ISRO launched the 1,350 kg Mars Orbiter Mission - Manglayaan - from Sriharikota using PSLV-C25, an XL variant of the launcher, on November 5, 2013 at 14:38 hrs to avail of the November 2013 launch window for the planet. The launch was earlier scheduled for October 28, 2013, but was postponed to accommodate the delay in the arrival in South Pacific, due to bad weather, of one of the two SCI ships to be used for tracking the launch of the spacecraft.
ISRO is aiming to send the spacecraft hurtling on a Mars intercept trajectory from earth orbit at 0.42 hours on December 1.
The Mars orbiter will be placed in an orbit of 372 x 80,000 km around Mars and will have a provision to carry 14.49 kg of scientific payload on- board.
ISRO initially planned to use the GSLV to launch a 500 kg Mars orbiter with 25 kg scientific payload, but scaled down its plans because of two back to back failures of the launcher in 2010.
The GOI sanctioned seed money of Rs 10 crore in August 2009 to carry out studies on suitable experiments for the mission.
The budget for FY 2012-13 allocated Rs. 125 crore for the mission during the financial year. The union cabinet cleared the project on Friday, August 3, 2012.
The MOM is being launched 22 days before the start of its journey to give mission planners sufficient time to raise its orbit before the opening of the Mars journey start window on November 27.
The lift off time slot will vary each day starting November 5 with five minutes leeway.
Propelling the MOM accurately on a Mars intercept trajectory would require a complex set of maneuvers during and after launch. Trajectory calculations would be specific to the date of the launch; they will have to be recomputed in case of any launch delay.
"The time of lift-off and required coasting duration is different for each day of launch; and one has to work out a series of different trajectory management strategies corresponding to each possible launch date," says V Adimurthy, professor at Satish Dhawan Space Center and senior adviser (interplanetary missions) of ISRO. [via The Economic Times]
The spacecraft's orbital insertion will involve long coasting of the rocket between third and fourth stage.
"The management of the long coast between third and fourth stage is a complex issue," says Adimurthy.
PSLV-C-25 will inject the MOM into a 250 X 23000 km orbit with an inclination of 17.864 degree. The MOMS velocity would be progressively increased to the Earth escape velocity of 11 km per second using three to five burns of the MOM's Liquid Apogee Motor (LAM).
In order to minimize the energy requirement for the journey to Mars, the Argument of Perigee (AOP) of the MOM would need to be between 276.4 deg to 288.6 deg, compared to 178 deg in earlier missions. (The AOP is the angle between the perigee of a earth satellite and its ascending node.)
This will necessitate a launch flight regime lasting 2,657s, as against 1,200s for regular PSLV missions, with a 1,580-1,800s coasting before the ignition of the PS4 stage.
According to ISRO, the long coasting necessitated specific modification and validation of the coast phase guidance algorithm, on-board battery capacity augmentation, assessment on the performance of inertial systems for extended flight duration and deployment of two ship-borne terminals to capture the crucial telemetry data during flight in the non-visbility zone.
ISRO said that additional provisions were made for the thermal management of Vehicle Equipment Bay, PS4 stage and also the Spacecraft elements considering the longer exposure to extreme cold space.
The MOM's 55 million miles journey to Mars will take 300-days. Its trajectory would need to be accurate enough to bring it within 60 km of the Red Planet on September 22, 2014 to ensure successful Mars capture.
The Liquid Engine on the MOM, also called the 440-Newton Liquid Engine, is a modified version of the Liquid Apogee Motor (LAM) used on earlier missions that required orbit raising, such as Chandrayaan.
The Liquid Motor will raise the orbit of the MOM, propel it on a Trans-Mars trajectory, and slow it down for Mars orbit insertion.
The LM is capable of generating 440 Newton thrust. One of the mission challenges would be the restart of LM after a 300 day journey to Mars.
The MOM is also fitted with 8 22-Newtpm thrusters for controlling the orientation of the spacecraft and also for correcting the trajectory during the heliocentric phase of the mission.
The MOM carries 850-kg of fuel, of which 365-kg would be used for orbit raising.
The MOM with its solar panel, sensors and communication antenna deployed. Photo Courtesy ISRO
ISRO initially planned to use the GSLV to launch a 500kg Mars orbiter, but scaled down its plans because of two back to back failures of the launcher in 2010.
It is likely the weight of the Mars orbiter has been reduced to allow its launch using a PSLV-XL.
