Minimize Chibis-M

Chibis-M Microsatellite Mission

Chibis-M (Chibis means a “lapwing” in Russian, it is the name of a bird of the Vanellus family, the “M” stands for Molniya=Thunderstorm) is a low-cost microsatellite mission of IKI-RAS (Space Research Institute-Russian Academy of Sciences), Moscow, Russia. The partner institutions of the science mission are: SINP (D. V. Skobeltsyn Institute of Nuclear Physics) of the Lomonosov Moscow State University (MSU), Moscow; SRG (Space Research Group) of Eötvös University, Budapest, & BL-Electronics Kft., Solymar, Hungary; and LC-ISR (Lviv Centre-Institute for Space Research) of NANU-NKAU, Lviv, Ukraine. The PI of the Chibis project is Lev Zeleny of IKI.

The objective of the mission is to study the interrelation of the transient plasma-wave processes connected with the manifestation in the ionosphere of solar-magnetosphere-ionosphere-atmosphere connections and the parameters of space weather. The fundamental goal is the search for universal laws governing transformation and dissipation of plasma-wave energy in the magnetosphere-ionosphere system. 1) 2) 3) 4) 5) 6) 7)

Event monitoring of the ULF/VLF spectrum is required to register the EMR (Electromagnetic Radiation) occurring with various types of lightning events and space weather phenomena. In particular, the VLF emissions are closely connected with lightning discharges. The science goals will be achieved with the following coordinated studies:

1) In situ study of the fluctuations of electrical and magnetic fields, the parameters of thermal and epithermal plasma in the ionosphere near the F layer during different helio- and geomagnetic conditions. Identify the generation mechanisms for TLEs (Transient Luminous Events) and TGFs (Terrestrial Gamma-ray Flashes) and advance the physical understanding of the links between TLEs and TGFs.

2) Parallel observations of the geomagnetic and geophysical parameters at ground-based observatories with the time event scales from 10-1 to 10-3 s.

3) Study of the EMR phenomena (spectra of ULF/VLF waves) in different regions of near-earth space by means of the comparative analysis of the EMR measurements carried out simultaneously by different spacecrafts and ground geophysical stations.

It is important to note that the signals recorded by the on-board magnetic-wave complex in KNA “Groza” can be transmitted via telemetry also as waveforms, which makes it possible to conduct precise a posteriori spectral - temporal processing on the Earth. The most efficient methods for their analysis are the simultaneous measurements of the SCD (Spatial Current Density) and the magnetic field fluctuations arising during a wave process.



Recently, a number of fascinating physical effects have been discovered which have changed fundamentally our notions about the lightning discharges in the atmosphere. The satellites COMPTON and RHESSI detected powerful impulses of gamma rays (1017-1018 quanta with energies > 100 keV) coming from the Earth. These impulses were found to be generated 2-3 µs before the main lightning stroke. The short (~1 µs) single discharges resulting in the generation of high-power radio-impulses (> 100 GW) were found in high-altitude (13-20 km) thunderclouds. A wideband electromagnetic emission from these discharges were detected on the ground at distances up to a few thousand km. Ground observations revealed gamma bursts related to the jumps of an electric field typical for the step-wise propagation of the lightning leader.

All these observational effects are possibly caused by a new physical phenomenon known as “runaway electron breakthrough” which was theoretically predicted by Gurevich & Zybin in 2001. Emerging during the breakthrough an avalanche of runaway electrons accelerated up to the relativistic energies produces gamma emission. This type of electric discharge can occur under rather low magnitudes of the atmospheric electric field, but its initiation requires seeding high-energy particles. The seeding high-energy electron can be produced by the cosmic rays. The accelerated motion of lower energy electrons in the thunderstorm electric field produces a powerful burst of radio emissions. Thus, the high altitude discharges in the atmosphere are to be accompanied by powerful splashes of radio, UV, X-ray and gamma ray emissions.

