Interregional Public Organisation
MICROSPUTNIK
APPROVED
G.M. Tamkovich
Manager of Research and Educational
Microsatellite Program,
IPO Microsputnik,
Chairman of Board,
Doctor of Science (Engineering)
EXPRESS-REPORT
on Results of the
Russian/Australian Research and Educational Microsatellite Kolibri-2000 Mission
Moscow
2002
TABLE OF
CONTENTS
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INTRODUCTION |
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1.
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ABOUT MAIN OBJECTIVES OF THE RESEARCH AND EDUCATIONAL
MICROSATELLITE PROGRAM AND TASKS OF MICROSATELLITE KOLIBRI-2000 MISSION |
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2.
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BASIC RESULTS OF PRE-FLIGHT AUTONOMOUS AND INTEGRATED
TESTS, AND PRELAUNCH PREPARATION AT COSMODROME |
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3.
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MICROSATELLITE INTEGRATION ACCORDING TO INTERNATIONAL
LEGAL STANDARDS OF THE INTERNATIONAL SPACE STATION |
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4.
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SPACE EXPERIMENT TO SUPPORT MICROSATELLITE LAUNCH |
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5.
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CONTROL OF MICROSATELLITE AUTONOMOUS FLIGHT |
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6.
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BASIC RESULTS OF MICROSATELLITE FLIGHT-DESIGN TESTS |
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7.
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BASIC RESULTS OF THE EDICATIONAL PROGRAM |
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8.
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BASIC RESULTS OF RESEARCH PROGRAM |
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9.
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REVEALED PROBLEMS AND THEIR SOLUTIONS |
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10.
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NEAR-TERM PROSPECTS OF PROGRAM DEVELOPMENT |
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INTRODUCTION
1. Mass – 20.5 kg, including
2. Power capacity of solar arrays (0.5 m2) is 30-60 W;
3. Single-axis attitude control system is no less that + 10î;
4. Radio link of 145/435 ÌHz.
1. ABOUT MAIN OBJECTIVES OF THE RESEARCH AND EDUCATIONAL MICROSATELLITE
PROGRAM AND TASKS OF MICROSATELLITE KOLIBRI-2000 MISSION
The implementation of the Russian/Australian school space project
pointed to the necessity from the very beginning to identify the main project
objectives and tasks, features and contents of project components, which would
meet up to date requirements in terms of relevance and available capabilities.
It was concluded that the Russian/Australian school space project should be
research and educational by its nature and should become not the only but the
first one in the Research and Educational Microsatellite program.
The Research and Educational Microsatellite Program is
a fundamentally new trend of space programs, the main emphasis of which is
placed on the integrated conceptual development of research and technological
creative work of high-school children and students. Cosmonautics is one of the
rare area of activity, where each person can find a sphere to apply his own
abilities. Through acquisition of knowledge and experience, specific work
allows him to have a gradual improvement of his abilities and become a
high-professional specialist in the chosen research area.
The state-of-the-art of the research and technological
progress makes it possible to adapt the issues related to satellite development
and operation, as well as its control and data acquisition processes to the
educational programs. Therefore, the formation of the Research and Educational
Microsatellite Program is not only reasonable, but rather relevant for the
present day.
Cosmonautics is in intensive progress, and today it is
hard to image the mankind evolution without using the space activity results. A
great advance in the development of microelectronics, mass application of
microprocessors, spread of space technologies, availability of space system
elements gave rise to possible solution of a wide range of urgent tasks by
using microsatellites. They are widely used in satellite communication, remote
sensing, space physics and technology, education, etc. Microsatellites can be
developed by small teams and within a short period of time.
The Research and Educational Microsatellite Program is very important
and useful for the cosmonautics itself. Space exploration will be more
efficient, if highly educated specialists interested in space science and
technology are engaged in it. Education is a more effective way of brining this
understanding home to a person, therefore, his initiation to space should start
at school. The implementation of a long-term Research and Educational
Microsatellite Program aimed at realization of space projects incorporating
development and launch of microsatellites and deployment of ground control,
data receiving and processing complexes, which will aid in efficient solution
of a wide range of scientific, technological and educational tasks, should
become a part of this initiation.
The Research and Educational Microsatellite Program offers a simple open
access to scientific and telemetry information received from the satellite.
