Annexure - 1

Specifications of MOM-MCC


MCC: Payload Features

Mars Colour Camera (MCC) is a medium resolution Camera, with RGB Bayer pattern detector. It is a `true colour’ camera flown onboard Mars Orbiter Mission. MCC will return images of Mars, its Moons (Phobos & Deimos) and other celestial objects in natural colour.   MCC is designed to meet the following scientific objectives: ‐

  1. To map various morphological features on Mars with varying resolution and scales using the unique elliptical orbit.
  2. To map the geological setting around sites of Methane emission source, if any.
  3. To provide context information for other science payloads.

It is aimed to image the complete Mars disk in very short time. From the proposed orbit of ~300 km x 71,000 km around Mars, the camera will image localized scenes at high spatial resolution as well as provide a synoptic view of the full globe.




Resolution (m)

19.5 @ Periareion

Frame Size (km)

40 x 40 @ Periareion

Full Mars disc from 63000 km to Apoareion


Spectral region

0.4 µm – 0.7 µm R-G-B (Bayer Pattern)

Frame rate

1s (frame selection at 1s, 8s or 15s period by BDH through ground commanding)

Exposure time

Total 16 ground programmable exposures ranging from 34µs to 490ms

Data volume/frame

40 Mb

System MTF

> 22% (@ 46 LP/mm)


> 97 (@ Near Saturation)

Size (mm)

346(L) x 128(W) x 113(H)

Mass (kg)


Power (W)




Annexure – 2


TIS: Payload Features

Thermal Infrared Imaging Spectrometer (TIS) is a plane reflection grating based IR spectrometer with all refractive optical elements. It uses an un-cooled microbolometer detector operating in 7mm to 13mm Infrared wavelength range TIS consists of f/1.4 fore optics lens assembly with a focal length of 75mm and a field of view (FOV) of ±3.18°. A slit is placed at the focal plane of fore optics which is input to the spectrometer. A collimating lens allows the beam to fall on plane reflection grating which then disperses the incident energy into different wavelengths. The dispersed spectrum is then refocused by a focusing optics on 160 x 120 pixels micro-bolometer based area array detector.




258m @ Periareion (@372km)

55 km @ Apoareion (@80000km)


41km x 258 m @ Periareion

8800km x 55km @ Apoareion

Spectral region

7µm – 13µm,  12 bands

Spectral resolution

~500 nm   (12 bands)

Optical smile

< 0.2 pixel

NEDT (Radiometric performance)

< 1K @300K

Data rate

6.56  Mbps


Spectral Binning

Mode 3 (Nominal mode)

10 (12 bands)

Mode1 (Special mode)

No binning (120 bands)





Annexure – 3

MSM: Payload Features


MSM was designed to measure extremely small concentration of methane gas in the planetary atmosphere. It is a differential radiometer based on Fabry-Perot Etalon (FPE) filter which measures solar radiation reflected from planetary surface in the short wave infrared (SWIR) region. An FPE filter transmits light at extremely narrow, well defined spectral bands which are evenly spaced in the frequency domain. FPE filter of MSM is designed in such a way that its transmission peaks coincide with six prominent absorption lines of methane gas in the SWIR region. Since radiation is measured only at absorption line positions rather than over a wide spectral band, MSM is very sensitive to variations in gas concentration. 


To retrieve gas concentration, the radiance measured by the sensor needs to be corrected for ground reflectance and atmospheric scattering. Conventionally, it is done by measuring radiance in a broad reference channel which is away from gaseous absorption bands. Since ground reflectance and atmospheric scattering depends on wavelength, it is not possible to correct the data fully. The new sensor design of MSM innovatively circumvents this problem by making use of another FPE filter in the reference channel with its transmission peaks falling just outside the absorption lines. Therefore methane absorption in reference channel is negligible where as ground reflectance and atmospheric scattering remains same.




Resolution (km)

0.63 @ Periareion ,  135 @ Apoareion

Swath (km)

4.4 @ Periareion,  948 @ Apoareion

Spectral Region (nm)


Integration Time(ms)

0.25, 0.5, 1 and 2 (Selectable )

Quantization (bits)

20 (internally Binned)

Data Rate (Mbps)


Size (mm)

426(L) x 355(W) x 118(H)

Mass (kg)


Power (W)





Annexure – 4

Specifications of MOM-LAP

LAP instrument is developed on the absorption gas cell based photometry technique that operates on the principle of resonant scattering and resonance absorption. It comprises a set of tungsten filaments furnished ultra-pure [99.999 %] hydrogen and deuterium gas cells that serve as narrow-band rejection filters at their hydrogen and deuterium Lyman-a wavelengths, respectively.  The functional specifications of instrument are presented in the following Table. LAP can function in two modes i.e., i) Photometer mode in which the incoming line-of-sight photon flux within the spectral bandwidth [8 nm] of the Lyman alpha filter is measured without activating the filaments in gas cells. This mode of operation is useful to assess the hydrogen distribution as a function of altitude (generation radial profiles) as MOM goes through different layers of the Martian atmosphere. ii) Absorption cell mode in which, filaments of deuterium and hydrogen gas cells are activated in a cyclic manner to record the relative signal contribution, from which the D/H ratio can be estimated employing the calibration and normalization factors derived from ground based experiments. 

