RU2560170C1 - Method of tests of aircrafts with telemetric system of registration of key parameters and device for its implementation - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: system of tests of aircraft with telemetric system of registration of key parameters contains the functional units, the control equipment, the onboard telemetric transferring module (OTTM) with the antenna installed on the aircraft (A)and the ground receiving station with antenna. The ground receiving station contains the registration telemetric system equipment which comprises the control panel, the calculator, the targeting drive connected in a certain way.

EFFECT: steady reception of telemetric information from aircrafts at long-range flight and complex profiles of its trajectory.

1 dwg

Description

The proposed group of inventions relates to military equipment and can be used in complexes of testing ground aircraft (LA) (guided missiles or shells).

Testing modern aircraft is an expensive process, requiring significant material, time costs. To evaluate the technical solutions used in aircraft design, it is necessary to obtain reliable and most complete data on the functioning of the aircraft and its units at all stages of aircraft testing.

A known method of testing a rocket with a telemetric registration system for its basic parameters, in which telemetry information is read from the functional blocks of the rocket, is transmitted to the on-board telemetry transmitting module (BTMP), where it is converted to a digital binary code, from which information packets are generated in binary code about each registered parameter. During the flight of the rocket, the BTPM emits information packets in binary code about each registered parameter. A digital sequence of codes is transmitted through the BTPM, an antenna system over the air, to the ground receiving point (NPP) of the ground equipment of the telemetric registration system, in which information is received, processed in real time, RF patent No. 2373486, publication 2009, November 20, class IPC F42B 15/00 / 1 /.

When implementing this method, ground-based equipment of the telemetric registration system is used, which contains an NPC with an antenna, and a rocket with a telemetric registration system of its main parameters, which contains functional blocks, control equipment, BTMP, consisting of a series-connected analog-to-digital converter, a signal controller, and a multi-channel radio transmitter, connected through a switching device with a BTMP antenna, while the inputs of the analog-to-digital converter are connected to the functional outputs units and control equipment, and the control input of the multi-liter radio transmitter is connected to one of the outputs of the control equipment / 1 /.

The known method for testing a rocket with a telemetric registration system for its main parameters and a rocket with a telemetric registration system for its basic parameters provide real-time multichannel transmission of information about the parameters of the functioning of rocket blocks during testing and testing. However, when launching an aircraft over a long range with a complex trajectory profile, due to the limited aperture of the antenna pattern of the low-frequency antenna, the radio-visibility of the aircraft over the entire flight path is not ensured, which leads to a significant, several-fold decrease in the transmission coefficient of the low-frequency antenna relative to the BTMP antenna. These factors lead to a multiple decrease in the energy of the received LPC signal and distortion of telemetry information to its complete loss in some parts of the aircraft trajectory, and also make it difficult and sometimes impossible to justify the analysis of the functioning of the main sides and nodes of the aircraft during its flight.

Therefore, the objective of the proposed group of inventions is to eliminate the above drawbacks, namely, providing the NRP telemetry registration system of the main parameters with reliable uninterrupted communication with the aircraft on the entire flight path at long flight ranges and complex path profiles, the stable reception of telemetry information from the aircraft to the NLP, improving accuracy and the reliability of the test results of the aircraft and the analysis of the functioning of the aircraft blocks.

In the method of testing aircraft with a telemetric registration system for the main parameters, which includes reading telemetric information from the functional blocks of the aircraft, converting it into binary code, from which information packets about each registered parameter are formed, radiation of information packets in the direction of the ground control equipment of the ground-based telemetry registration system, receiving and processing information in real time in the RPE, the task is achieved by the fact that before launching the aircraft, they also calculate the initial data are brought into the ground equipment of the telemetric registration system: the coordinates of the position of the antenna of the LSP and the dependence of the trajectory parameters of the aircraft on the flight time, from the moment of launch and during the flight of the aircraft, they read the current calculated trajectory parameters of the aircraft in real time, the reference point of which is synchronized with the moment of launch of the aircraft , calculate the direction of the aircraft relative to the position of the antenna NPP, combine the axis of the radiation pattern of the research institute with the direction to the aircraft.

In the aircraft testing system with a telemetric registration system for the main parameters, containing functional blocks installed on the aircraft, control equipment, BTMP with an antenna, and in the ground equipment of the telemetric registration system - a ground receiving station with an antenna, while the inputs of the BTMP are connected to the outputs of the functional blocks and control equipment, the task is achieved by the fact that the ground-based equipment of the telemetric registration system is equipped with series-connected control panel, a calculator and a guidance drive, the output of which is connected to the antenna of the NPP, while the second input of the calculator at the time of launching the aircraft in parallel with the aircraft is connected to the second output of the control panel.

The technical result is provided due to the fact that in the test method of aircraft with a telemetric registration system for the main parameters before starting the aircraft, the initial data are calculated and input into the ground equipment of the telemetric registration system: coordinates of the position of the antenna of the scientific research institute and the dependence of the trajectory parameters of the aircraft on the flight time, from the moment of launch and during the flight of the aircraft, the current calculated trajectory parameters of the aircraft are read in real time, the origin of which is synchronized with the time of launch and the aircraft, calculate the direction of the aircraft relative to the position of the antenna NPP, combine the axis of the antenna pattern of the NPP with the direction to the aircraft.

