RU102823U1 - COMPREHENSIVE TRAINING DEVICE - Google Patents

Abstract

 A comprehensive training device containing a model of an onboard complex control system, a model of sensors, a descent control knob, a model of a motion control system, a model of an executive system, a control and training control panel, an image of the Earth and the ISS station, an astronaut sighting simulator, an orientation control knob, a handle motion control, centrifuge control panel, centrifuge control system, centrifuge cabin, spacecraft motion model, astronaut’s console, the first output of which connected to the fourth input of the training control and management panel, the fifth output of which is connected to the second input of the spacecraft motion model, the fifth output of which is connected to the first input of the sensor model, the third output of which is connected to the seventh input of the model of the motion control system, the first input of which is connected to the sixth output of the control and control panel, the third output of which is connected to the first input of the onboard complex control system model, the third output of which is connected to the third input of the astronaut’s panel, and the second output of the model of the onboard complex control system is connected in parallel with the second input of the sensor model, with the second input of the model of executive bodies and with the second input of the model of the motion control system, the third output of which is connected to the first input of the model of executive bodies, the third output of which is connected to the first input of the model the motion of the spacecraft, the third output of which is connected to the input of the Earth's image generator and the ISS station, the output of which is connected to the input of the cosmonaut’s simulator, the output of which

Description

The utility model relates to the field of space technology and can be used on simulators of manned spacecraft (PKA), equipped with electronic display systems and optical surveillance equipment.

Given the complexity of the crew’s space flight under the ISS program and, accordingly, the crew training program under this program, it is necessary to train astronauts on simulators with high technical characteristics and functionality, with a high degree of compliance with real space flight.

Closest to the utility model is the "Comprehensive learning device", described as a utility model - Patent No. 81361 of 03/10/2009, Authors: Suvorov AP, Terekhov VV and etc.

Integrated training device - Patent No. 81361 allows for comprehensive training of astronauts: phased, including the stages of initial training, pre-training and final stages, when the conditions of a full, so-called through space flight are reproduced, starting from the launch, with the physical effect of overload on the astronaut; flight in orbit with the implementation of controlled modes of orientation, approach, approach, docking and undocking under conditions of physical impact of zero gravity, and descent from orbit with the physical effect of overload. However, this comprehensive training device, which contains mathematical models of standard algorithms for on-board computers, does not provide complete and accurate reproduction of flight operations, taking into account emergency (emergency) situations performed by the crew under the ISS program.

The purpose of the proposed utility model is to provide the most complete and high-quality training of astronauts on a comprehensive training device, at all stages of a manned space flight: launch, orbital flight with the implementation of controlled modes of orientation, approach, approach, docking and undocking, descent, taking into account emergency (emergency ) situations; with imitation of real physical effects on the astronaut in all of these space flight sites.

This goal is achieved by the fact that to the closest to the complex teaching device, it contains an enlarged astronaut’s remote control, an onboard complex control system model, a sensor model, a spacecraft’s motion model, a launch control stick (RUS), a motion control system model, and an executive system model, a control and training control panel, an image generator of the Earth and the ISS station, a simulator of a special astronaut's visor (VSC), an orientation control knob (OBM), a motion control knob ( ORE), a centrifuge control panel, a centrifuge control system, a centrifuge booth “A”, are additionally introduced, an on-board central computer, an on-board computer for descent, a multiplex communication channel, a communication device with the computer, and a simulator of matching devices.

Figure 1 presents the structural diagram of a utility model. Figure 1 marked:

1 - astronaut's console;

2 - model of the onboard complex control system;

3 - model of the motion of the spacecraft;

4 - model of sensors;

5 - trigger control knob (RUS);

6 - model of a motion control system;

7 - model of executive bodies;

8 - remote control and management training.

9 - orientation control knob (CBR);

10 - image generator of the Earth and the station M K S;

11 - simulator of a special astronaut’s visor (VSK);

12 - motion control knob (RUD);

13 - control panel centrifuge;

14 - centrifuge control system;

15 - cab "A" of the centrifuge;

16 - on-board central computer;

17 - airborne descent calculator;

18 - multiplexed information exchange channel;

19 - communication device with a computer;

20 - simulator matching devices.