Salient Features of LAP instrument



Operational Range

3,000 km – periapsis – 3,000 km

Pointing Direction

Nadir, Limb and Exosphere

Field of View

0.0016 steradians

Dynamic Range

1 - 5 x 107 counts per second


Solar-blind PMT

Gas Cells

Hydrogen, Deuterium

Bandpass Filter

8 nm (Peak l: 122 nm)


0.036 cps/R



LAP On-board Operations around Mars


LAP is operated in the Martian orbit around the best possible sun-lit peri-apsis in order to register the Martian exospheric line-of-sight hydrogen and deuterium Lyman-alpha brightness in photometer and absorption cell mode, as well as operated at several thousand of kilometres away from Mars (~70,000 km) in order to measure the background counts. So far LAP is operated for more than 50 times in the Martian orbit and there have been few special operations during which the field of view (FOV) of LAP is aligned to see UV-stars in order to perform on-board photometric calibration.


Annexure – 5

Specifications of MOM-MENCA

MENCA: Payload Features


MENCA is a transmission type quadrupole neutral mass spectrometer with open source ionizer that uses 70 eV electrons to ionize the ambient neutrals. The mass filtering is accomplished by the Quadrupole Mass Analyser (QMA). MENCA is equipped with a Channel Electron Multiplier (CEM) and a Faraday Cup (FC) detector. The instrument is operated at different mass scan rates and different bias voltages of the CEM detector in order to meet required scientific objectives. MENCA is also eqippped with a Bayard-Alpert Gauge to measure the total pressure. Following Table  summarises the functional specifications of MENCA.


Functional specifications of MENCA

Mass range

1 to 300 amu (programmable) with 1 amu resolution


Quadrupole Mass Analyser for relative abundance measurement and Bayard-Alpert Gauge for total pressure measurement


Channel Electron Multiplier, Faraday Cup



MENCA: Observations around  Mars


MENCA is operated in the Martian orbit around the peri-apsis in order to study the Martian neutral exosphere as well as at several thousand kilometers away from Mars in order to understand the nature of the background. So far MENCA is operated for more than 200 times in the Martian orbit. There have been few special operations during which the Field Of View (FOV) of MENCA is aligned along the velocity vector of the MOM spacecraft in order to study the Martian exosphere with maximum efficiency.








Annexure – 6

Data products from MCC, TIS and MSM

Standard data products of MCC:


Level 1B           : Radiance product PDS format

Level 1C           : Geo-referenced (Radiometrically and geometrically corrected) product PDS format


Standard data products of MSM:


Level 1B           : Radiance product in Methane and Reference Channels in PDS format


Standard data products of TIS:


Level 1B           : Radiance product in 7-13 µm range PDS format



Standard Data products of MENCA:

Data products are mass spectra in the mass range 1 to 300 amu with unit mass resolution. The data structure is [time, mass, number of samples, raw partial pressure] and [Time, raw total pressure]. Calibration factors will be provided separately along with SPICE kernels for ancillary data processing.


Standard Data products of LAP:


Level-0              : Raw payload data along with the ancillary information, which includes ephemeris and attitude in PDS format.


Level-1              : Corrected / Calibrated Data in PDS format.


Annexure - 7



Cover Page of the Proposal



Title of the Proposal                                            





Name and Designation of PI                           





Telephone, Fax and E-mail Address    





Name of Institution with full Address including e-mail and phone/FAX no     





Signature of PI with Date




Signature of Head of Institution                      





Announcement of Opportunity (AO) proposal

Submitted to Space Applications Centre /

Space Physics Laboratory / Laboratory for

Electro-Optics Systems,  ISRO on

Annexure - 8



Format of the Proposal



  1. Title of the Proposal:



  1. Name of the Principal Investigator:






            Mailing Address:


  1. Summary of the proposed work



  1. Details on the preliminary work done/background experience, if any



  1. List of Publications in the related field



  1. Description of the project


  • Theme
  • Objectives
  • Study area (latitude/ longitude)
  • Type of data products required (season(s), periodicity and number)
  • Methodology
  • Schedule/Quarterly mile stones
  • Expected results and its possible uses
  1. Name of Co-investigator(s) in the AO project (please include bio-data of all Investigators)
  2. Whether any collaboration with payload team is required, if yes, provide details?
  3.  Extent of Financial support needed from ISRO for executing the work within the shortest possible time (Provide item wise and year wise breakup in table form)
  4. Available facilities and equipment at your institution

Annexure -9


Format for Declaration





We have carefully read the terms and conditions of Announcement of Opportunity for utilizing Mars Orbiter Mission data from MCC/ TIS / MSM / LAP/ MENCA (strike out whichever is not applicable) payloads (MOM-AO) programme and agree to abide by them.


It is certified that if the AO proposal is accepted and supported by ISRO, the facilities as identified in the proposal and administrative support available at our institution and needed to execute the project will be extended to the Principal Investigator and other Co-Investigators.


We certify that the data products provided would be used only for the intended AO project.


It is agreed that data products will be returned to ISRO in case the AO project does not progress /

complete as scheduled.




Signature of PI with Name and Designation





Signature of Head of Institution with Name and Designation








Seal of Head of Institution