The Program incorporates the implementation of several projects and
foresees a launch of five microsatellites within five-seven years. In so doing,
the Russian/Australian research and educational Project Kolibri-2000 is the
first project in the frame of the Program (Kolibri-1), and microsatellite
Kolibri-2000 is a basic model in structure, service systems, way of launch and
interaction with the ground control, data receiving and processing stations.
The satellite structure and service systems, as well
as principle of its operation in general should have no sophisticated elements,
but should meet high modern requirements for satellites of a similar class.
The ground control complex and school data receiving
and processing stations should be built on a basis of transceivers widely used
in radio amateur complexes, and universally used personal computers. Separate
software fragments can be developed by schoolchildren and students involved in
the program. At the same time the microsatellite program cannot be simplified,
because one of its main objectives is to gradually extend abilities of
schoolchildren.
A complex of microsatellite research hardware should
be selected based on the same criteria. On the one hand, the hardware should be
small-sized and simple, but on the other hand, it should make it possible to
receive real relevant scientific data, process and interpret it.
In addition, the development and operational cost of
the microsatellite and relevant ground station, as well as the launch cost
should be minimized in order to be consistent with the cost for the educational
programs.
The first mission under the microsatellite Kolibri-2000 Program was
essentially aimed at verification of these conceptual program fundamentals in a
real flight and performance of flight tests of the basic microsatellite model.
A complex of the research microsatellite Kolibri-2000
hardware generally meets the specified requirements, provides valuable
scientific data compatible with the information of other satellites. Scientific
equipment for subsequent satellites of this series can be built on a basis of
the scientific instruments of microsatellite Kolibri-2000 complex.
The chosen technique of launching the satellite from the
Progress transport cargo vehicle providing logistics support to the
International Space Station not only allowed to solve the task in a reliable
and low-price way, but laid the basis for the microsatellite integration
according to the International legal standards. This factor is significant not
just as a potential start for further satellites of this series, but also as a
means of attraction of the partners participating in the Space Station
development, assembly and operation, and, through them, of a wide world
community to the Program activities.
2. BASIC RESULTS OF PRE-FLIGHT AUTONOMOUS AND
INTEGRATED TESTS, AND PRELAUNCH PREPARATION AT COSMODROME
The microsatellite admission to flight as part of the transport cargo
vehicle and the International Space Station was preceded by a large scope of
activities. The microsatellite passed an expertise and certification as a
separate spacecraft and component of the Russian Segment of the International
Space Station. The prelaunch preparation and preflight autonomous and
integrated tests were performed at the cosmodrome.
The technical expertise of the
Kolibri Project had to solve the following tasks:
·
Outline analysis of design solutions for the
microsatellite as a separate spacecraft;
·
Analysis of mechanical, electrical and thermal
interfaces of the microsatellite and the cargo vehicle;
·
Analysis of the design and ergonomic solutions
taken in development of the transport and launch container and microsatellite,
and used materials;
·
Investigation of interference between the
transport and launch container with the microsatellite and the cargo vehicle;
·
Integration of the microsatellite into the
Russian Segment of the International Space Station;
·
Determination of feasibility of the Kolibri
microsatellite launch as per the proposed concept;
·
Determination of the main areas of the
scientific and engineering studies to support the development of the Research
and Educational Program of microsatellites developed on a basis of
microsatellite Kolibri-2000.
In so doing, the microsatellite and Progress
M1-7 safety-related solutions were subjected to a more thorough expertise.
The expertise was conducted
in the course of:
·
Analysis of the design, engineering and
operational documentation for the transport cargo vehicle and Kolibri microsatellite;
·
Technical consultations with the documentation
developers;
·
Meetings with the Project developers (IKI RAS, SKB ÊP IKI RAS,
NILAKT RÎSÒÎ);
·
Joint participation in ground tests of the
Kolibri microsatellite equipment on dedicated stands provided by SKB ÊP IKI RAS
and on the integrated stand of the checkout and test facility;
·
Mock-up design of the flight transport and
launch container in Progress M1-7 vehicle at the checkout and test facility;
·
Development test of integration of the
transport and launch container with the microsatellite on the docking assembly
of the cargo vehicle during training sessions of the prime and backup crews
(ISS-4) at Yu.A. Gagarin RGNII TsPK with participation of
specialists from SKB ÊP IKI RAN.
