the modeling complex of the prototype GOS receives useful signals emitted by a segment formed from radiating elements of an AFAR of n × m size, which moves along the plane of the lattice, thereby simulating the mutual position of the aircraft and the target, radiating signals in the direction of the GOS, and additionally on the plane of the AFAR other segments moving along the AFAR plane, emit signals also in the direction of the GOS and imitate: jamming interference, self-protection, distracting noise, Doppler noise, etc., which makes it possible to reproduce radio noise The situation for the GOS is close to real in almost the entire range of the angular displacement of the GOS LA antenna. In this case, the GOS works only in the mode of receiving signals, and the radio noise environment is simulated on the basis of a priori knowledge of the parameters of the received GOS signals.

Thus, the device of the prototype does not allow for debugging, testing, research, semi-natural modeling of control systems and homing of an aircraft with an active type HL (AGSN), and does not imitate retransmission interference.

The technical result and the essence of the invention consists in providing the ability to carry out work on debugging, testing, research, semi-natural modeling of control systems and homing aircraft with AGSN, as well as to further simulate the relay interference.

The technical result is achieved by the fact that the device contains a flat active phased antenna array (AFAR), representing a set of radiating elements having a square or triangular arrangement on the plane of the lattice, from which the segments are formed: the first segment, simulating the reflected signals from the target, the second segment, imitating signals of noise interference and the third segment, imitating signals of relay interference, the radiation of each of which is always directed towards the active homing head (AGSN), which Toraya, together with an inertial control system, is installed on a dynamic rotary stand, the input of which is connected to the first output of the computing and modeling unit, the input of which receives signals from the inertial control system, the second, third and fifth outputs of the computing and modeling unit are connected to the second input of the target simulation unit , with the input of the noise interference simulation block and with the second input of the relay interference simulation block, from the outputs of which the signals are transmitted to the first, second and third inputs of the block is switched I emitting elements, the output of which is connected to the radiating elements, and the fourth and sixth outputs of the computing and modeling unit are connected to the fourth input of the switching unit of the radiating elements and the second input of the signal receiving and processing unit, the first input of which is connected to the output of the AHSN, and the output is connected to the second input of the relay interference simulation block and the second input of the target simulation block, characterized in that the device contains two blocks: a signal receiving and processing block, which consists of: a measuring node the input power, the attenuator node, and the relay interference simulation unit, which includes: a pulse or continuous signals receiving node, a signal modulator node in amplitude, phase, frequency, a signal delay node, a radiation control node, a transmission node for the relay signals, This first input of the signal receiving and processing unit is connected to the AHSN output, the second input is connected to the sixth output of the computing and modeling unit, the output is connected to the first input of the target simulation block and to the first input of the block tation relay interference, and the first input of the interference simulation relay connected to the output receiving signal processing unit and a second input coupled to the fifth output computationally modeling unit, an output connected to a third input of the switch radiating elements.

This technical result is achieved by the fact that the composition of the known device (application for the invention No. 2015137623 from 04.03.2015 g "Method polunature modeling the homing system of the aircraft and device for its implementation") introduces two additional blocks: the unit receiving and processing signals, the structure of which includes: the node of the power meter of the input signals, the node of the attenuator, and the block of simulation of relay interference, which consists of: the node receiving the pulsed or continuous signals, the node of the modulator signal amplitude, phase, frequency, signal delay unit, the radiation control unit, relay node and a signaling simulating relay unit interference.

FIG. 1 and FIG. 2 presents drawings explaining the claimed technical solution. FIG. 1 is given for explanation of the prototype. FIG. 2 for convenience, used prototype digitization.

FIG. 1 and FIG. 2:

1. Radiating element.

2. Radiating element.

3. Radiating element.

4. Computational modeling block.

5. Dynamic swivel stand.

6. Radiating element.

7. Active homing head.

8. Inertial control system.

9. Block target simulation.

10. Block imitation of noise interference.

11. Signals that simulate noise interference.

12. Radiating element.

13. The switching unit radiating elements.

14. Active phased antenna array.

15. Segment, imitating the reflected signals from the target.

16. Segment, imitating interference of cover, self-cover, leading, etc.

17. Signals that mimic the reflection from the target.

18. Segment, imitating the relay interference.

19. Signals that mimic the relay interference.

20. Block receiving and processing signals.

20.1. Node power meter input signals.

20.2. Attenuator node.

21. Relay interference simulation unit.

21.1 Node receiving pulse or continuous signals.

21.2. Node modulator signals in amplitude, phase, frequency.

21.3. Signal delay node.

21.4. Node control radiation.

21.4 Relay signal transmission node.

The technical novelty of the invention lies in the fact that due to the inclusion in the block diagram of the device two new blocks: the block of receiving and processing signals 20 and the block of simulating relay interference 21, the stand acquires a new quality - the ability to work on debugging, testing, research, semi-natural modeling LA homing systems not only with passive and semi-active GOS, but also with active GOS, and with imitation, at the same time, relay interference.