For this, the ground-based equipment of the telemetric recording system is equipped with a control panel, a calculator and a guidance drive connected in series, the output of which is connected to the NPP antenna, while the second input of the calculator at the moment of launching the aircraft in parallel with the aircraft is connected to the second output of the control panel.

The result of all operations is a tracking radiation pattern of the LSP antenna, which during the flight of the aircraft is directed to the BTPM antenna, which provides an increased energy reserve of the radio channel and stable communication of the aircraft with the LSP throughout the flight path.

This technical solution is illustrated by graphic materials.

In FIG. schematically shows a block diagram of an aircraft testing system with a telemetric registration system for the main parameters, with the help of which the proposed test method for aircraft is implemented, where

1 - aircraft;

2 - functional blocks;

3 - control equipment;

4 - BTPM;

5 - antenna BTMP;

6 - ground equipment telemetric registration system;

7 - NPP;

8 - antenna NPP;

9 - guidance drive;

10 - calculator;

11 - control panel.

Before starting at a given range in the ground-based equipment of the telemetric registration system (6) in the control panel (11), for example, from satellite navigation equipment, the coordinates of the position of the antenna of the NPP (8) are determined. Ballistic, program data are entered from the keyboard of the block (11) and the trajectory parameters of the aircraft (1) are calculated.

Based on the calculations in the control panel (11), the initial data is generated: the coordinates of the antenna position of the LSP and the dependence of the trajectory parameters of the aircraft on the flight time and enter them into the random access memory (RAM) of the computer (10).

When launching an aircraft (1) from the control panel (11), using the “Shot” button, a command is sent via the start cable to the launch circuits of the aircraft (1) and to the synchronizing (second) input of the computer (10). In block (10), the current time of the flight of the aircraft t _i begins and the current design path parameters of the aircraft (1) entered in the RAM, corresponding to t _{i, are} read.

When testing the aircraft from the outputs of the functional units (2), telemetry signals containing information on the main parameters of the aircraft (1) and control signals of the control equipment (3) are fed to the inputs of the BTPM (4). In block (4), according to the control equipment signals (3) according to the control algorithm of the aircraft, the telemetry signals from the outputs of the functional blocks (2) are converted into binary code and formed into information packets about each registered parameter, which are emitted by the BTPM antenna (4) in the direction of the NRP (7).

In the calculator (10) at the moments t _i , the direction of the aircraft (1) relative to the position of the antenna of the NPP (8) is calculated from the coordinates of the position of the antenna of the NRP (8) and the current trajectory parameters of the aircraft (1). At the output of the calculator (10), a signal proportional to this direction is formed and fed to the input of the guidance drive (9) connected to the antenna of the NPP (8). The guidance drive (9), based on the received signal, deploys the antenna of the NRP (8) so that the axis of the antenna pattern of the NRP (8) is aligned with the calculated direction to the aircraft (1). The result of all operations is a tracking radiation pattern of the NPP antenna, the axis of which is directed to the aircraft (1). In this case, the time step At _{i is} selected from the necessary accuracy of tracking the antenna pattern of the NPP antenna (8) for the aircraft (1).

NPP (7) through the antenna NPP (8) receives signals from the aircraft (1), decrypts the received data on the parameters of the functional units (2) and processes telemetry information. The axis of the antenna pattern of the NLP antenna (8) is directed at the aircraft (1), which ensures the operation of the LNP antenna with a directional coefficient close to the maximum, therefore, the stability of communication between the LNP (7) and the BTPM (4) along the entire flight path of the aircraft.

In the proposed device, the functional blocks (2), control equipment (3), BTPM (4), antenna BTPM (5), NPP (7), antenna NPP (8) can be performed, for example, similarly to the prototype blocks / 1 /. Guidance drive (10) can be performed, for example, as a direct current tracking drive, L.V. Rabinovich, B.I. Petrov, V.G. Terskov et al. Design of tracking systems, ed. L.V. Rabinovich. M., Mechanical Engineering, 1969, pp. 86-87, / 2 /. As a computer (10) and a control panel (11), for example, a small baguette-type computer can be used similarly to a gun control panel, RF patent No. 2247297, publication 02.27.2005, class. IPC F41G 5/00, 7/22 / 3 /.

Thus, the use of the proposed test method for aircraft with a telemetric registration system for the main parameters and a device for its implementation allows the RPE to provide reliable uninterrupted communication with the aircraft on the entire flight path and stable reception of telemetric information from the aircraft at long flight ranges and complex path profiles, increase the accuracy and reliability of the test results of the aircraft and the analysis of the functioning of the aircraft blocks.

Claims (1)

A test system for aircraft with a telemetric registration system for the main parameters, containing functional blocks installed on the aircraft, control equipment, an onboard telemetry transmitting module (BTMP) with an antenna, and in the ground equipment of a telemetry recording system - a ground receiving station with an antenna, while the inputs of the BTMP are connected with outputs of functional blocks and control equipment, characterized in that the ground-based equipment of the telemetric registration system is provided in series with control panel, a calculator and a guidance drive, the output of which is connected to the antenna of the NPP, while the second input of the calculator at the time of launching the aircraft in parallel with the aircraft is connected to the second output of the control panel.