To verify the results of the technical expertise of
the Kolibri Project, S.P. Korolev RSC Energia departments issued dedicated
certificates on:
·
Ballistics-related safety of the Kolibri
Project
·
Systems extending and separating the Kolibri
microsatellite;
·
Loads on the Kolibri microsatellite;
·
Design solutions made for the transport and
launch container with the Kolibri microsatellite with regard to their
functionality, safety and reliability;
·
Results of Kolibri microsatellite thermal
control analysis;
·
Safety of the materials used in the transport
and launch container and microsatellite;
·
Power supply system of the Kolibri
microsatellite;
·
Ergonomics;
·
Scientific hardware;
·
Installation of the transport and launch
container with the microsatellite on the cargo vehicle docking assembly ring.
The analysis of conclusions made in the
dedicated project expertise certificates allowed to state that:
·
There are no radical problems, which could
impede the experiment performance, and the vehicle systems parameters as a
whole satisfy the experiment conditions;
·
In terms of the functionality, safety and
reliability assurance, the solutions made in development of the design, systems
and mechanisms of the transport and launch container and microsatellite are
optimal;
·
Proposed trajectory plan for the experiment
performance assures safety of the International Space Station, cargo vehicle
and microsatellite in all mission phases in nominal and off-nominal situations;
·
The scope of studies and their results confirm
the expediency of developing the Research and Educational Microsatellite
Program based on the Kolibri Project.
For the microsatellite certification the
following certificates were issued:
- Certificates for admission to full-scale
tests concerning:
§
Sanitary-hygienic expertise;
§
Fire safety;
§
Radiation safety;
§
Electromagnetic compatibility with equipment of
the cargo vehicle and International Space Station;
- «Certificate of flight experiment safety on the
International Space Station;
As a result
of the activities:
·
Specific experience was acquired in development
of ground technical documentation for all kinds of tests, flight control
documentation for the International Space Station and transport cargo vehicle,
ways of further updating of the microsatellite space experiments documentation
were identified;
·
Stand-alone tests of the onboard systems and
microsatellite as a whole, including joint tests with the transport and launch
container, and as part of Progress M1-7 cargo vehicle were performed;
·
Mounting procedures for installation of the
transport and launch container with microsatellite on the transport cargo
vehicle docking ring were tested, the crew procedures describing appropriate
actions of the International Space Station crew were released, and training of
ISS-4 crew on the full-scale mockup of the transport and launch container was
conducted;
·
Necessary prelaunch preparation operations were
performed at the cosmodrome, including charging of chemical current sources,
integration of the transport and launch container in the cargo compartment,
check of fasteners.
3. MICROSATELLITE INTEGRATION ACCORDING TO
INTERNATIONAL LEGAL STANDARDS OF THE INTERNATIONAL SPACE STATION
·
A plan of organizational and engineering
actions on integration of the microsatellite into the Russian Segment of the
International Space Station was verified in actual practice.
·
The microsatellite structure, scientific
hardware and service equipment (onboard systems, radio equipment, electric
power supplies) were certified.
·
Thorough investigations showed the adequacy of
actions taken to assure the required safety of the International Space Station
and its crew, as well as the consistency of the microsatellite performance with
the requirements for cargoes to be accommodated on the Station.
·
By the results of joint activities with the
International Space Station partners the Flight Safety Certificate for the
satellite as a whole and its separation from Progress M1-7 transport cargo
vehicle mutually agreed with the Partners was produced.
4. SPACE
EXPERIMENT TO SUPPORT MICROSATELLITE LAUNCH
The implementation of the space experiment
incorporated the following major activities related to the microsatellite
flight as part of the Progress M1-7 transport cargo vehicle and International
Space Station:
- Launch of the microsatellite in the cargo
compartment of the transport cargo vehicle into orbit by the Soyuz rocket and
space complex and its delivery to the International Space Station;
- De-installation of the transport and launch
container with microsatellite from the cargo compartment of the Progress M1-7
cargo transport vehicle;
- Accommodation and storage of the transport
and launch container with microsatellite aboard the Russian Segment of the
International Space Station;
- Installation of the transport and launch
container with microsatellite on the Progress M1-7 docking assembly ring;
- Launch of the microsatellite to an
independent orbit through separation from the transport and launch container.
By the results of performed activities the following conclusions can be
made:
·
In the course of the International Space
Station operation an independent spacecraft was first accommodated, stored and
operated on the station as an equipped and ready for operation microsatellite
presenting a sophisticated scientific-engineering instrument with a large number
of potential hazards requiring a dedicated analysis.
