RU2729152C2 - Method for multi-loop control of space communication apparatus and system for its implementation - Google Patents

Abstract

FIELD: astronautics.SUBSTANCE: group of inventions relates to method and system of multi-loop control of space communication apparatus (SCA). To control the SCA, selecting controlled parameters, generating primary signals, on the basis of which control signals are generated through the ground control loop and, if necessary, additional control loops. System comprises telemetric sensor, process control loop and actuators, service control loop and autonomous control loop connected in a certain manner.EFFECT: higher efficiency of control of SCA at occurrence on its board of a wide range of high-speed dangerous situations.2 cl, 3 dwg

Description

The invention relates to space technology and can be used to control low-orbit communication spacecraft (KAS) of the "Gonets" type.

Known methods and systems for controlling spacecraft (SC) based on a control loop using telemetry signals for transmission over communication channels, including information sensors, onboard and ground radio transmitters and radio receivers, decoding devices, recording devices (see, for example, RF patent No. 2134488; book "Modern telemetry in theory and practice", Nazarov AV, ed. "Science and technology", St. Petersburg, 2007 p. 27, 181).

The closest analogue, selected as a prototype of the claimed invention, is a method for controlling onboard equipment, implemented in the radio complex of relatively simple communication spacecraft (KAS) "Gonets", including a traditional telemetry system for transmitting digital signals over communication channels (see, for example, patent RF No. 2440677) used in the technological control loop (TCL) of the spacecraft.

TKU for low-orbit KAS communication, is characterized by relative simplicity and high reliability. This loop is based on the telecontrol and control system of the onboard systems of the KAS closed through the ground control complex (GCC). Usually, control operations are carried out once every several days (from 7 to 30 days).

A significant disadvantage of the known methods and control systems of the UAN (in particular the prototype) is the limited efficiency of the UAN control when a wide range of fast-moving hazardous situations occurs on board, which can lead to a decrease in the effectiveness of the targeted use of the UAN or to its loss.

The problem solved by the proposed invention is to increase the efficiency of the UAN control when a wide range of fast-moving dangerous situations occurs on board.

The solution of this problem (in terms of the method) is provided by the fact that the method of multi-loop control of the CAS, which consists in using an additional control loop in the control process of the CAS in the form of a service (1-2 communication sessions on each loop over a service radio link) and autonomous (real-time control time using the onboard control complex). In this case, signals proportional to the speed and acceleration of the primary telemetry signal are sequentially generated, the boundary values of these signals are set. On the basis of the efficiency of signal transmission, additional optimal control loops are determined. When the current values of the signals go beyond the set boundary values or their combination, the optimal control loops are determined, at the output, each of which is generated according to the a priori data, the control signals of the CAS.

In terms of the device, the solution to this problem is provided by the fact that the multi-loop control system of the CAS, including the interconnected telemetry sensor, the technological control loop and actuators, according to the invention, the system additionally contains a service control loop, the input of which is connected to the output of the telemetry sensor, and the outputs -connected to other inputs of the executive devices of the spacecraft and an autonomous control loop consisting of the first and second differentiating circuits connected in series to the output of the telemetry sensor, the outputs of each of which and the output of the telemetry sensor are connected to the inputs of the corresponding logical blocks connected through the decoder to the corresponding inputs of the executive organs of the spacecraft.

The proposed technical solution will allow ensuring the efficiency of the UAN control, necessary for trouble-free operation, in the event of a wide range of fast-moving hazardous situations on board, and increase the efficiency of the targeted use of the UAN.

The essence of the proposed method is disclosed in Fig. 1, according to which:

1. Any particularly important controlled parameter P is set (for example, temperature or pressure in the working compartment, power supply voltage of onboard systems, interference environment, etc.).

2. A primary signal P (t) is formed, proportional to the variable value of this parameter (Fig. 1a).

3. Set the boundary (Fig. 1a) values of the change of this signal (Rdop.v, Rdop.n), which is closed through the NKU technological control loop provide the control process. In this case, for each value of the primary signal, control signals are a priori generated and the CAS is controlled.

4. In addition, the service and autonomous control loops (ACS and ACS) are additionally used.

5. Signals proportional to the speed (Fig. 1b) and acceleration (Fig. 1c) of the primary signal are sequentially generated, the boundary (permissible) values of these signals are set.

6. Based on the permissible values of the signal transit time, additional control loops, optimal in terms of their efficiency, are determined (when the current signal values go beyond the set boundary values or in their totality), at the output of each of which, according to a priori signs, control signals of the CAS are generated (Fig. 1d ).

Thus, depending on the situation on board the CAS, an algorithm is triggered that allows you to quickly select the optimal (in this situation) control loop, which provides the necessary response of the control system to the emerging situation.