ISRO invited scientific payload proposals for the orbiter from agencies all over the world.
The following are the payloads short listed for the Mars orbiter: [via The Hindu]
The five scientific payloads are expected to be delivered to ISRO in March, 2013.
Past Mars orbiter missions launched by other nations have carried all the above payloads except the Methane Sensor.
Former Chairman of Indian Space Research Organisation Prof U.R. Rao told PTI on August 28, 2012 in Bengaluru, “We have selected very good experiments. One of the experiments is essentially to look for methane....where the methane comes from (what could be producing methane gas detected in the Martian atmosphere)."
"Some experiments have been selected and some are on the waiting list. The weight capability is not high. Total weight of the experiments selected can’t be more than 15 kg," he added. [via Hindu]
Observations over the last decade suggest that methane clouds form briefly over Mars during the summer months.
Release of methane has been observed to occur from discrete surface locations on Mars, although the exact location and mechanism of release is still unknown.
The presence of methane on Mars indicates the planet is still alive, in either a biologic or geologic sense, according to NASA and university scientists.
Dr. Michael Mumma of NASA's Goddard Space Flight Center in Greenbelt, Md. says:
"Methane is quickly destroyed in the Martian atmosphere in a variety of ways, so our discovery of substantial plumes of methane in the northern hemisphere of Mars in 2003 indicates some ongoing process is releasing the gas.
"At northern mid-summer, methane is released at a rate comparable to that of the massive hydrocarbon seep at Coal Oil Point in Santa Barbara, Calif."
NASA scientists are hard at work modelling the methane cycle on Mars and the agency is keen to study in detail the methane cycle of the martian atmosphere using an orbiter, but ISRO might actually beat NASA to it if ISRO's Mars Orbiter is able to make the November 2013 launch window.
MENCA, weighing 4 kg, would provide the first ever insitu measurement of the neutral composition (in the mass range of 1 to 300 amu, with 1 amu resolution) and density distribution of the Martian exosphere (atmosphere ~ 500 km and beyond from the Martian surface).
The quadrapole mass spectrometer based MENCA payload is developed by SPL jointly with AVN and AERO Entities.Measurement of D/H (Deuterium to Hydrogen abundance ratio) will improve our understanding of the process involved in the loss of water from the planet.
LAP measures the relative abundance of deuterium and hydrogen from Lyman-alpha emission in the Martian upper atmosphere.
The Mars Orbiter will have a single solar array with three panels of 1400 x 1800 mm capable of generating 750 watts of power in Martian orbit.
It will also be equipped with a 36 AH Lithium-ion battery for power storage.
On January 4, 2013, Mr. Goswami, director of Physical Research Laboratory, Ahmedabad, while speaking to the press on the sidelines of the Indian Science Congress in Kolkata, said the mission would perform science that had so far not been done
"The mission has a very specific science objective as we want to study the atmosphere of Mars. This mission will explore things which have not been done previously by other countries,” he said.
An ISRO scientist told The Pioneer in August 2012 that the Indian orbiter "will concentrate on climate and geology which is going to be crucial for future explorations of Mars." [via The Pioneer]
The orbiter will join the international effort of assessing the suitability of Mars to life by searching for subsurface groundwater trapped in aquifers for thousands of years. It will also study the effect of solar wind on the Mars' atmosphere and its surface magnetic field.
Speaking to the press in September 2012, ISRO Chairman K Radhakrishnan said, "The voyage to Mars will take about 300 days. For the first time, we are doing a voyage for such a long time."
He added that the challenges faced by ISRO included developing on-board autonomy for the Mars Orbiter to handle and the infrastructure to maintain constant communication between the spacecraft and ground control.
"This is one of the challenges…. Mars is important because we will be developing several critical technologies needed for the future," he said.
Other important challenges include
During launch, the MOM was tracked by ISRO ground stations at Sriharikota, Port Blair, Brunei and Biak in Indonesia till separation of stage 3. Following stage 4 ignition, the MOM was tracked by two specially equipped Shipping Corporation of India ships - 'Yamuna' and 'Nalanda' - positioned in the South Pacific Ocean. The ships relayed information on the last stage and ejection of the spacecraft into space,
During its journey from Earth to Mars, MOM will be tracked by ISTRAC (ISRO Telemetry, Tracking and Command Network) using the Indian Deep Space Network (IDSN) at Baylalu on the outskirts of Bangalore and sea-borne S-band terminals.