·
The concept of separation of the transport
cargo vehicle with the depressurized cargo compartment from the International
Space Station was first tested on the station.
·
Visual tracking of the microsatellite
operations, both regarding the support activities inside the International
Space Station, and during the vehicle separation from the station, and then the
microsatellite separation from the vehicle was successfully provided.
·
A high tech effectiveness of the microsatellite
design in terms of its prelaunch preparation, and a high quality of the crew
procedures were verified. In combination with a high professionalism of ISS-4
crew they allowed to perform all activities with a good quality and within a specified
time.
·
A particular emphasis should be laid on the
efficient and professional work of the ISS-4 crew commander, cosmonaut Yuri
Onufrienko, who personally provided a qualitative and reliable installation of
the transport and launch container on the Progress M1-7 transport cargo vehicle
docking assembly ring.
All of the proceeding is intended to illustrate the prospects of further
activities on development of microsatellites of this type and their full
reliability, as well as the absence of future obstacles put by the
International Space Station partners.
5. CONTROL OF MICROSATELLITE AUTONOMOUS FLIGHT
The microsatellite
autonomous flight was controlled by the Lead Command Station established at
NILAKT ROSTO base in Kaluga. In the injection phase and during the first
communication sessions it was duplicated at SKB KP IKI (Tarusa)
and in the Lead Spacecraft Control Center at ÊÂ ÌÎ
(Krasnoznamensk).
During
the mission of microsatellite Kolibri-2000 the following operations were
performed:
·
Full-scale actual tests of the onboard and
ground control complex were performed. All systems and equipment of the ground
control complex including hardware and software operated normally.
·
After the telemetry information analysis no
failures and malfunctions of the onboard avionics systems were detected.
·
Scheduled interaction with the microsatellite
data receiving stations, including school stations in Russia and aboard was
established.
·
Procedure of data transmission to the
recipients and users according to preliminary requests was tested.
·
The experience of preliminary daily and
detailed session-by-session planning of the microsatellite flight control
activity was verified.
·
Taking into account the environmental changes
(increase of solar activity and respective increase of atmosphere density in
microsatellite flight altitudes), real-time decisions were taken to intensify
the service systems operations (attitude control, satellite thermal control,
power system operation adjustment).
·
School receiving stations, including stations
located in Australia, passed a complete required cycle of thorough testing,
they were essentially prepared for information reception and processing, and
participated in reception of the scientific and housekeeping information from
the microsatellite.
·
By the results of the microsatellite operation
daily reports were generated and distributed. The received scientific and
telemetry information was preliminary processed and distributed.
·
Development tests for pilot operation of the
mobile microsatellite control complex were successfully performed with a ride
of the control team to field conditions to the suburbs of Kaluga.
·
The ground services:
§
worked for 46 days of direct interaction with
the microsatellite;
§
performed 256 communication sessions;
§
received 1495 files of scientific information;
§
received 2076 files of long-term telemetry
information;
§
received 2072 files of telemetry express
information;
§
received 534 files of additional telemetry
information;
§
received 1200 files of microsatellite attitude
information;
·
In interaction with the Australian ground
stations they:
§
received 128 letters from Australian schools
§
sent 168 letters to Australian schools with the
directives, instructions, diagrams, programs, data, and explanations.
The use of the remote satellite
servicing system developed by NILAKT ROSTO within the Project Kolibri-2000
ensured a real-time and flexible command control of the microsatellite,
in-depth and qualitative monitoring of its onboard systems, efficient operation
of the onboard and ground automatic equipment, as well as a wide acquisition,
downlink and presentation of the onboard instrumentation information. The remote
satellite servicing system can be recommended as a basic system for subsequent
projects to be implemented in this area.
·
For Ballistic Support of Microsatellite Flight:
Ballistic tracking of the
Kolibri microsatellite (radio amateur call-sign RS-21) was provided by the
ground control complex of NILAKT ROSTO based on NORAD trajectory data received
via Internet at regular intervals (from 20.03.02 to 04.05.02).
By processing the trajectory data the initial
conditions were identified for ballistic calculations and support of the ground
control complex operation and Navigator program.
Upon reception of new initial conditions, ephemerid
tables were calculated for a four-day interval to plan the satellite activities
and generate the onboard time programs.