The microsatellite Chibis-M will be equipped with two payload instruments: “Thunderstorm” and “Wave Package”. A special synergy of this project is expected -- because not only the direct observation of lightning, but also the synchronized study of the wave processes which are triggered by the lightning will be carried out in parallel onboard the satellite and at ground support stations. This will give an unprecedented opportunity to monitor the development of the lightning mechanism from its generation until the relaxation in the form of electromagnetic (EM) waves.

Special attention is paid at the ULF-VLF frequency range. These waves play a major role in the interactions in the system “magnetosphere-ionosphere-atmosphere-lithosphere” and their study is essential to monitor them.

The new world of various TLE (Transient Luminous Event) types like red sprites, blue jets, elves, carrot sprites, gigantic jets, etc. -- is illustrated in Figure 1 (Ref. 6).


Figure 1: Artist's rendition of various TLE types in the upper atmosphere (image credit: AGU, S. Nielson, et al.)



Figure 2: Artist's view of the deployed microsatellite Chibis-M (image credit: IKI, Ref. 7)


The Chibis-M spacecraft has been developed by IKI of Moscow. It is of Kolibri-2000 heritage, an educational program with a launch of the Kolibri microsatellite on Nov. 26, 2001 on the Russian transport cargo vehicle Progress M1-7 service flight to the ISS.

The spacecraft is 3-axis stabilized. The ACS (Attitude Control Subsystem), developed by ScanEx RDC of Moscow, has a mass of 2.8 kg and features the following configuration: 8) 9)

• Actuation: Electromagnetic coils, flywheels motors

• Attitude sensing: rate sensors, digital solar sensors, magnetometer.

Several operating modes are being offered by the system. The ACS may be used for orbit inclinations in the range of 45-98.6º for altitude ranges of 400-700 km.


Figure 3: Photo of the ACS (image credit: ScanEx RDC)

ADCS (Attitude Determination and Control Subsystem): Attitude sensing is provided by 5 digital sun sensors, a Honeywell magnetometer (HMR 2300R)and three single-axis angular velocity sensors (ADIS 16130). Actuation is provided by three mutually orthogonal magnetorquers and six reaction wheels. The magnetorquers are used to induce a controllable dipole magnetic moment. The reaction wheels are based on a brushless DC electric motor. The motor forces the wheel to accelerate or stop its rotation which results in the control torque. The torque value may be finely tuned according to the on-board computer commands, the torque direction is controlled by the proper distribution of the wheels rotation rates. The ADCS control unit is the main body of the system, linking sensors and actuators together and providing a feedback for the external control devices. The main tasks for the unit are the information collection and an analysis using attitude determination algorithms; processing attitude information to construct necessary control actions and passing all required information to the actuators in order to implement a torque. The pointing accuracy of the spacecraft is ±0.1-0.2º, while the angular velocity estimated error is 0.05º/s.. 10)

A combined GPS/GLONASS receiver provides the orbit and timing for the spacecraft. In addition, there is a gravity gradient boom for passive stabilization; however, the gravity boom is currently in stowed position, it will be used only as a backup passive stabilization system in case of a fly wheel failure.

Total mass of microsatellite at launch
Scientific payload mass
Service system mass
Construction and temperature control system

34.4 kg
12 kg
18.2 kg
3.3 kg

Mission design life

≥ 2 years

EPS (Electrical Power Subsystem)

50 W (average power supply)

Spacecraft stabilization

3-axis stabilized + passive stabilization of the gravity gradient boom (when needed)


Use of GPS-GLONASS receiver for orbit and time provision

Table 1: Overview of some spacecraft parameters

RF communications: The TT&C data link (referred to as engineering channel) uses the VHF-band (145 MHz) in the uplink and the UHF-band (435 MHz) in the downlink at data rates of 9.6 kbit/s. The S-band (2.2 GHz) is used for the downlink of the payload data at rates of 128 kbit/s (1.2 Mbit/s max). The CCSDS packet telemetry protocol is being used. The on-board storage capacity is 50 Gbit. A volume of ~ 50 MByte/day of science data are being downlinked.