The utility model includes an astronaut’s remote control 1, the first output of which is connected to the fourth input of the training control and management console 8, whose fifth output is connected to the second input of the spacecraft’s motion model 3, the fifth output of which is connected to the first input of the sensor model 4, the third output of which is connected to the seventh input of the model of the traffic control system 6, the first input of which is connected to the sixth output of the control and control panel 8, the third output of which is connected to the first input of the model of the control system on-board complex ohm 2, the third output of which is connected to the third input of the astronaut's console 1, and the second output of the model of the onboard complex control system 2 is connected in parallel with the second input of the sensor model 4, with the second input of the model of executive bodies 7 and with the second input of the model of the motion control system 6, the third the output of which is connected to the first input of the model of executive bodies 7, the third output of which is connected to the first input of the motion model of the spacecraft 3, the third output of which is connected to the input of the Earth image generator and the MK station 10, the output of which is connected to the input of the special cosmonaut's visor simulator (VSK) 11, the output of which is connected to the fourth input of the cockpit “A” of the centrifuge 15, the second output of which is connected to the second input of the training control and management console 8, the first output of which is connected to the remote control input control centrifuge 13, the output of which is connected to the first input of the control system of the centrifuge 14, the third output of which is connected to the first input of the cab "A" of the centrifuge 15, and the second input of the control system of the centrifuge 14 is connected to the fourth output of the mode and the motion of the spacecraft 3, and the orientation control knob (RUO) 9 is connected to the sixth input of the model of the motion control system 6, the fifth input of which is connected to the launch control knob (RUS) 5, and the motion control knob (ORE) 12 is connected to the fourth input of the model motion control system 6, the eighth output of which is connected in parallel with the third input of the onboard central computer 16 and with the input of the onboard computer of the descent 17, the output of which is connected to the fourth input of the multiplex communication channel 18, t the first output of which is connected to the second input of the astronaut’s console 1, the fourth output of which is connected to the third input of the cockpit “A” of the centrifuge 15, the eighth output of the control and training control panel 8 is connected to the input of the communication device with the computer 19, the output of which is connected to the first input of the onboard central calculator 16, the second output of which is connected to the second input of the multiplex channel of information exchange 18, the first input of which is connected through the simulator of matching devices 20 to the seventh output of the control and control panel 8 , the third output of which is connected to the first input of the on-board complex control system model 2.

- The multiplex information exchange channel (MKIO) 18 serves as the main communication channel of the simulator computer system with the on-board central computer (BCV), with the on-board descent computer (BVS), the astronaut’s console (PC), and the MKIO is the communication channel of the on-board central computer, on-board descent calculator with remote control of astronauts (PC). The main characteristics of the multiplex channel of information exchange are reflected in the structure of the channel, the organization of the exchange of information, the information transmission line, the organization of transmission control. Multiplex channel of information exchange provides:

- receiving information from subscribers via external interfaces;

- processing the received information according to the program laid down;

- the issuance of the resulting information to subscribers via external interfaces.

The exchange of information in the ICIP is carried out by means of program control of information flows with time division in the form of a “circular” transmission. The method of exchanging information is asynchronous. In the "circular" transmission of information, the source simultaneously transmits the same information to several receivers. The address of the product when exchanging information on the ICIP is set programmatically.

The ICIE includes: a controller, terminal devices, a data transmission trunk line.

The exchange of information on the ICIE is carried out in the "controller" and "terminal device" modes.

The controller performs the following main functions: managing the exchange of information, interfacing with the information transmission line, monitoring the transmission of information, the status of terminal devices and self-monitoring.

The terminal device receives and executes controller commands addressed to it, carries out interfacing of the on-board equipment with the information transmission line, monitors the transmitted information, self-checks and transfers the control results to the controller.

Messages include command, information and response words.