1)
For the Lead Control Station in Kaluga the following data was calculated:
· schedule and parameters of ÇÐÂ AES RS-21 for Kaluga,
Moscow standard time;
· schedule and parameters of ÇÐÂ AES RS-21 for Sidney,
Moscow standard time;
· schedule and parameters of ÇÐÂ AES RS-21 for Sidney,
Sidney time;
· data of shadow parts of the orbit of AES RS-21, Moscow standard time;
· data of ascending nodes of orbit of AES RS-21, Moscow standard time.
2)
For school receiving stations in Sidney the following data was
calculated:
· schedule and parameters of ÇÐÂ AES RS-21, Sidney time;
· schedule and parameters of ÇÐÂ AES RS-12/13, Sidney time
(Satellite RS-12/13 was
used as a signal sensor debug the ground complex);
· antenna target designation tables for AES RS-21, Sidney time;
· antenna target designation tables for AES RS-12/13, Sidney time;
· radio link frequency tables for Sidney-AES RS-21 (145 ÌHz),
Sidney time;
· radio link frequency tables for Sidney-AES RS-12/13 (145 ÌHz),
Sidney time;
· initial conditions in AMSAT form;
· initial conditions for Navigator program in Sidney.
3)
For operation monitoring in Moscow the following data was calculated:
· schedule and parameters of ÇÐÂ AES RS-21 for Kaluga,
Moscow standard time;
· schedule and parameters of ÇÐÂ AES RS-21 for Sidney,
Sidney time.
4) For regional Tarusa station
the following data was calculated:
· schedule and parameters of ÇÐÂ AES RS-21 for Tarusa, Moscow
standard time;
· antenna target designation tables for AES RS-21, Moscow standard time;
· radio link frequency tables for Òàrusa-EAS RS-21 (145 ÌHz),
Moscow standard time;
· radio link frequency tables for Òàrusa-EAS RS-12/13 (145 ÌHz),
Moscow standard time.
Moreover, if needed, the route of subsatellite point of AES RS-21 to
plan the satellite devices activation/deactivation time when producing onboard
time programs was calculated.
For specified time intervals the route of the subsatellite point was
calculated in order to track the data of scientific measurements for NIIYaF
MGU.
·
For Specific Communication Sessions:
In the first
microsatellite entry into the communication coverage of the Kaluga ground
control complex its signal was promptly detected, measured and evaluated for
the purpose of utilization. In the next communication session with the
satellite a stable two-way radio communication was established, commands passed
and were executed, telemetry information was received.
In further sessions the functionality of the following onboard systems
and functions were checked:
·
Three-component flux-gate magnetometer
·
Operation of the control unit of the attitude
and stabilization system (ÁÓ ÑÎÑ-1), in different modes
·
Operation and parameters of 145 MHz radio
transmitter,
·
Operation of radio transmitter and 435 MHz
command system
·
Generation and transmission of various types of
information
·
Operation of telemetry systems in different
modes
·
Operation of the electric power system
·
Generation, accumulation and transmission of
the attitude information in different modes
·
Operation of the particle and filed analyzer
·
Generation, accumulation and transmission of
the scientific information in different modes
·
Generation, accumulation and transmission of
the digital information of the particle and field analyzer
·
Operation of the control unit of the attitude
and stabilization system (ÁÓ ÑÎÑ-2) in different modes
·
Operation of communications in simplex modes in
145 MHz and 435 ÌHz ranges
·
Operation of radio systems at increased and
decreased radiation power
·
Operation of communications at different
information exchange rates (uplink and downlink).
·
Operation of the onboard time service, its
setting and correction.
·
Operation of the onboard command line, various
methods of installation of command programs, status check, correction and
complement.
·
Operation of the onboard audible processor and transmission
of voice messages in 145 MHz and 435 ÌHz ranges.
·
Operation of the general-access telemetry
system sending information by Morse telegraph code signals.
6. BASIC RESULTS OF MICROSATELLITE
FLIGHT-DESIGN TESTS
By results of the flight-design tests of
microsatellite Kolibri-2000 the following conclusions can be made:
·
Validity of the fundamental technical solutions
concerning the microsatellite design and major onboard systems was verified.
·
All organizational and technical interfaces
between participants involved in the microsatellite development and operation
were identified and agreed.