Device for semi-natural modeling of the control system of an aircraft with active homing heads (Fig. 2) contains a flat active phased antenna array (AFAR) 14, representing a set of radiating elements 1, 2, 3, 6, 12, etc., having a square or triangular shape location on the plane of the lattice, of which segments are formed: the first segment 15, simulating the reflected signals 17 from the target, the second segment 16, simulating the signals of noise interference 11 and the third segment 18, simulating the signals of relay interference 19, and The radiation of each of which is always directed towards the active homing head (AGSN) 7, which, together with the inertial control system 8, is installed on a dynamic swivel stand 5, the input of which is connected to the first output of the computing and modeling unit 4, the input of which receives signals from the inertial system control 8, the second, third and fifth outputs of the computing and modeling unit 4 are connected to the second input of the target simulation block 9, to the input of the noise interference simulation block 10 and to the second input of the retro simulation block inherent noise 21, from the outputs of which the signals are transmitted to the first, second and third inputs of the switching unit of the radiating elements 13, the output of which is connected to the radiating elements 1, 2, 3, 6, 12, etc., and the fourth and sixth outputs of the computing and modeling unit 4 is connected to the fourth input of the switching unit of the radiating elements 13 and to the second input of the signal receiving and processing unit 20, the first input of which is connected to the output of the AGSN 7, and the output is connected to the second input of the relay interference simulation block 21 and to the second input of the simulation block Objectives 9, characterized in that the device contains two blocks: a block of receiving and processing signals 20, which consists of: a node of a power meter of input signals 20.1, a node of an attenuator 20.2, and a block of simulating relay interference 21, which consists of: a node of receiving pulsed or continuous signals 21.1, node modulator signals in amplitude, phase, frequency 21.2, node delay signals 21.3, node radiation control 21.4, node transmitting relay signals 21.5. The first input of the signal receiving and processing unit 20 is connected to the AGHSN 7 output, the second input is connected to the sixth output of the computing and modeling unit 4, the output is connected to the first input of the target simulation block 9 and to the first input of the relay interference simulation block 21, and the first input the relay interference simulation unit 21 is connected to the output of the signal receiving and processing unit 20, the second input is connected to the fifth output of the computing and modeling unit 4, the output is connected to the third input of the switching unit of the radiating elements 13.

Device for semi-natural modeling of the control system of the aircraft operates as follows.

и углам ориентации ЛА в пространстве ϕ_iЛА, которые поступают на динамический поворотный стенд 5, на котором установлена исследуемая ГСН 7 совместно с инерциальной системой управления 8. Одновременно вычислительно-моделирующий блок 4, решая уравнения движения цели относительно ЛА, определяет данные:Computational-modeling unit 4 in a general form solves the equations of the dynamics of the aircraft and the spatial movement of the aircraft, the movement of the target and the mutual movement of the aircraft and the target, and as a result, forms signals proportional to the angular velocities of the movement of the aircraft around the center of mass of the aircraft

and angles of orientation of the aircraft in space ϕ _ILA , which are fed to a dynamic swivel stand 5, on which the investigated GOS 7 is installed together with the inertial control system 8. At the same time, the computing and modeling unit 4, solving the equations of motion of the target relative to the aircraft, determines the data:

- the position of the target in space relative to the aircraft and the corresponding position of the emitting useful signals of the segment 15 (so that it is directed towards the GOS) on the plane AFAR 14, which is formed from the radiating elements 1, 2, 3, 6, 12, etc. AFAR 14 and has a size of n × m elements;

- the position of the source of interference interference in space relative to the aircraft and the corresponding position of the segment emitting signals (in particular, as shown in Fig. 2, segment 18, so that it is directed towards the GOS) on the plane AFAR 14, which is formed from the radiating elements 1 , 2, 3, 6, 12 and others. AFAR 14 and has a size of n1 × m1 elements;

- the position of sources of noise interference in space relative to the aircraft and the corresponding position of the segments emitting signals (in particular, as shown in Fig. 2, segment 16, so that it is directed towards the GOS 7) on the plane AFAR 14, which is formed from the radiating elements 1, 2, 3, 6, 12, etc. AFAR 14 and has a size of n2 × m2 elements;

- phase delay of the radiation of each radiating element 1, 2, 3, 6, 12 and other segments 15, 18, 15 AFAR 14, which determines the position of the phase front of the segments so that the perpendicular to the phase front of the respective segments is directed to the GOS 7 ;

- change the frequency of the signals as a function of the calculated reciprocal velocity of the aircraft and the target, which is necessary to simulate the Doppler effect;

- the power of the signals as a function of the calculated distance between the aircraft and the target, taking into account the distance between the AESA 14 and the GOS 7;

- characteristics of the target (EPR goals, angle of the goal, distance to the target, etc.);

- characteristics of the radio noise environment and, in particular, relay interference: the level of modulation of the AHSN signals in amplitude, phase, frequency, the amount of delay of the AHSOS signals;

- signal fluctuations, including a change in the polarization of the reflected signals to simulate the reflected signals from the target.