IDSN comprises two large antennas, 18-m and 32-m in diameter
ISRO will also get position data from NASA’s Deep Space Network through its three stations located in Canberra, Madrid and Goldstone on the U.S. West Coast.
At the time of Mars capture in September 2014, tracking and communication with MOM will be done using the 70-metre antenna of Nasa's deep space network at Canberra in Australia.
Discovered by Rob McNaught at the Siding Observatory in Australia on January 3, 2013, Comet C/2013 A1 is on a trajectory that will take it within close proximity of Mars, with a 1 in 8,000 probability that it will impact the planet at a of 2,00,000 kph.
Following press reports that the comet could force a push back of the MOM, ISRO Chief K Radhakrishnan said on Wednesday, April 18, 2013, "The comet could bring some constituents, but we don't expect any effect on the spacecraft. It will pass 50,000 km away from Mars' surface. We will get more information on the comet in future and scientists are looking at all possibilities."
The PSLV-C25 took off at 2:38 PM on November 5, 2013 and 44-min later successfully placed MOM into an elliptical orbit with a period of 6-hr 50-min, perigee of 248.4-km, apogee of 23,550-km, inclination of 19.20-deg and AOP of 283-deg.
The primary and secondary solar panels of the spacecraft were successfully deployed and all subsystems powered ON. Health of the Spacecraft is Confirmed Normal.
Stage 2 and 3 of the PLSV-C25 overperformed during launch taking the MOM to a higher altitude than intended, but Stage-4 compensated accurately for the over-performance.
ISTRAC started receiving spacecraft telemetry from T+500 and took control of the spacecraft after it separated from stage-4. ISTRAC will now use the LAM of the spacecraft to extend it’s apogee to over a lakh km.
The first orbit raising maneuver of India's Mars Orbiter Spacecraft was successfully performed starting at 01:17 AM IST on November 07, 2013 when the LAM was fired for 416 seconds raising the spacecraft's apogee to 28825 km. The perigee is now 252 km.
The second orbit raising Maneuver was successfully performed starting at 02:18:51 AM IST on November 08, 2013, with a 570.6 s burn of the liquid motor, which raised the apogee from 28814 km to 40186 km.
The third orbit raising maneuver was successfully performed using a liquid motor burn on Nov 09, 2013 for 707s starting at 02:10:43 hrs IST, which raised the apogee to from 40,186 km to 71,636 km.
ISRO plans a supplementary orbit raising operation at 05:00 hrs IST on November 12 to raise the apogee to around 100,000-km. ISRO has not announced if the additional burn would have consequences as a result of additional fuel burnt.
The following is the text of the ISRO statement on the fourth orbit raising burn
In the fourth orbit-raising operation conducted this morning (Nov 11, 2013), the apogee (farthest point to Earth) of Mars Orbiter Spacecraft was raised from 71,623 km to 78,276 km by imparting an incremental velocity of 35 metres/second (as against 130 metres/second originally planned to raise apogee to about 100,000 [1 lakh] km). The spacecraft is in normal health. A supplementary orbit-raising operation is planned tomorrow (November 12, 2013) at 0500 hrs IST to raise the apogee to nearly 1 lakh km.
During the orbit-raising operations conducted since November 7, 2013, ISRO has been testing and exercising the autonomy functions progressively, that are essential for Trans-Mars Injection (TMI) and Mars Orbit Insertion (MOI).
During the first three orbit-raising operations, the prime and redundant chains of gyros, accelerometers, 22 Newton attitude control thrusters, attitude and orbit control electronics as well as the associated logics for their fault detection isolation, and reconfiguration have been exercised successfully. The prime and redundant star sensors have been functioning satisfactorily. The primary coil of the solenoid flow control valve was used successfully for the first three orbit-raising operations.
During the fourth orbit-raising operations held today (November 11, 2013), the redundancies built-in for the propulsion system were exercised, namely, (a) energising the primary and redundant coils of the solenoid flow control valve of 440 Newton Liquid Engine and (b) logic for thrust augmentation by the attitude control thrusters, when needed. However, when both primary and redundant coils were energised together, as one of the planned modes, the flow to the Liquid Engine stopped. The thrust level augmentation logic, as expected, came in and the operation continued using the attitude control thrusters. This sequence resulted in reduction of the incremental velocity.
While this parallel mode of operating the two coils is not possible for subsequent operations, they could be operated independently in sequence.