·
The microsatellite structure with the transport
and launch container withstood all mechanical loads in the launch phase,
four-month storage conditions on the International Space Station and during
separation of the microsatellite from the transport and launch container
integrated in Progress M1-7 transport cargo vehicle.
·
The feasibility of the technical concept of a
safe and reliable separation of the microsatellite from the transport cargo
vehicle was verified, options of actions in various off-nominal situations were
studied, probability of ONS occurrence was determined. All mechanical nodes of
the transport and launch container and deployment mechanisms of the
antenna-feeder devices, solar arrays, microsatellite gravitational beam
operated normally.
·
The magneto-gravitational attitude system
performed its functions both in microsatellite in-orbit attitude, and in
investigation of dynamic characteristics of the magneto-gravitational attitude
system and microsatellite behavior in low orbits under disturbed atmosphere and
magnetosphere conditions during solar flares on the 17th and 23rd
of April 2002 in various attitude modes (gravitational, aerodynamic and spin-up
around the Z axis).
·
The electric power supply system (solar arrays,
unit of chemical batteries and automatic equipment for optimization of
charge-discharge processes) kept its functionality after a four-month storage
on the International Space Station (without recharging of chemical batteries
onboard the station) and during a 46-day autonomous microsatellite flight
ensured a required level of power supply for all onboard systems. When
performing dynamic operations of the magneto-gravitational attitude system
related to the attitude changes a slight shortfall of electric power was
observed. This can be explained by an off-nominal position of solar arrays
relative to the Sun.
·
New data obtained on the microsatellite
in-flight thermal control displayed (for implemented altitudes and
microsatellite orbit lighting) a definite thermal insulation redundancy. This
point will be taken into consideration in development of further
microsatellites of this series.
·
The full-scale space experiment on
the microsatellite verified the feasibility of the onboard avionics located in a
depressurized container in open space conditions. This approach significantly
improves the mass-dimensional characteristics of the satellite.
·
The functionality of the satellite scientific
hardware and service equipment on the upper boundary of the allowable operating
temperatures was virtually verified. The passive thermal control system
provided a thermal mode of the instruments operation in a range of 55÷65°Ñ, that is slightly
higher as compared to the estimated upper limit (by 5÷15°Ñ). However, the
qualitative ground testing of the avionics and chemical batteries defined their
safe operation in all flight phases.
·
The attitude accuracy definition system consisting
of the flux-gate magnetometer and sun tracker operated normally.
·
The service remote maintenance equipment ÊÀ-DOKAÁ
along with the radio complex provided an efficient interaction of all onboard
instruments throughout the microsatellite mission. The command and telemetry
radio links had a stable operation for data reception and transmission with
Kaluga and Sidney ground control complex and Tarusa telemetry information
receiving station in two high frequency ranges of 145 ÌHz
and 435 ÌHz.
·
The audible processor operated normally with a
good quality of voice messages.
·
Full-scale actual tests of the electric power
supplies were performed. They demonstrated a correct choice of the lifetime of
chemical current sources and power of solar arrays. Cases of implementing
threshold values of electric current were identified, in which the
microsatellite hardware is completely off.
·
Possibilities to significantly increase the
in-flight lifetime of the systems and the duration of the microsatellite flight
were revealed (for example, due to the launch from a higher orbit). This will
provide an additional capability to make measurements by using a set of
scientific hardware.
·
The microsatellite development test base was
developed and tested based on the horizontal and vertical hanging stands. This
base is partially used for residual magnetization tests.
The basic institutions of the educational
program are school of computer technologies Gelios and school of physics and
technology in Obninsk, which are functionally connected with the Institute of
Nuclear Power, as well as Sidney satellite project combining Knox Grammar
School (for boys) and Ravenswood Girls School (for girls).
During preparation for satellite in-orbit operation the schoolchildren
acquired necessary knowledge about the near-earth space, magnetic field of the
Earth, Van Allen belts, microsatellite design and development process. For
processing of data received from microsatellite Kolibri-2000 schoolchildren
developed the Decoder program, which allows to decode the data and present it
in a format suitable for further analysis, i.e. in the format of tables and
charts. For analysis of the satellite in-orbit operation schoolchildren
developed a program, presenting a 3D microsatellite model, rotating around the
magnetic field vector in accordance with the results of measurements of the
field density vector projections in the satellite coordinate system.