These data (Fig. 2) from the computing and modeling unit 4 are fed to the switching unit of the radiating elements 13 AFAR 14, as well as to the receiving and processing unit 20, to the target simulation unit 9, the relay interference simulation unit 21, the noise interference simulation unit 10 to set the characteristics of the target, radio noise environment and, including, relay interference. The signals from blocks 21, 9, 10 through the switching unit radiating elements 13, which preconfigured by the commands of the computing and modeling unit 4 radiating elements 1, 2, 3, 6, 12 and other segments 15, 16 and 18 to the transfer mode, arrive on radiating elements 1, 2, 3, 6, 12, etc., the totality of which, defined in the computing and modeling unit 4 forms the corresponding segments 15, 16, 18, their spatial position on AFAR 14, the position of the phase front of each segment, due to the delay the phase of radiation of each radiating element egmenta, output power and reproduces the signal parameters of noise interference and interference the relay, which creates conditions for the simulation target, and radio noise environment, including interference in the relay HIL LA real flight to the target. Signals from the output of AGSN 7 are fed to the input of the receiving and processing unit of signals 20 via a high-frequency cable and, after receiving and processing with the help of nodes 20.1 and 20.2, according to information from the computing and modeling unit 4, are fed to the simulation unit of target 9 to simulate signals reflected from the target 17 and a relay interference simulation unit 21, where, according to information from the computing and modeling unit 4, using nodes 21.1-21.5 are used to simulate the relay interference signals 19.

In this case, in blocks 1-21 elements of wide application are used.

The invention is illustrated by the drawing, which shows a block diagram of a device - a stand for semi-natural modeling of an aircraft control system with homing heads (Fig. 2). FIG. 2 shows three types of segments, the number of which may be different.

The use of a device for semi-natural modeling of an aircraft control system allows for testing the interaction of all on-board aircraft systems involved in the operation of aircraft control and homing systems, debugging software and algorithmic support of the on-board computer in the GOS in real time in the entire range of angular velocities of the “LA-target” without distortion of the dynamics of the aircraft self-homing system contour, with passive, semi-active and active type HSS and simulate the radio-noise environment and, in particular, retransmit interference interference.

The proposed device for semi-natural modeling of an aircraft control system with active homing heads allows in some cases to replace field tests with semi-natural modeling, which provides a significant reduction in the cost of field tests of aircraft control systems.

List of used sources

1. RU 2263869, F41G 3/26, G09B 9/08. 2005.

2. Application for invention No. 2015137623 dated 03/04/2015 g “Method for semi-natural modeling of the homing system of an aircraft and device for its implementation”.

Claims (1)

Device for semi-natural modeling of an aircraft control system with active homing heads, containing a flat active phased antenna array - AFAR, representing a set of radiating elements having a square or triangular shape on the plane of the grid from which the segments are formed: the first segment imitating the reflected signals from the target , the second segment imitating the noise interference signals and the third segment simulating the relay interference signals, the emissions of each of which always directed towards the active homing head - AGSN, which, together with the inertial control system, is installed on a dynamic rotary stand, the input of which is connected to the first output of the computing and modeling unit, the input of which receives signals from the inertial control system, the second, third and fifth outputs are computationally -model unit is connected to the second input of the target simulation block, to the input of the noise interference simulation block and to the second input of the relay interference simulation block, from the outputs of which The signals are transmitted to the first, second and third inputs of the switching unit of the radiating elements, the output of which is connected to the radiating elements, and the fourth and sixth outputs of the computing and modeling unit are connected to the fourth input of the switching unit of the radiating elements and the second input of the signal receiving and processing unit. which is connected to the output of AGSN, and the output is connected to the second input of the relay interference simulation block and to the second input of the target simulation block, characterized in that the device contains two blocks: Signal reception and processing, which consists of: an input power meter node, an attenuator node, and a relay interference simulation unit, which includes: a pulse or continuous signal receiving node, a signal modulator node in amplitude, phase, frequency, delay node signals, a radiation control unit, a relay signal transmission unit, the first input of the signal receiving and processing unit is connected to the AHSN output, the second input is connected to the sixth output of the computing and modeling unit, the output is dinene with the first input of the target simulation block and the first input of the relay interference simulation block, and the first input of the relay interference simulation block is connected to the output of the signal receiving and processing unit, the second input is connected to the fifth output of the computing and modeling block, the output is connected to the third input of the switching block radiating elements.

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