- Scheme of inclusion MKIO in the simulator is shown in figure 2.

The onboard central computer 16, which contains standard software, simulates the control system of a transport ship in flight in orbit, including the following modes: orientation, approach, approach, docking with the ISS station, undocking of the transport ship from the ISS orbital station.

- The on-board central computer, based on the given initial conditions (state vector), received through the channel of the command-relay line simulator, calculates (integrates nonlinear differential equations) the predicted position of the spacecraft, and also controls the spacecraft in automatic mode according to the established standard algorithms in the on-board central computer. To execute the descent mode in the on-board central calculator, the control settings are calculated and then transferred to the on-board descent calculator. The on-board central computer generates control information on the astronaut’s console for monitoring by the astronauts in the form of the formats “ORIENT”, “APPROXIMATION”, “MERCHAGE”, “DOCKING”, “INTERCONNECTION”.

An analytical description of the on-board program of the orbital flight control system, including orientation, approach, approach, docking and undocking modes, corresponding to standard algorithms, is presented in the form of sets consisting of three elements [4]:

T = <X, Y, S>

Where: X - the set of input parameters of the calculator aggregates

X = Y X, here N is the number of units in the model of a digital computer.

Y is the set of output parameters of the aggregates of the model of the computer

Y = Y Y;

S is a map of the form S: X → Y, called the conjugation operator, which associates with each input parameter X of aggregate A some output parameter Y of aggregate A, associated with it by an elementary channel

.

The mathematical description of the aggregate model is presented in the form of the following expression:

P = {X, Y, D, U, R (D), F (R), N};

where X, Y is the set of input and output parameters of the unit,

D = {D, D, D} is the set of intermediate parameters,

U = {U, U, U} - the set of data characteristics (features),

R (D) = {R (D), R (D), ... R (D)} is the set of relations on the set of elementary data (features),

N = {N, N, ... N} - the set of data copies (features) in the relationship,

F (R) = {F (R), F (R), ... F (R)} is the set of functional dependencies between relations.

The characteristic of elementary data (features) of the structure can be specified by a tuple of the form U = (<view type>, <range of change>, <value>). The transition of the unit from one state to another is determined by the arrival of input signals, the end of the performed operation of the transformation of data structures and the type of event that occurred at the end of the operation.

The connection of the onboard central computer with the simulator computing system, where the simulator software is implemented: the spacecraft’s motion model, the vehicle’s onboard systems model, propulsion system model, sensors model, visualization system is carried out through the interface devices (USO) via MKIO-USO line -Ethernet according to the protocol of information exchange of the Ministry of Defense of BCV with the MO of the simulator.

The onboard central computer with the astronaut’s remote control and the onboard descent computer are connected via a simulator of matching devices via the multiplex channel of the information exchange using the information exchange protocols MO BTsV with MO PK and MO BTsV with MO BVS.

The composition of the onboard central computer includes (figure 3):

- central processor;

- code exchange device;

- device for receiving and issuing relay commands;

- bus intermodule exchange (Q-Bus);

- device of a secondary power source.

The on-board descent computer 17, which contains the standard on-board mathematical software, simulates on the simulator the automatic control of the descent of a transport spacecraft from orbit to Earth. The on-board descent calculator software includes: software component “current forecast of the descent vehicle motion parameters”; software component "dynamic control settings"; software component "automatic control of the descent vehicle"; software component of "ballistic and navigation support"; software component “forming information for the astronaut’s console of formats”: “BNO” (“ballistic and navigation support”), “SUS”, “RUS”, “AUS”, “BVS / TRANSIT”.

The onboard descent computer is connected with the astronaut’s console and with the central onboard computer via a simulator of matching devices via the multiplex channel of the information exchange using the information exchange protocol MO BVS with MO PK and MO BVS with MO BVC ..

The connection of the onboard descent computer with the simulator computer system, which implements the descent vehicle motion model, the propulsion system operation model, the linear acceleration meters block model, is carried out via the Ethernet interface unit.