In the active microsatellite flight phase regular duty shifts were arranged
at Obninsk school of physics and technology on Wednesdays and Saturdays. The
data received by e-mail was processed by means of the developed programs.
The basic results of the onset of the educational program implementation
are as follows:
· The key conceptual provisions for improvement of compact and mobile
stations for receiving scientific and housekeeping information from the
microsatellite at educational institutions were developed.
· A possibility of on-line establishment of a remote information receiving
station was demonstrated. A communication session from such a mobile station brought
to the suburbs of Kaluga was conducted. Thus, it opens up the way for access to
participation in the space educational program from any place.
8. BASIC RESULTS OF RESEARCH PROGRAM
The magnetic and electrical fields of the Earth at
altitudes of 200-400 km have not been virtually investigated during the last
few tens of years. Thus, the Kolibri microsatellite mission made a fresh start
in the area of geomagnetic observations in the new millennium. The measurements
made during the microsatellite flight are unique in that the flight time
coincided with the period of high solar activity and increased atmosphere
density, respectively.
The research program has been implemented by using
scientific hardware including the following instruments:
1. Three-component flux-gate magnetometer measuring the magnetic intensity
by three orthogonal components in a range of +/- 64000 nT and its
fluctuations caused by magnetic storms, as well as spectral fluctuation density
in a frequency band of 50-60 Hz in one component. The three-component
flux-gate magnetometer is also used by the onboard attitude system providing
compensation of the microsatellite oscillations;
2. Particle and filed analyzer measuring:
à)
Particles:
-
electrons with energies of more than 100 KeV (in two directions, i.e. zenith
and nadir);
more than 300 KeV; >600 KeV;
-
protons with energy of more than 50ÌeV;
-
neutrons of 0.1 eV – 1.0 ÌeV;
-
Gamma radiation with energies >300
KeV and >2 ÌeV.
á)
Electric field:
- induced
quasi-static field in a range of +/- 2560 ìV/ì;
-
spectral fluctuation density in a frequency band of 50-60 Hz in one component.
When activated, instruments of the scientific hardware
as a whole, hardware detector and electronic units (mainly built of
home-manufactured components) operated normally in open space (without a
pressurized container) and temperature conditions close to the limit allowable
in operation.
The in-flight data preprocessing and physical
interpretation demonstrated the following:
·
Measures to provide a high electromagnetic
cleanness, which were taken during the microsatellite development and testing,
were fully verified in flight, that allowed to measure magnetic and electric
fields in respective ranges of the scientific hardware with a sensitivity
exceeding the levels reached in some specialized International projects, e.g.
INTERBAL (Russia).
·
New data on fluctuations of the magnetic field
and fluxes of energy particles coming from the Sun and deep space was obtained.
A positive correlation of the fluctuation level of the magnetic and electric
fields with the solar activity was determined, specifically during very high
geomagnetic disturbances observed on the 17th and 23rd of
April 2002.
·
Orbit portions were identified, in which the
fluctuation intensity of the magnetic and electric fields in a range of 50-60
Hz is above the level of 3s, that can indicate that power transmission lines radiation penetrates
through the ionosphere.
·
Radiations similar in nature to geomagnetic
pulsations generated in the ionosphere during magnetic storms and related to
dropout of energy particles recorded by the particle and filed analyzer stand
out in spectra of magnetic field fluctuations with a high frequency resolution
in a range of 0.05-15 Hz.
·
Data obtained on the magnetic field intensity
vector, specifically when the microsatellite attitude and stabilization system
was in an active mode, are unique to a great extent, as it allows to
investigate, with a high time resolution, the dynamics of the attitude and
oscillations of the microsatellite, having a small mass and relatively large
surface area.
·
Possibility to transmit a volume flow of
scientific and telemetry information in radio amateur frequency ranges was
verified in practice.
·
Methods of real-time reception and processing
of scientific information flows from the Lead Command Station through the
Internet computer network were implemented.
·
Techniques of interaction with Obninsk school
of physics and technology team for joint processing of the received scientific
information were tested.
·
Under the physical science experimental program
on the Russian Segment of the International Space Station concurrent
measurements were made on similar equipment in the frame of Scorpio experiment.
·
Preliminary results of the research and
research and educational programs were presented in the reports on the Third
Inter-branch Scientific and Technical Microsatellite Conference at
TsNIIMachinostroinie (Korolev) and VII International Exhibition-Congress “High
Technologies. Innovations. Investments”, that was held in the frame of high
tech week in Saint-Petersburg.
