Method for testing airborne vehicles with telemetry system of basic parameter registration and device for its implementation

FIELD: aviation.

SUBSTANCE: in case of the testing method of airborne vehicles (AV) before starting the AV, coordinates of the antenna position of the ground reception centre (GRC) are calculated and entered into the ground equipment of telemetry recording system. Current coordinates are determined during the AV flight. They are included into information packets of telemetry data, that are read off from the functional units of the AV and converted into binary code. Generated data bursts are emitted in the direction of the ground reception centre (GRC). Reception and processing of data transmitted into the GRC in the real time mode are carried out. Direction toward the AV with which the axis of the direction pattern of GRC antenna is combined, is calculated according to the obtained coordinates of AV. Testing system of the AV with telemetry system of the main parameter registration comprises the following units installed on the AV: functional units, control equipment, on-board telemetry transmitting module (OTTM), satellite navigation equipment. Ground equipment of telemetry registration system comprises the GRC with antenna, control panel, computer, guidance drive, connected in a certain way.

EFFECT: stable reception of telemetry data from the board of the airborne vehicle.

2 cl, 1 dwg

 

The proposed group of inventions relates to military technology and can be used in the complexes of the ground development of the aircraft (AC) (guided missiles or projectiles).

Testing of modern aircraft is an expensive process that requires considerable financial, time costs. For evaluation used in the construction of LA technical solutions necessary to obtain accurate and most complete data on the functioning of the LA and its units at all stages of testing LA.

The known method of testing the rocket with a telemetry system for the registration of its main parameters, in which the functional blocks of the rocket is read telemetry information, enters the on-Board telemetry transmitter module (VTPM), which is converted into digital binary code, from which to derive information packets in a binary code of each recorded parameter. During the flight the rocket BTPM emits information packets in a binary code of each recorded parameter. Digital code order comes through BTPN, an antenna system for a radio channel in a surface receiving the item (NPP) ground equipment telemetry system of registration, which is the reception of information, its processing in real-time, patent RF №2373486, publication 2009, 20 but�ber, CL. IPC F42B 15/00 /1/.

When implementing this method using ground-based telemetry equipment registration system containing RPE with an antenna and rocket telemetry system of registration of its main parameters containing function blocks, control apparatus, BTPM, consisting of serially connected analog-to-digital Converter, signal controller and mnogomernogo transmitter is connected via a switching device with antenna BTPM, the inputs of analog-to-digital Converter connected to the outputs of the function blocks of the control equipment, and the control input mnogomernogo the radio transmitter is connected to one of outputs of the control equipment /1/.

Data known method of testing the rocket with a telemetry system for the registration of its main parameters and missile telemetry system of registration of its main parameters provide real-time multi-channel transmission of information about the parameters of the blocks of the rocket in the process of testing and refining. However, when LA at greater range, with a complex profile of the trajectory due to the limited aperture of the antenna RPE does not provide radiowidget LA throughout the trajectory, which leads to significant, several times, smart�increasing the transmission coefficient of the antenna about NLP antenna BTPM. These multiple factors cause a reduction energy take the NCE signal and the distortion of the telemetry data to its complete loss in some sections, the trajectory, and also make it difficult, and sometimes make it impossible for a reasonable analysis of operation of major sides and sites of LA in the process of its flight.

Therefore, the objective of the proposed group of inventions is to eliminate the above disadvantages, namely, the RPE reliable continuous communication with LA throughout the flight trajectory for large ranges of flight and complex profiles, trajectories, stable reception of the telemetry data from onboard LA, RPE, improving the accuracy and reliability of test results LA and analysis of the functioning of the units.

In the method of testing aircraft with telemetry system of registration of the main parameters, including the read function blocks LA telemetry data, convert it into binary code, which form information packets about each of the detected parameter, the radiation information packages in the direction of the terrestrial NPP instrumentation telemetry systems of registration, reception and processing in GMP information in real time, the task is achieved by the fact that before the start of LA is calculated and injected into Naz�mnou equipment telemetry systems for recording the position coordinates of the antenna RPE, and during the flight in the aircraft in real time to determine the current coordinates of LA include in their information packets of the detected parameters to pass in NCE telemetry ground equipment registration system, after receiving and processing the information to calculate the NPP LA direction relative to the position of the antenna RPE, combine the axis of the antenna RPE with a focus on LA.

In the system testing of aircraft with telemetry system of registration of the main parameters, containing mounted on the rocket apparatus control function blocks, BTPM antenna BTPM, the inputs BTPM connected to the outputs of the function blocks of the control equipment, and ground equipment telemetry system of registration - NII antenna research Institute, the task is achieved by the fact that in LA installed satellite navigation equipment and ground equipment telemetry system of registration is provided with series-connected remote control, transmitter and actuator traverse, the output of which is connected with the antenna RPE, the yield of satellite navigation equipment is connected to the input BCPM, and the second input of the transmitter - with the release of the research Institute.

The technical result is ensured by the fact that in the method of testing aircraft � telemetry system of registration of key parameters before the start of LA is calculated and injected into the ground equipment telemetry systems for recording the position coordinates of the antenna RPE, and during the flight in the aircraft in real time to determine the current coordinates of LA include in their information packets of the detected parameters to pass in NCE telemetry ground equipment registration system, after receiving and processing the information to calculate the NPP LA direction relative to the position of the antenna RPE, combine the axis of the antenna RPE with a focus on LA.