A supplementary 303.8 s orbit raising liquid engine burn starting at 23:45 PM on November 11, 2013 successfully raised the apogee from 78,276-km to to 1,186,42-km after. The spacecraft is now orbiting the earth once in 2802.34-min. Orbital inclination now is 19.28-deg and the angle of Perigee to 287-deg.
The fifth Orbit Raising Liquid Engine burn starting at 01:27 AM IST, November 16, 2013 and lasting 243.5 s raised the Apogee from 118642 km to 192874 km.
MOM after fifth Liquid Engine burn.The spacecraft is now orbiting the earth once every 5475.24 at an inclination of 19.35-deg and a Angle of Perigee of 288-deg.
A 1328.89-sec burn of ISRO's Mars Orbiter Mission (MOM) 440-N Liquid Engine at 00:49 AM on December 1, 2013 imparted the expected delta-v of 647.96 m/sec and achieved a successful Trans Mars Injection (TMI). The spacecraft reportedly used about 198 kg of fuel were used for firing the 440 Newton engine for 23 minutes.
(MOM's FB didn't mention that thrusters were also used for the TMI along with 440-N engine, as initially planned. ISRO had earlier announced that the 8 thrusters on the spacecraft would operate simultaneously with the 440-N engine. However, during 4th orbit raising, the 440-N engine had shut down prematurely when an attempt was made to operate it with the 8 thrusters. A report in The Hindu later said that the thrusters were used.)
MOM seems to have achieved Earth escape velocity with a 23-sec shorter burn of the 440-N engine than initially calculated?
Earlier ISRO had announced that at 00:36 hrs on December 1, the MOM's 440-Newton Liquid Engine and its 8 22-Newton thrusters will burn for 1,351-sec and impart the spacecraft a delta-v of 648 m/sec, sending it hurtling on a Mars intercept trajectory.
Following Trans Mars Injection yesterday, December 1, 2013, the Medium Gain Antenna of the MOM was powered for long distance communication.
TMI will take MOM beyond the Earth's sphere of influence, which extends up to 9.25 lakh km, through a long helio-centric phase, to Mars' sphere of influence.
MOM will escape from the sphere of influence (SOI) of the Earth around 1.15 a.m. of December 4, 2013.
On September 24, 2014, when the spacecraft intercepts Mars' orbit around the sun, it must be 376 km plus or minus 50 km above Mars. On the same day, the next crucial operation of the spacecraft’s Mars orbit insertion has to take place.
Mars mission Project Director S. Arunan told The Hindu on November 29, 2013, "The engine burn was aimed at giving the satellite a final escape velocity (which should be a minimum of 10.7 km per second). At launch, it got the speed of 9.8 km per second. The six orbit raises added 0.873 km per second; the December 1 burn should give it the last push of 0.648 km a second — which all add up to the crucial velocity of about 11.4 km per second."
The spacecraft will be travelling 680 million km on its Mars intercept trajectory.
On December 11, 2013 following Trans-Mars injection, the thrusters will be used to perform the first mid-course correction. Additional mid-course correction maybe required during the helio-centric phase. The second mid-course correction is planned for April 2014, the third in August 2014. There will be a final mid-course correction on September 14, 2014, 10 days before we insert it into the Martian orbit. [via The Hindu]
During the launch of a Geo-synchronous Satellite the Liquid Engine is restarted a week after its launch. In the case of Chandrayaan-1 in 2008, it was restarted after a fortnight; ISRO had qualified it for restart after one month.
During the last two years, considering the specific requirements of our Mars Orbiter Mission for re-starting the spacecraft’s 440 Newton engine after it has idled for about 300 days, we had done these two actions.
For the MOM ISRO has provided a set of parallel circuits for the propellants’ flow-lines and also provided redundancy in the form of a latch-valve. ISRO has adopted the following two measures to ensure that the Liquid Engine operates without a glitch on September 24, 2014 after staying idle in Space for over 300 days.
Following its December 1 Trans-Mars injection burn, one portion of the fluid circuit will be closed. The parallel path will be energised for the operation in September 2014.
Tested the Liquid Engine in a special test facility established at the Liquid Propulsion Systems Center at Mahendragiri, Tamil Nadu. On restart, the engine performed within specifications, with just a two percent degradation in performance.