Launch: On Nov. 2, 2011, the Chibis microsatellite arrived at the ISS (International Space Station). It was part of the payload carried by the cargo service vehicle Progress M-13M (Russian ID, or Progress 45 (NASA ID). The Progress M-13M spacecraft lifted off from the Baikonur Cosmodrome in Kazakhstan on Oct. 30, 2011, starting with the 45th unmanned Russian space station resupply mission. The docking of Progress 45 marked the fully successful return of Progress operations to ISS after the loss of Progress 44 in August 2011. Progress 45 delivered 2800 kg of food, fuel and supplies to the space station, including the Chibis-M microsatellite.

The Chibis spacecraft is to be released and deployed on the return flight of Progress into a higher orbit than the one of ISS. After this event, the Progress vehicle will be directed to its predefined destination, namely the Pacific Ocean (Ref.15).

Final orbit of Chibis: Near-circular orbit (not sun-synchronous), altitude = 480 km, inclination = 52º.



Mission status:

• The Chibis-M mission is operating nominally in February 2014. The Chibis-M microsatellite is on orbit as a free-flyer since January 25, 2012. During this time, about 2000 contacts were made with the spacecraft; approximately 300 contact periods were used to download the data of the Groza equipment, totaling ~30 GB. 11)

The map of Figure 4 is derived from data of the RFA (Radio Frequency Analyzer) device onboard the microsatellite "Chibis-M". The points marked on the map represent instrument response characteristic radio emissions of lightning events in the 26-48 MHz range. The highlighted areas with the highest number of events, which are in good agreement with the known regions of high lightning activity, occur primarily in the equatorial latitudes.


Figure 4: “Picture of the month: Map Chibis-M,” IKI, December 16, 2013 (Space Research Institute)

The RFA device data provide not only scientific information, but are also being used as a "trigger" for the other instruments on board the microsatellite: a signal received from the RFA switch in the data recording process from the instruments operating in other range of the electromagnetic radiation. Together, they represent the "bulk" image atmospheric lightning discharge in the visible, ultraviolet, X-ray and gamma-ray and ultra-low frequency range where the manifest magnetic ripple effects of electrical activity in the ionosphere.

• The Chibis-M mission is operating nominally in 2013. 12)

• In the summer of 2012, the Chibis-M is in nominal flight operations.

• Mission operations of the Chibis-M microsatellite are planned to be started in March 2012, after all systems have been tested (Ref. 15).

On January 25, 2012 ,the microsatellite Chibis (lapwing) was successfully deployed from the transportation vehicle Progress M-13M and started its own mission.

• The new orbit parameters are: perigee = 497 km, apogee = 513 km, inclination = 51.6°, period = 94.55 minutes. The telemetry information confirmed that all onboard systems are working. The size of the microsatellite with open solar panels and antenna is 1.2 m x 1 m. 13)

• On January 24, 2012, the Progress M-13M space freighter with the Chibis-M microsatellite undocked from the ISS Pirs docking module as scheduled, in an automated mode. Thereafter, Russian controllers started the propulsion engines and brought Progress M-13M into an orbit of ~ 500 km altitude (including two orbit corrections). The Chibis-M microsatellite was deployed on January 25, 2012 from the space freighter and will remain in orbit for at least four years studying lightnings and thunderstorms in the Earth's atmosphere. 14)

• Progress M-13M is planned to remain docked to the Space Station for nearly three months. It will undock from the Pirs Nadir port in late January 2012 and will raise the Chibis microsatellite to the pre-designed near-circular orbit of 480 km altitude, inclination ~52º. Then Chibis-M will be deployed and will begin its own mission in space. 15)



Sensor complement: (Groza, KNA Groza)




RGD (Roentgen & Gamma ray Detector)

- X-ray energy range: 50-500 keV
- Time resolution: 30 ns
- Duration of cycle: 10-100 ns