·
The basic results of implementing the research
and educational microsatellite concept, results of the design and development
of microsatellite models, which first fulfilled tasks of system (integrated)
nature in space were reported at symposiums, International conferences and
seminars more than 20 times (complete list of publications and reports will be
presented in the final report in the third quarter of 2002).
9.
REVEALED PROBLEMS AND THEIR SOLUTIONS
·
Research and educational microsatellite
Kolibri-2000 fulfilled the entire mission program despite a relatively short
active lifetime restricted by the required strict performance of nominal
separation of the Progress cargo vehicle and unexpectedly high warming-up of
upper atmosphere layers within this time. The housekeeping telemetry data
received from Kolibri-2000, that was fully processed and analyzed by
specialists, will allow to make necessary updates aimed at improvement of
operational characteristics of Kolibri microsatellites for
research-and-technical and educational programs.
·
Major microsatellite utilization-related
problems were revealed. They are first of all related to a short lifetime of
this satellite (46 days), that is not quite enough to arrange a coordinated
large-scale educational program covering schoolchildren from various regions of
the country and several foreign countries.
·
Major difficulties in the satellite service
systems operation were caused by an increased solar activity and earth
atmosphere conditions, respectively. Thus, the nature made the flight test
tougher. High loads produced by the atmospheric drag in real orbit on the
satellite in different attitudes became an additional verification of the
preliminary studies of the microsatellite geometric characteristics, estimated
definition of acting forces and moments, flight control procedures.
·
Regarding the ground control complex operation,
it is necessary to coordinate the interaction of the data receiving stations,
provide mutually agreed planning of activities with regard to real situation,
as well as improve them in terms of reliability and cost.
·
In the context of the educational program
optimization it is reasonable to consider options of principal increase of
duration of the microsatellite lifetime (increase the initial altitude at the
beginning of operation, provide possibilities to perform one or periodic
reboots of the microsatellite, improve the aerodynamic shape in order to reduce
the atmospheric drag).
·
Economic estimation of the satellite
development and operation cost, real admissible financial and economic
parameters to be introduced into the feasibility study of further
Program-related activities and adequate selection of sources of funds and
sponsors, as well as state support approved all over the world for such
programs will have to be additionally studied.
10. NEAR-TERM PROSPECTS OF
PROGRAM DEVELOPMENT
Regarding the information received within the microsatellite
Kolibri-2000 mission the following conclusions about near-term prospects can be
made:
·
Development and improvement of the
near-earth space investigation programs and solution of the research and
educational tasks by using microsatellites of this class are reasonable from the
scientific and technological point for view, economically beneficial and useful
for education of the younger generation, formation of their scientific and
technical view of the world, strengthening of practical interaction among the
peoples of the world. Thus, the primary need for urgent development of this
area of activities has been demonstrated.
·
The microsatellite operation verified the
possibility of expanding the educational program, including data transmission
through fixed and mobile school and university scientific information receiving
stations. This shall be used in further activities.
·
The satellite structure and onboard systems had
a successful operation in more severe in-flight test conditions. They were
aggravated by a long-duration storage of the microsatellite onboard the Station
and increased solar activity during the satellite autonomous flight. The
microsatellite structure and onboard systems can serve the basis for
development of other satellites of this series.
·
The principle concept of building the ground
control complex for research-and-educational satellites based on the radio
amateur hardware can be considered as validated. The ground complex is suitable
for control of further microsatellites of this series with the assumption that it
will be upgraded, and further activities will be needed to modify separate
elements.
·
The service systems and scientific hardware for
the next microsatellite Kolibri-2 under the Research and Educational Program
will have to be developed proceeding from the requirements for possible
guaranteed work with the educational program users all the year round.
·
The scientific hardware of microsatellite
Kolibri-2 will have to be developed proceeding from maximum simple
interpretation of data received from the microsatellite. In particular,
consideration should be given to transmission of the large-scale earth surface
images, which can be recognized.
·
Based on the above brief recommendations
microsatellite Kolibri-2 can be developed and launched by the end of 2003 with
the involvement of the same cooperation and potential participation of the
countries having experience in similar activities, e.g. the USA, Great Britain,
Germany, Canada, France, etc.
·
The financing of this activity shall be based
on parity contributions of the project participants and state support.