To do this in LA installed satellite navigation equipment and ground equipment telemetry system of registration is provided with series-connected remote control, transmitter and actuator traverse, the output of which is connected with the antenna RPE, the yield of satellite navigation equipment is connected to the input BCPM, and the second input of the transmitter output SPE.

The result of all operations is tracking antenna patterns of NPP, which during the flight LA directed to the antenna BTPM that provides prolonged energy supply of radio and stable relationship with LA NCE throughout the trajectory.

This technical solution is illustrated graphic materials.

The drawing schematically shows a block diagram of a system test aircraft with telemetry system of registration of the main parameters, which implements the proposed method ICP�LA cal, where

1 - flying machine;

2 functional blocks;

3 - control equipment;

4 - satellite navigation equipment;

5 - BTPM;

6 - antenna BTPM;

7 - satellites (navigation system);

8 - ground equipment telemetry system of registration;

9 - SPE;

10 - antenna RPE;

11 - motor guidance;

12 - evaluator;

13 - remote control.

Before starting on a given range in the control unit (13) determines the position coordinates of the antenna RPE (10) and injected them into random access memory (RAM) computer (12).

When testing LA on Board with outputs of functional blocks (2) signals that contains information about the basic parameters LA (1), and the control signals of the control equipment (3) arrive at the inputs BTPM (4). Satellite navigation equipment (4), taking cues from the SNA group (7), this time scale determines the coordinates of LA (1), which are also fed to the input of BTPM (5). In block (5) from the control apparatus (3) according to the control algorithm LA telemetric signals from the outputs of the functional blocks (2) and the coordinates of LA from the output of the satellite navigation equipment (4) is converted to binary code and are formed in the information packages of registered parameters, which are radiated by antenna BTPM (6) in the direction of the NCE ().

SPE (9) through the antenna RPE (10) receives signals from aboard LA (1), decrypts the received current coordinates of LA (1), the data about the parameters of the functional blocks (2) and transmits the coordinates of LA (1) in the transmitter (12). For stored in RAM block (12) the coordinates of the position of the antenna RPE (10) and the current coordinates of LA (1) computer (12) calculates the direction of LA relative to the position of the antenna RPE (10). The output of the transmitter (12) is formed is proportional to the given direction of the signal and deliver it to the drive input guidance (11) connected to the antenna RPE (10). Drive guidance (11) on the received signal deploys the antenna RPE (10) so that the axis of the antenna RPE (10) are aligned with the calculated direction to LA (1). The result of all operations is tracking the radiation pattern of the antenna RPE, the axis of which is directed at LA(1).

SPE (9) through the antenna RPE (10) processes the telemetry information about the parameters of the functional blocks (2). The axis of the antenna RPE (10) directed to LA (1) that secures the antenna to work NCE with the Directive gain of close to the maximum, therefore, the stability of communication between the SPE (8) and BTPP (4) throughout the trajectory of LA.

In the proposed device function blocks (2), control equipment (3), BTPM (), antenna BTPM (6), SPE (9), the antenna RPE (10) can be performed, for example, similar to the prototype units III.

Similar to the blocks used in the patent of Russian Federation №2247297, publication 27.02.2005 G., CL IPC F41G 5/00, 7/22 /2/, as satellite navigation equipment (4) can be applied, for example, the device orientation of the GPS system, as a calculator (12) and control unit (13) can be applied, for example, small-sized computers Baguette".

Drive guidance (11) can be performed, for example, as a servo DC drive. L. V. Rabinovich, B. I. Petrov, V. G. Terskov, etc Proektirovanie tracking systems, ed. by L. V. Rabinowitz, M., Mashinostroenie, 1969, p. 86-87, /3/.

Thus, using the proposed method of testing aircraft with telemetry recording system basic settings and device for its implementation allows to provide RPE reliable continuous communication with LA throughout the trajectory and stable reception of the telemetry data from the Board of LA for large ranges of flight and complex profiles, trajectories, to improve the accuracy and reliability of test results LA and analysis of the functioning of the units.

1. Method of testing the aircraft (AC) with a telemetry system for the registration of the main parameters, including the read function blocks LA �telemetrically information convert it into binary code, which form information packets about each of the detected parameter, the radiation information packages in the direction of the surface receiving the item (NPP) ground equipment telemetry system of registration, reception and processing in GMP information in real time, characterized in that before the start of LA is calculated and injected into the ground equipment telemetry systems for recording the position coordinates of the antenna RPE, and during the flight in the aircraft in real time to determine the current coordinates of LA include in their information packets of the detected parameters to pass in NCE ground equipment telemetry system of registration, after receiving and processing the information to calculate the NPP LA direction relative to the position of the antenna RPE, combine the axis of the antenna RPE with a focus on LA.

2. System test aircraft with telemetry system of registration of the main parameters, containing mounted on LA function blocks, control devices, on-Board telemetry transmitter module (BCPM) with aerial and ground telemetry equipment registration system - ground collection point with the antenna, wherein the inputs BTPM are connected to the outputs of functional blocks and devices�tour management, characterized in that in LA installed satellite navigation equipment and ground equipment telemetry system of registration is provided with series-connected remote control, transmitter and actuator traverse, the output of which is connected with the antenna RPE, the yield of satellite navigation equipment is connected to the input BCPM, and the second input of the transmitter output RPE.



 

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