DUV (UV Detector)

- Emission wavelength: 300-450 nm
- Time resolution: 30 µs


DPC (Digital Photo Camera)

- Info matrix: 1000 x 1000 pixels, 10 bit
- Frame duration: 0.2 s (107 bit/s)
- Spatial resolution = 300 m


RFA (Radio Frequency Analyzer)

- Dipole electric aerial
- Frequency range: 20-50 MHz
- Dynamic range: 70 dB
- Time resolution: 20 ns


KNA Groza [ULF/VLF Wave Package (WP)]

- E and B sensors in the range of 0.1 Hz - 40 Hz


Data acquisition system

- Operative memory (5-10 cycles): 1..75-3.5 Gbit
- Memory (50 cycles): 17.5 Gbit


Table 2: Overview of scientific instruments


Figure 5: Schematic view of ionospheric perturbations (image credit: LC-ISR)


Scientific payload Groza:

The scientific payload of the Chibis-M, designed for the study of new physical processes at high-altitude atmospheric lightning discharges, includes: 16)

• RGD (X-ray and Gamma-ray Detector) with a 0.02-1.0 MeV energy band

• DUF (Ultraviolet Detector) of radiation with wavelengths from the UV (180-400 nm) to IR (650-800 nm)

• RFA (Radio Frequency Analyzer) in the frequency range 26 - 48 MHz

• CFK (Digital Camera) with a spatial resolution of 300 m and the exposure time of 15 frames/s

• MWC Magnetic Wave Complex) in the frequency range of 1 - 40,000 Hz

• BND (Data Acquisition Unit).

Each instrument of Groza has a ring memory (RM) with a fixed size sufficient to record a few events. The total size of the memory of the instrument is determined by the maximum duration of the event, which is set for each instrument by the PI of the experiment. The duration of the record can be controlled by ground commands. For example, the RFA can provide registration time 50 ms, RGD - 20 ms, DUF - 100 ms. Other digitization parameters also can be set by command from the Earth: the period of sampling (sampling time), the criterion of "event" or trigger of the instrument (Ti), the size of saved memory "before" and "after" the event. Due to the accidental nature of the events, the project is interested in the record in the RM which is connected to the on-board time forming the identity array of the event (header, number, etc.), Figure 6. Only the records matching the Ti criterion are stored in RM. If no event was identified, the next loop of recording is carried out.


Figure 6: Example of production of the trigger complex Tc by the BND instrument (image credit: Chibis-M collaboration)

The logic of the Groza operation is illustrated below in the example of the RGD instrument intended to record sporadic outbursts (bursts) of the hard X-ray and gamma-ray at high-altitude atmospheric discharges. Four gamma-ray scintillators are used, which are based on crystals of NaI(Tl) with a diameter of 5 cm and a thickness of 1.0 and 2.0 cm. In the course of the experiment, the permanent recording of the RGD readings is carried out. The output of the detectors providing the time profile of the burst is digitized with a resolution of less than 100 ns and recorded during a time interval that is set by the internal RM resources (not less than 20 ms) and is further overwritten with the subsequent set of readings. Thus, the RM always keeps the current sequence of digitized detector readings of the last 20 ms. Along with the recording of the digitized signals from each of the 4 detectors, the number of counts (with a signal amplitude exceeding a threshold corresponding to the energy release in the detector 25 keV) is accumulated over the interval of 3 ms and over the interval of 1 s (optionally) prior to the interval of 3 ms. By summing up the counts at each detector channel during 1 s interval prior to 3 ms, one can determine the background level. The excess of counts summed over 3 ms over the background level for a certain number of "sigma" in a predefined number of detectors (the number of "sigma" and the number of detectors are set by ground command, the default value - 3σ for at least two detectors) is a sign of the event.