The MOM uses a closed loop control for orbit-raising, trans-Mars injection and Mars orbit injection burns. A precision accelerometer is used to determine velocity changes and control the duration of the burn to achieve required changes in velocity. As a result, minor variations in the performance of the liquid engine are automatically compensated by changes in duration of the burn.
The following MOM features give it the ability to operate autonomously.
During MOM's six orbit raising Liquid Engine burns from November 7 to November 16, ISRO tested the redundancies built into the system.
The gyroscopes, accelerometers, star-sensors, and attitude and orbit-control electronics, attitude control thrusters, the FDIR and the thrust augmentation logic, which enables the augmentation of the thrust of the 440 Newton liquid engine by eight numbers of 22 Newton control thrusters during the critical phases of operation, were tested. The termination of the burn of the 440 Newton engine, based on the feedback from the accelerometer, was tested. The on-board sequencer, which is used to store and initiate time-tagged command, was also tested.
ISRO is currently in the process of testing the orbiter’s high-gain antenna and the medium-gain antenna which are required for long distance communication. It will also energize its scientific instruments to check their health.
A national committee of scientists chaired by former Isro chief U R Rao gave the MOM a go-ahead on Friday, September 20, 2013. A pre-shipment review will be held on September 26 and the spacecraft moved to Sriharikota on September 30 for integration with the launcher. Launch is scheduled for October 28 from Sriharikota between 3.30pm and 4pm.ISRO unveiled the MOM to the media for the first time on Wednesday, September 11, 2013 and announced that launch will occur between October 21 and November 19 from Sriharikota. The orbiter is set to be moved to Sriharikota on September 27
On July 2, 2013, speaking to the press after the successful launch of IRNSS-1A onboard PSLV-C22XL, ISRO Chief K Radhakrishnan said, "We are planning to start stacking the Mars mission from July 29. We are looking to launch the mission any day from October 21. Either on November 28 or 29, the Mars mission is scheduled to leave the Earth’s orbit and start its voyage to Mars.”
On April 18, 2013 ISRO Chief K Radhakrishnan said, "India's Mars Orbiter is on schedule. The five instruments are ready and will be integrated soon.
He added, "The spacecraft sub systems are in the process of integration while the launch vehicle, PSLV, is also getting ready. It will be integrated from August onwards."
On March 29, 2013 the Deccan Herald reported that ISRO had started integration of the Mars orbiter.
Sources within the ISRO told the newspaper that preliminary design reviews had been completed and the integration process has begun.
"The structure has been delivered to clean room and the propulsion system integration is in the final stage," a source said.
ISRO is planning to move the newly developed rocket engine for orbital insertion to Sriharikota by April end after the completion of the high vacuum testing here.
On March 17, 2013, while addressing mediapersons, ISRO Chief K Radhakrishnan said: "The Mars mission is progressing well and the payloads will be received by March end for integration."
"We require the PSLV C25 for the launch. Sub-systems are currently being tested at the satellite center here. By September, we shall have the satellite ready. Also ground station augmentations are being made," Radhakrishnan added.
As on January 4, 2013, a proto flight model had been completed, ahead of the flight model to be developed by March end 2013.
The Liquid Apogee Motor (LAM) that will propel the Mars orbiter out of Earth orbit and send it hurtling towards Mars was tested for 670 seconds on Monday, October 8, 2012 at ISRO's Liquid Propulsion Systems Center at Mahendra Giri in Tamil Nadu.
"The test was successful and will go on for about 45 days," ISRO chief spokesperson Devi Prasad Karnik told the TOI.
The rocket engine for orbital insertion around Mars was due to be tested in June 2012, P C Agarwal, a space scientist who was part of the ISRO-appointed committee that evaluated the feasibility of the mission, told the press in March 2012.
In October 2012, ISRO announced Dr M Annadurai as program director of the Mars Orbiter Mission. SK Shivkumar will oversee design and development of the Orbiter. [via DNA]
Annadurai was earlier project director of Chandrayaan 1. Shivkumar, who played a key role in realizing the ground segment for Chandrayaan 1, is the director of Isro Satellite Center in Bengaluru, which will be t he lead center for the design, development, fabrication and testing of the Mars Orbiter Mission's payloads and satellites.
Following his appointment, Annadurai told DNA, “It is one more challenge for us to execute. The Mars Orbiter Mission is an extension of the earlier mission (Chandrayaan I) as we are looking to explore beyond the Moon.”
S. Arunan is the Mars mission Project Director.