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DEVICE FOR SEMI-ACTUAL SIMULATION OF AIRCRAFT CONTROL SYSTEM WITH ACTIVE HOMING HEADS

机译：主动蜂鸣器控制系统的半实物模拟装置

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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
机译：技术领域本发明涉及一种用于具有航空航天飞机（SA）的寻的头（HH）的控制系统（CS）的半实时仿真的设备，测试的性能以及对寻的可操作性和可控性的研究。头，以及调试作为CS和SA HH一部分的车载数字计算机（PC）的程序算法支持。装置包括平面有源相控天线阵列-APAA（14），它是一组发射元件（1），（2），（3），（6），（12），在平面上具有正方形或三角形阵列（14）的阵列，形成段，其模仿来自目标（15）的反射信号，噪声干扰信号（16）和中继干扰信号（18）。每个段（15），（16），（18）的排放始终指向主动自导引导头-ASGHH（7），它与惯性控制系统（8）一起安装在动态旋转工作台上（5）的哪个输入连接到计算模拟单元（4）的第一输出，从惯性控制系统（8）接收到该输入的信号。计算仿真单元（4）的第二，第三和第五输出分别连接到目标仿真单元（9）的第二输入，噪声干扰仿真单元（10）的输入以及中继干扰仿真单元（21）的第二输入，辐射元件从其输出信号传输到辐射元件（13）的开关单元的第一，第二和第三输入，其输出连接到辐射元件（1），（2），（3），（6），（12） 。计算仿真单元（4）的第四和第六输出端与辐射元件（13）的开关元件的第四输入端以及信号接收和处理单元（20）的第二输入端相连，信号接收和处理单元（20）的第一输入端与ASGHH（7）相连。 ）输出，并且该输出连接到中继模仿单元（21）的第二输入和目标仿真单元（9）的第二输入。该设备包括信号接收和处理单元（20），输入信号功率计单元，衰减器单元以及用于模拟中继干扰的单元（21），其中该单元用于接收脉冲或连续信号的单元，用于调制信号的单元通过幅度，相位，频率，信号延迟单元，辐射控制单元，中继发送信号发送单元。信号接收和处理单元的第一输入连接到ASGHH（7）输出，第二输入连接到计算建模单元（4）的第六输出，输出连接到目标仿真单元（9）的第一输入和中继干扰模拟单元（21）的第一输入。中继干扰模拟单元（21）的第一输入连接到信号接收和处理单元（20）的输出。第二输入连接到计算仿真单元（4）的第五输出。输出连接到辐射元件开关元件（13）的第三输入。效果：可以进行调试，测试，研究，使用AIGS的航天器的控制和归位系统的半实时仿真工作，以及还可以模拟中继干扰。; 1 cl，2 dwg

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