Presentation on Control Systems

ugliestmysticΤεχνίτη Νοημοσύνη και Ρομποτική

14 Νοε 2013 (πριν από 3 χρόνια και 8 μήνες)

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DISTRIBUTION AMONG INDUSTRIES


Space industry


Power industry


Rail transportation


Different industries

CONTROL


SYSTEMS


FOR


INTERCONTINTAL


BALLISTIC

MISSILES

CONTROL

SYSTEMS


FOR


LAUNCH

VEHICLES


GNC

SYSTEM

FOR


LV TO
LAUNCH

SATELLITES AND
SPACECRAFTS


GNC


SYSTEM


FOR


LV TO
LAUNCH



SATELLITES AND SPACECRAFTS


CONTROL


SYSTEM

FOR

DNEPR

LAUNCH

VEHICLE


Dnepr LV features:



it is a middle
-
class LV for space vehicle injection

into the Earth circular and elliptic orbits;


booster ( two stages ) is a part of 15A18 missile

withdrawn from action;



upper ( the third ) stage is a derivative from

warheads delivery stage of 15A18 missile.

New features of upper stage:

-

repeated main engine firing

and new scheme of its operation;

-

additional low
-
powered motive installation

for stage stabilization while coasting;



launch


from silo launch facilities, Baikonour
.


CS Performance
:



LV mission and motion control at phases of pre
-
launch
preparation, launch and space;


vehicle placing into required orbit;


it is derived from CS for 15A18 missile by

means of modification both HW and SW;



combined error of injection comes to:

-

for orbit altitude, km
-

4;

-

for angle of orbit inclination, ang. min
-

2,5;


duration of injection, hours
-

up to 1,0.


CONTROL

SYSTEM


FOR

ROKOT


LAUNCH

VEHICLE


ROKOT LV features:




booster ( two stages ) is a part of 15A35 missile
withdrawn from action;



upper ( the third ) stage is a specific developed one. It
provides repeated main engine firing and controlled
coasting flight:



launch will be made from launch pad, Plesetsk
.





CS Performance:




LV mission and motion control at phases of pre
-
launch
preparation, launch and space vehicle placing into
required orbit;


it is designed for the ROCOT LV specially, with up
-
to
-
date componeuts use;


combined error of injection comes to:

− for orbit altitude, percentage up to 1,0;

− for angle of orbit inclination, ang. min up to 2,5;



duration of injection, hours
-

up to

7,0
.


CYCLONE
-
4 LV features:



it is a middle
-

class LV for space vehicle injection into a near
-
earth circular or elliptic orbits;

its upper, the third, stage is a specific developed one and provides
repeated main engine firing and controlled coasting flight;


it is intended to be launched from an equatorial launch site.


CS Performance:




it provides LV mission and motion control at phases of

pre
-
launch preparation, launch and payload placing into required orbit;



it provides stages equipment check at all phases of LV mounting
and testing;



it is designed with up
-
to
-
date components use;



to improve injection accuracy it is equipped with INS and GPS
based navigation subsystem;



combined error of injection comes to:

-

for orbit altitude, km up to 1,5;

-

for angle of orbit inclination, 2..3 ang. Min;


duration of injection, hours
-

up to 3,5.

CONTROL

SYSTEM


FOR


CYCLONE
-
4

LAUNCH

VEHICLE

CONTROL


SYSTEMS

FOR


SPACEC
RAFT
S

TSELINA family


T
heir orbit altitude

were of 500
-

900 km.

84 ones were launched.

Some of them operate

up to the present
.


19
6
7

-

2005



OCEAN family



Their circular orbits had an
altitude about 500 km.

5 spacecrafts were
launched. Some of them
operate up to the present
.


1970


1984


KOSMOS

family




They were placed into

geostationary orbits and
allowed the imaging of the
Earth surface. System
«
Oko
»
.



1991
-

2008


CONTROL


SYSTEMS

FOR

SPACEC
RAFT
S


ARKON


Spacecraft for Earth
remote sensing.

Apogee
-

2700
-

2900 km.

Perigee
-

1400
-

1600 km.