The Scientific Committee of the project has acknowledged that the best option for lightning strikes registration at the first stage would be such when the Tc is initiated with the Ti of RFA, the latter being the highest sampling speed instrument that measures the intensity of radio emissions in a typical lightning range of 26-48 MHz. The instrument includes a spectrum analyzer with five broadband filters, evenly spaced over the operating range. At the output of each filter a set of threshold elements and the majority scheme of signal enrollment (precision of trigger binding to the board time is 1 µs) are mounted. After the Ti receiving a radio signal over a time period, defined by a ground command, is recorded in the RM, Figure 7. In this case, the moment of the Ti receiving is in the middle of the selected time interval. The Ti can be used by other MS instruments to record likely lightning discharge at the same moment as the RFA in the ultraviolet, infrared, gamma radiation and ELF frequency ranges.

During its operation, the RFA has identified areas of the most intense man-made interference and most promising areas for the registration of lightning activity. The RFA operation schedule is planned now with taking these zones into account. For the past eight months of satellite operation in 2012 several hundred triggers were recorded with more than a hundred of them associated with short and powerful lightning. Figure 7 demonstrates examples of the RFA waveform recordings of lightning discharges possessing different appearances. They show gradual increase of electromagnetic activity ending by a single powerful short radio pulse and subsequent decay of the field, or multiple short discharges, following with an intervals of 50-100 µs during about 1 ms, or increased storm activity during 400 µs without discharges at all.


Figure 7: Examples of different waveforms recorded with the RFA in the equatorial region. The duration of each recording is 3ms (image credit: Chibis-M collaboration)

Chibis-M is able to effectively monitor electromagnetic environment of the Earth at ionospheric altitudes producing simultaneous measurements of electromagnetic emissions in a very broad frequency band from VLF and VHF to X- and gamma-rays. Special technique of trigger formation makes it possible to prevent uncontrollable expanding of the amount of data stored. Recordings of VLF electromagnetic fields conducted by Chibis-M are believed to be relevant to natural processes in the ionosphere and the magnetosphere of Earth, in the first place to lightning activity what was proved with primary analysis of received data (Ref. 16).


KNA Groza (Wave Probe):

The objective of KNA Groza is the study of the process of the development of the stepped leader of high-altitude lightning in high electric fields.

The Wave Probe (WP) device is a combination of three sensors in one module: SLP (Split Langmuir Probe), search-coil magnetometer, and electric probe. The Wave Probe instrument was already successfully tested in the spatial experiment VARIANT onboard the Ukrainian SICH-1M satellite (launch Dec. 4, 2004).

Frequency range for all channels

0.1 - 40,000 Hz

Dynamic range

120 dB

Noise level of measuring channels at 1 kHz

- Electric current density channel: ≤ 10-13 A/cm-2 Hz-1/2
- Magnetic induction channel: ≤ 0.02 pT Hz-1/2
- Electrical potential channel: ≤ 10-6 V Hz-1/2

Current density transformation factor

77 V/mA/cm2

Magnetic induction transformation factor

100 mV/nT

Power consumption

< 0.25 W

Instrument size

- Sensor: 24 mm diameter, x 294 mm
Preamplifier: 136 mm x 43 mm x 28 mm

Instrument mass

- Sensor: 0.225 kg
- Preamplifier: ≤ 0.125 kg

Table 3: Specification of the WP assembly


Figure 8: Overview of ULF/VLF Wave Probe components (image credit: LC-ISR)



Figure 9: Schematic view of the ULF/VLF sensor configuration (image credit: LC-ISR)


Figure 10: Schematic view of the Wave Probe construction (image credit: LC-ISR)


Figure 11: Photo of WP (Wave Probe, left), protection and testing cover (TC, middle), WP with TC (right), image credit: IKI

Event processing:

The PSA (Programmable Signal Analyzer) provides event processing of the payload strobe for the fixation at lightning discharge occurrence of EM radiation generation in the UHF/VLF (2 x 104 to 10-2 Hz) range. The EMR generated in the basic phase of the lightning discharge, called whistles, are recorded in the VLF frequency range. The main task is the measurement of the EM fluctuations in the range of frequencies 0.1Hz - 40 kHz.