The claimed method is implemented by means of the proposed system shown in FIG. 2, where:

Technological control loop

1 - Telemetry sensor of a particularly important parameter (TD).

2 - Telemetry device (TMU).

3 - Ground transmitter (NPRD).

4 - Mission Control Center (MCC).

5 - Onboard receiver (BPRM).

Service control loop

2-1 - Telemetry device (TMU).

3-1 - Ground transmitter (NPRD).

4-1 - System Control Center (NCC).

6 - Onboard receiver (BPRM).

Autonomous control loop

7 - AC actuators (IU).

8 - Differentiating circuit 1 (DS1).

9- Differential circuit 2 (DS2).

10 - Logic block 1 (LB1).

11 - Logic block 2 (LB2).

12 - Logic block 3 (LB3).

13 - Decoder (DS).

FIG. 3 as an example, variants of schemes for the implementation of a logical unit (LU) are presented, where:

10 - LB1

10-1 - Comparator block 1.

10-2 - Comparator block 2.

10-3 - Inverter (NOT circuit).

11 - LB2

11-1 - Comparator block 1.

11-2 - Comparator block 2.

11-3 - Inverter (NOT circuit).

12 - LB3

12-1 - Comparator block 1.

12-2 - Comparator block 2.

12-3 - Inverter (NOT circuit).

The proposed system operates as follows.

The telemetry signal from the TD output (1) is fed to the inputs of TMU (2) TKU and TMU (2-1) ACU, LB1 (10) and, if necessary, to other inputs LB2 (11) and LB3 (12), as well as to input of serially connected DS1 (8) and DS2 (9) ACU.

The output of DS1 (the rate of change of the primary signal) is fed to the input of LB2 (11) and, if necessary, to the second other input of LB3 (12), the input of which is the output of DS2 (acceleration of the change in the primary signal).

When the input signals are exceeded at the inputs of the comparator units 1 and 2 of the LU (10, 11,12) the set permissible thresholds (U), a certain positional signal is formed at the output of each of them, the set of which is fed to the inputs of the DS (13). With negative values of the change in the primary signal, its speeds and accelerations, they are fed through the inverters (10-3, 11-3, 12-3) to the inputs of the second blocks of comparators (10-2, 11-2, 11-3) LU (10 , 11, 12).

Signals from the outputs of TMU (2) through MCC (4), NPRD (3) and BPRM (5) TKU and TMU (2-1) via NCC (4-1), NPRD (3-1) and BPRM (6) SKU are fed to the corresponding inputs of the IU (7) of the spacecraft, to other inputs of which the outputs of the DS (13) are connected.

Differentiating circuits are widely known in the theory of electrical radio circuits. Comparators and inverters are key elements in the theory of radio electronic engineering (see, for example, VI Zubchuk, "Handbook of digital circuitry", Kiev, ed. Technics, 1990, pp. 36, 42, 53). These comparators are triggered when the input signal exceeds the set value at their other input. Inverters reverse the polarity of the input signal. The diode matrix is built according to the traditional scheme of code converters (see, for example, AG Alekseenko. Fundamentals of microcircuitry. Sov radio, 1973, pp. 103-105).

The use of the proposed technical solution will make it possible to ensure the promptness of the UAN control, which is necessary for trouble-free operation, in the event of a wide range of fast-moving hazardous situations on board, and to increase the efficiency of the targeted use of the UAN.

Claims (2)

1. The method of multi-loop control of communication space vehicles, in which a technological control loop is used, a particularly important controlled parameter is selected, a primary signal proportional to the variable value of this parameter is formed, the boundary values of the change in this signal are set, which is carried out by a closed technological control loop through the ground control complex control process, for each value of the primary signal, control signals are a priori generated and the spacecraft is controlled, characterized in that they additionally use the service and autonomous control loops, sequentially generate signals proportional to the speed and acceleration of the primary signal, set the boundary values of these signals, determine additional optimal by the speed of the control loops, when the current values of the signals go beyond the set boundary values or by their combination, the optimal control loops are determined at the output of each of which, according to a priori signs, control signals of the spacecraft are generated. 2. A multi-loop control system for a communication spacecraft, which implements the method according to claim 1, including interconnected telemetry sensor, technological control loop and actuators, characterized in that it additionally contains a service control loop, the input of which is connected to the output of the telemetry sensor, and outputs are connected to other inputs of the spacecraft actuators, and an autonomous control loop consisting of the first and second differentiating circuits connected in series to the output of the telemetry sensor, the outputs of each of which and the output of the telemetry sensor are connected to the inputs of the corresponding logic blocks connected through a decoder to the corresponding inputs executive bodies of the spacecraft.

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