1997, 2002
-

2003


KORONAS



A
utomatically guided
orbital station for study of
solar activity. It operates
up to the present.




1994

-

2001



COUPON



T
he first component of
space segment for satellite
intercommunications and
data communications
system BANKER.

(geostationary orbit).


1997

CONTROL

SYSTEMS


FOR

MODULES OF STATION
«
MIR
»






«
Kvant
»,

«
Kvant
-
2
»,

«
Kristall
»,




«
Spectr
», «
Priroda
»




Docking with station
«
Mir
»




Delivery of the scientific apparatus,


PLs and propellant




Control of the station
«
Mir
»

motion



Orbits:

Circular

250

-

550
km

PERFORMANCE


DATA


OF

CONTROL


SYSTEM

(CS)

FOR


SUPPLY

SPACECRAFT
-
MODULE

(SSM)

AND


FUNCTIONAL


AND

CARGO

UNIT

(FCU)

Peculiarity:




CS is installed in power unit FCU that is the first
component of the ISS ALPHA;



FCU CS is a modification of basal control system which
was qualified completely during preparation and mission of
modules QUANTUM
-
2, CRYSTAL, SPECTRUM and
NATURE. Development chronology
-
1994…1997.




Performance data of the CS for FCU is in accordance of
those for the SSM. In addition the FCU CS will provide the
specified spatial orientation during docking to FCU of the
rendez
-
vous module NODE1 Unity delivered by re
-
used
spacecraft SHUTTLE as well as the orientation of joint
structure FCU+NODE1 during direct docking of SHUTTLE
the next time;




This CS can be used to construct other components of
the ISS ALPHA. To expand the CS functionality and to
upgrade its performance it can be supplemented with
additional HW and SW. Such modification will provide
combined operation of FCU CS and CS of other ISS
components as well as the operation of ISS different
configurations during its assembling and operation.

ISS: Final configuration

The 1
st

phase of the ISS assembling: FCB
"Zarya" + NODE
-
1 in autonomous flight during
~ 600 days

Phase of the ISS
assembling: FCB
"Zarya" + NODE
-
1
perform docking to
service module «Zvesda»

ISS «ALPHA»

SC name,

date of
launch

Egyptsat
-
1,

17.04.2007

МS
-
2
-
8,

17.08.2011

МS
-
2
-
8М,

2013


Purpose


Remote sensing of


Earth.


Remote sensing of Earth.


Scientific data acquisition


for investigation of space


plasma characteristics.


Remote sensing of Earth.


Testing of ammoniac


propulsion system.


Tasks for
control
system


Building of orbital


orientation. Turns of SC


into required direction.


Control of SC


sub
-
systems hardware


and PL. Processing of


command information.


Building of orbital


orientation. Turns of SC


into required direction.


Control of SC


sub
-
systems hardware and


PL. Processing of


command information.




Building of orbital


orientation. Turns of SC


into required direction with


accuracy, which provides


operation of PL having high


resolution. Control of SC


sub
-
systems hardware and


PL. Processing of command


information.

Control

system units


OBC, angular rate


meter based on


fibre
-
optic gyroscopes,


astro
-
measurement


system, magnetometer,


electromagnetic actuator,


fly
-
wheeled actuator.


OBC, set of angular rate


meters based on
fibre
-
optic


gyroscopes,


astro
-

measurement


system, magnetometer,


multi
-
unit attitude sensor,


electromagnetic actuator,


fly
-
wheeled actuator.


OBC, set of angular rate


meters based on
fibre
-
optic


gyroscopes,
astro
-
system


with 2 optical blocks,


magnetometer,


electromagnetic actuator,


fly
-
wheeled actuator.

Control

systems


of


spacecrafts

for


remote

sensing

of


Earth

Strap
-
down inertial
navigation
system


Purpose:


-

initial alignment of inertial system;


-

definition of LV navigating movement parametres.