Computer No


Sampling speed (max)

Search coil (Bx, By, Bz)


0.1 Hz-40 kHz

100 kHz

Electric VLF (E=E2-E1)


0.1 Hz-40 kHz

100 kHz

Plasma current (I1, I2)


0.1 Hz-40 kHz

100 kHz

Electric ULF (E=E2-E1)


DC-100 Hz

250 Hz

Magnetometer (BMx, BMy, BMz)


DC-100 Hz

25 Hz

Table 4: Overview of PSA-SAS3 (Spectral Analyzer and Sampler- version 3) input signals


Figure 12: Photo of the PSA instrument (image credit: LC-ISR, SRG, IKI)


Figure 13: Block diagram of PSA-SAS3 (image credit: LC-ISR, IKI, SRG)

The magnetic - wave experiment is aimed also at the study of the interrelation of plasma - wave processes in the ionosphere, which take place during the sun - magnetosphere - ionosphere - atmosphere interactions and is of great interest for studying the parameters of space weather. It is expected that the systematic study of these connections will make it possible to find the universal laws, which regulate conversion and dissipation of plasma - wave energy in the magnetosphere - ionosphere system.

The FM (Fluxgate Magnetometer) will be included in the WP. This is a newly developed low mass and low-power but highly sensitive device, especially designed for micro- and nanosatellites. Its parameters are (parameters are specified for all three analogue outputs):

Field measurement range

± 64 000 nT

Transformation factor

64 ± 0.6 (µV/nT)

Frequency range

DC to 10 Hz

Noise level at 1 Hz

≤ 10 pT Hz-1/2

Power consumption

< 0.5 W

Electronic unit dimensions

150 mm x 85 mm x 40 mm

Sensor mass
Electronic unit mass

< 0.1 kg
< 0.5 kg

Table 5: Parameters of the FM device LEMI-012M


Figure 14: Photo of the FM device (image credit: LC-ISR, IKI)

Full frequency band of received signal

1 Hz-20 kHz

Frequency characteristics flat part of pass band

1-20 kHz

Transformation factor

100 mV/nT

Output parameters

- Output voltage (max): ±5 V
- Output resistance: < 100 Ohm
- Loading resistance (min): 5 kOhm
- Short-time short-circuiting protection is available

Magnetic noise level

@ 10 Hz: ≤ 2 pT Hz-1/2
@ 100 Hz: ≤ 0.2 pT Hz-1/2
@ 1 kHz: ≤ 0.03 pT Hz-1/2
@ 10 kHz: ≤ 0.05 pT Hz-1/2
@ 20 kHz: ≤ 0.1 pT Hz-1/2

Power consumption

≤ 25 mW

Temperature range

- Operations mode: ±50ºC
- Switched off mode: -150ºC to 70ºC

Outer dimensions of instrument

Length: 211 mm, diameter: ≤ 25 mm

Table 6: Parameters of the IM (Induction Magnetometer) LEMI-127


Figure 15: Photo of the IM device, LEMI-127 (image credit: IKI)

603Frequency range for all channels

0.1 Hz to 40 kHz

Dynamic range

120 dB

Noise level of measuring channels @ 1 kHz

- Electric current density channel: ≤ 10-13 A cm-2 Hz-1/2
- Magnetic induction channel: ≤ 0.02 pT Hz-1/2
- Electric potential channel: ≤ 10-6 B Hz-1/2

Current density transformation factor

77 V/mA/cm2

Magnetic induction transformation factor

100 mV/nT

Temperature range

± 50ºC

Power consumption

< 0.25 W

Device dimensions

Sensor: 24 mm diameter
Preamplifier: 136 mm x 43 mm x 28 mm

Device mass

Sensor: 0.225 kg
Preamplifier: ≤ 0.125 kg

Table 7: Parameters of the Wave Probe LEMI-603


Figure 16: Photo of the Wave Probe LEMI-603 (image credit: LC-ISR)