The communication device with the computer 19 provides the exchange of information between the control and management of training and the central on-board computer. The device performs the task of controlling the central on-board computer, in particular, it sets the initial conditions for performing computational operations in the central on-board computer, and also provides the technological operations necessary for training on the dynamic simulator of controlled descent. Through the communication device with the on-board central computer, the internal parameters of the BCV are controlled and the algorithms of the BCV are modernized.

A simulator of matching devices 20 provides the exchange of information between the central on-board computer and the astronaut’s desk, between the on-board descent computer and the astronaut’s desk, as well as between the on-board computers. A simulator of matching devices performs structuring, translation into appropriate formats and scaling of the parameters of the spacecraft arriving at the astronaut’s console from on-board computers.

A comprehensive training device based on the TsF-18 centrifuge was put into operation in 2007 at the FSBI NII TsPK named after Yu.A. Gagarin and is currently training and preparing cosmonauts and crews under the ISS international program.

Information sources.

1. Patent No. 81361 of the Russian Federation 7 MKI: G09В 9 \ 16 2009 Integrated training device.

2. Patent No. 2254617 of the Russian Federation 7 MKI: G09В 9 \ 16 2005. Dynamic simulator. BIPM No. 17. 2005 year

3. Fundamentals of the theory of spacecraft flight. Edited by G.S. Narimanov, M. Mechanical Engineering. 1972

4. Training complexes and exercise machines. Development technologies and operating experience. Edited by V.E. Shukshunova, M. Mechanical Engineering. 2005 year

Claims (1)

A comprehensive training device containing a model of an onboard complex control system, a model of sensors, a descent control knob, a model of a motion control system, a model of an executive system, a control and training control panel, an image of the Earth and the ISS station, an astronaut sighting simulator, an orientation control knob, a handle motion control, centrifuge control panel, centrifuge control system, centrifuge cabin, spacecraft motion model, astronaut’s console, the first output of which connected to the fourth input of the training control and management panel, the fifth output of which is connected to the second input of the spacecraft motion model, the fifth output of which is connected to the first input of the sensor model, the third output of which is connected to the seventh input of the model of the motion control system, the first input of which is connected to the sixth output of the control and control panel, the third output of which is connected to the first input of the onboard complex control system model, the third output of which is connected to the third input of the astronaut’s panel, and the second output of the model of the onboard complex control system is connected in parallel with the second input of the sensor model, with the second input of the model of executive bodies and with the second input of the model of the motion control system, the third output of which is connected to the first input of the model of executive bodies, the third output of which is connected to the first input of the model the motion of the spacecraft, the third output of which is connected to the input of the Earth's image generator and the ISS station, the output of which is connected to the input of the cosmonaut’s simulator, the output of which connected to the fourth input of the centrifuge cabin, the second output of which is connected to the second input of the control and training control panel, the first output of which is connected to the input of the centrifuge control panel, the output of which is connected to the first input of the centrifuge control system, the third output of which is connected to the first input of the centrifuge cabin, the third input of which is connected to the fourth output of the astronaut’s console, and the second input of the centrifuge control system is connected to the fourth output of the spacecraft’s motion model, and the control knob orientation is connected to the sixth input of the model of the motion control system, the fifth input of which is connected to the shutter control knob, and the motion control knob is connected to the fourth input of the motion control system model, characterized in that an onboard trip computer, a multiplex information exchange channel, and a communication device are additionally introduced with a computer, matching devices simulator, on-board central computer, the third input of which is connected in parallel with the eighth output of the control system model and with the input of the on-board descent computer, the output of which is connected to the fourth input of the multiplex information exchange channel, the third output of which is connected to the second input of the astronaut’s console, and the first input of the multiplex information exchange channel is connected to the output of the matching device simulator, the input of which is connected to the seventh output of the console control and management of training, the eighth output of which is connected to the input of a communication device with a computer, the output of which is connected to the first input of the onboard central o calculator, the second output of which is connected to the second input of the multiplex channel of information exchange.