Weight ………………32 kg





Autonomous initial alignment
:






azimuth
……………
5
-
7 ang. min






horizon
……………
10
-
15 ang. sec





Accuracy of insertion into a






solnechno
-
synchronous orbit:






height ………………9,5 km





inclination …………12 ang. min

Strap
-
down astroinertial block


The

strap
-
down

astroinertial

block

is

intended

for

measurement

of

spacecraft

angular

movement

parametres

and

calculation

of

instrument

system

co
-
ordinates

orientation


parametres


in


inertial


system


co
-
ordinates
.


Error

of

a

absolute

angular

speed

vector

projection

determination:


-

without

calibration

in

orbital

flight


5,
0

10
-
4

deg/sec;


-

after

calibration

in

orbital

flight


1,0

10
-
4

deg/sec.

Error

of

a attitude

determination


15
ang
. sec;

Innovative
aspects and
main
advantages:


Astrocorrection

allows

to

use

rough

fiber
-
optical

gyroscope

as

a

angular

speed

measuring

instrument

in

strap
-
down

astroinertial

block
.

The

gyroscope

zero

deviation


estimation


in


flight

mode

and

adjustment

mode

is

provided

for

strap
-
down


astroinertial


block


accuracy


increase
.


Areas of
Application:


The


strap
-
down


astroinertial


block

is

used

as

a

structure

of

a

spacecraft

orientation


and


stabilisation

control

system
.

Stage of
development
:


The


device


is


at


a

pre
-
production

model

stage

of

development.

HARTRON MAIN
ACHIEVEMENTS

IN SPACE ACTIVITIES

DURING YEARS OF INDEPENDENCE


1994


SC injection in the frame of program «Koronas»;


1998


launch of functional cargo module


«Zarya»
-

Russian segment of the «
Alpha
» ISS
;


1998


docking of «Zarya» with Shuttle. Formation


of cluster


«Zarya» «NODE
-
1», 600 days of flight with «NODE
-
1»;


1999


start of commercial launches of the
«
Dnepr
»

launch vehicle;


2000


automatic docking of the
«
Zarya
»

module with the
«
Zvezda
»

module ;


2000


start of commercial launches of the
«
Rockot
»

launch vehicle;


2003


launch of the
«
Strela
»

launch vehicle;


2007


injection of the
«
Egyptsat
-
1
»

s
atellite

for Earth remote sensing;


2008


injection of the
KOSMOS
-
2
440 SC for Earth remote sensing;


2009


launch of the
«C
yclone
-
3
»
,
«
Dnepr
»
,
«
Rockot
»

launch vehicles;


2010


first flight testing Strap
-
down inertial navigation system
«
Ros
-
1
»
;


2011


second flight testing Strap
-
down inertial navigation system
«
Ros
-
1
»
,
launch of SC MS
-
2
-
8 (Sich
-
2).

Hartron

offers of cooperation options in space sphere

1. Earth remote sensing from space:

-

design of remote sounding of the Earth satellites orientation and stabilisation


control system;

-

design of satellite onboard data acquisition subscribers software.



2. Satellite navigation:

-

design of SC navigation software.


3. Satellite communication:

-

design of communication satellites orientation and stabilisation control system;


4. Ground infrastructure:

-

design of telemetry information processing software;

-

design of software for the operative control and the analysis SC flight in


command center.


5. Scientific
-
technical researches:

-

increase reliability and autonomy functioning of SC control system methods;

-

design high
-
precision strapdown stellar
-
inertial SC control system;

-

high
-
speed SC with elastic elements control methods.





6. Education of experts:

-

construction of theoretical principles of SC control systems;

-

automated technology design and testing onboard computers of SC control


systems software;

-

technology of optimisation of SC control systems on test stands;

-

onboard and land computer complexes operational systems;

-

principles of SC control in flight.





Hartron

offers of cooperation options in space sphere

Thanks for

attention
!

©
RPE Hartron
-
Arkos
, 20
11

CONTACT


Ukraine, 61070, Kharkov, Akademika Proskury str, 1


Ph.: +38(057) 315
-
01
-
93


Fax: +38(057) 315
-
43
-
49


E
-
mail: arkos@sovam.kharkov.ua


http://arkos.kharkov.ua