Ground segment:

The project uses a few ground stations in Russia. The main station is located in Tarusa (Russia). It provides facilities for both engineering and scientific channels. The spare station for engineering channel is provided in Kaluga (Russia), and a spare station for science data is located in Panska Ves (Czech Republic). 17) 18)


Figure 17: Illustration of the communication links and ground stations in Russia (image credit: IKI)

The nature of the low-cost mission requires that all nodes of the ground segment (stations, processing centers, operations centers, workstations of investigators) are being linked by public internet facilities.

The main node of the ground system is located at IKI of Moscow, providing the functions of MOC (Mission Operations Center) and DPDC (Data Processing and Distribution Center). Other organizations such as telemetry stations, SINP MSU (Skobeltsyn Institute of Nuclear Physics of Moscow State University) and LPI RAN (Lebedev Physical Institute of the Russian Academy of Sciences) interconnect through the main node.


Figure 18: Inter-node communications between the various entities of the mission (image credit: IKI)


Figure 19: The main nodes of the ground segment for the Chibis-M mission (image credit: IKI) 19)

Ground-based observations:

Ground-based observations coordinated with the Chibis-M mission are to be performed by institutions in the following countries:

• Russia (Caucasus observatory, Yakutsk Lightning Monitoring System)

• Europe (Eurosprite network - France, Spain, Hungary, Greece)

• Israel (Tel Aviv University)

• USA (Stanford University, Duke University)

• Brazil (Instituto Nacional de Pesquisas Espacias)

• New Zealand (WWLLN Network)

• India (Institute of Geomagnetism)

• Japan (Hokkaido University)


Theoretical and modeling efforts in support of the data analysis are to be provided by:

• European centers (Eindhoven University, )

• Russian centers (Lebedev Institute of Physics, Institute of the Physics of the Earth, N. Novgorod University).


1) Stanislav Klimov, Denis Novikov, Valeriy Korepanov, Andriy Marussenkov, Csaba Ferencz, Janos Lichtenberger, Laszlo Bodnar, “The Study of Electromagnetic Parameters of Space Weather. Micro-Satellite Chibis-M,” Proceedings of the 7th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, May 4-7, 2009

2) V. N. Angarov, G. K. Garipov, V. M.Gotlib, A V.; Gurevich, S. I. Klimov, V. G. Rodin, S. I. Svertilov, L. M. Zelenyi, “Investigation of new physical phenomena in the atmospheric lightning discharges: Micro-satellite CHIBIS-M,” Proceedings of the 7th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, May 4-7, 2009, IAA-B7-0214P

3) S. I. Klimov, L. M. Zelenyi, D. I. Novikov, Cs. Ferencz, J. Lichtenberger, L. Bodnar, V. E. Korepanov, A. A. Marusenkov, “Electromagnetic Parameters Study for Space Weather Research (Microsatellite “Chibis-M”),” Proceedings of the AGU Chapman Conference on the Effects of Thunderstorms and Lightning in the Upper Atmosphere, Penn State, College Park, PA, USA, May 10-14, 2009

4) L. M. Zelenyi, V. G. Rodin, V. N. Angarov, T. K Breus, M. B. Dobriyan, S. I. Klimov, O. I. Korablev, V. E. Korepanov, V. M. Linkin, E. A. Loupian, N. N. Ivanov, L. E. Lopatento, O. Yu. Sedykh, “Micro-satellite “Chibis” – universal platform for development of methods of space monitoring of potentially dangerous and catastrophic phenomena.,” Proceedings of the 5th International Symposium of the International Academy of Astronautics (IAA), Berlin, Germany, April 4-8, 2005, URL:

5) V. Korepanov, A. Marusenkov, S. Belyayev, S. Klimov, L. Zelenyi, D. Novikov, Cs. Ferencz, J. Lichtenberger, L. Bodnar, “Earth Observation Microsatellite Chibis,” Proceedings of the 60th IAC (International Astronautical Congress), Daejeon, Korea, Oct. 12-16, 2009, IAC-09.B1.1.11

6) V. Pilipenko, “New physical phenomena in the atmospheric lightning discharges: observations from microsatellites and ground,” FP7-SPACE-2010-1, URL:

7) L. M.Zelenyi, S. I.Klimov, A. A.Petrukovich, “International experiments of the Russian Academy of Sciences in the frame of the Space Weather Program,” The Scientific & Technical Subcommittee of the COPUOS (Committee on the Peaceful Uses of Outer Space) 2010, 47th session, Vienna, Austria, February 8-19, 2010, URL:

8) “Microsatellite attitude control system,” ScanEx RDC, URL:

9) Information provided by Stanislav Karpenko of Sputnix LLC, Moscow, Russia

10) M. Yu. Ovchinnikov, D. S. Ivanov, N. A. Ivlev, S. O. Karpenko, D. S. Roldugin, S. S. Tkachev, “Chibis-M Microsatellite ACS Development, Complex Investigation, Laboratory and Flight Testing,” Proceedings of the 9th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, April 8-12, 2013, paper: IAA-B9-1216P

11) The information was provided by Stanislav I. Klimov of IKI (Space Research Institute), Moscow.

12) Igor Afanasyev , “Open source smallsats in Russia,” The Space Review, January 7, 2013, URL:

13) Information letter N2 “Project Chibis” received on January 26, 2012 from Viacheslav Pilipenko of IKI (Space Research Institute), Moscow, URL:[tt_news]=2667&cHash=b5453ccfa30964a8230f766622b7f79d

14) “Progress Space Freighter Undocks from ISS,” Space Travel, Jan. 25. 2012, URL:

15) Information letter “Project Chibis” received on January 17, 2012 from Viacheslav Pilipenko of IKI (Space Research Institute), Moscow

16) S. I. Klimov, V. M. Gotlib., L. M. Zelenyi, V. N. Karedin, V. M. Kozlov, I. V. Kozlov, D. I. Vavilov, M. S. Dolgonosov, G. K. Garipov, S. I. Svertilov, V. V. Bogomolov, I. V. Yashin, V. E. Korepanov, L.Bodnar, Cs. Ferenz, “Algorithm of the formation of high altitude atmospheric lightning trigger testing -Academic microsatellite Chibis-M," Proceedings of the 9th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, April 8-12, 2013, paper:IAA-B9.0501

17) V. Nazarov, R. Nazirov, V. Gotlib, O. Batanov, N. Eismont, V. Karedin, F. Korotkov, A. Ledkov, Ya. Markov, A. Melnik, A. Tretiyakov, A. Popkov, S. Svertilov, “Low-cost ground segment for Russian Academia-University science space missions,” Proceedings of SpaceOps 2012, The 12th International Conference on Space Operations, Stockholm, Sweden, June 11-15, 2012, URL:

18) V. Angarov, N. Eismont, V. Gotlib, V. Kozlov, V. Nazarov, R. Nazirov, V. Rodin, “Ground segment of low budget satellite Chibis,” Proceedings of the 7th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, May 4-7, 2009, IAA-B7-0215P

19) V.Nazarov, R.Nazirov, L.Zelenyi, V.Angarov, O.Batanov, L.Bodnar, N.Eismont, V.Gotlib, V.Karedin, S.Klimov, F.Korotkov, I.Kozlov, A.Ledkov, A.Melnik, A.Papkov, V.Rodin, A.Ryabova, Ya.Shmelauer, A.Tretiakov, “Ground segment and operations for microsatellite Chibis-M: learned lessons, current status and prospective evolutions,” Proceedings of the 9th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, April 8-12, 2013, paper: IAA-B9-0802

The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: ”Observation of the Earth and Its Environment: Survey of Missions and Sensors” (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates.