EARLY DATA FOR EXOMARS 2016 CRASH ON MARS

HOME PAGE Web Site Contents Mars Report Contents Mars Report Abstract CV for Dr. David Roffman Diplomas PhD Thesis PhD Thesis Powerpoint Mars PowerPoint MSL Weather Reports Base on Mars? Seasonal Pressure Altitude Calculations Seismic Activity on Mars? Perserverance Weather Data MSL Years 5-6 Winter MSL Year 5 FALL MSL Year 5 Summer MSL Year 5 Spring MSL Years 4-5 Winter MSL Year 4 FALL MSL Year 4 Summer Weather MSL Year 4 Spring Weather MSL Yr 3-4 Winter Weather MSL Fall Yr 3 Weather MSL Yr. 3 Summer Weather MSL Yr. 3 Spring Weather Martian plume March 25 2017 MSL Ultraviolet 3 YEARS OF MSL UV Desai, EDL, Parachutes & ExoMars Mars winter vs. summer temps Helo to Mars Sea at Utopia Planitia, Mars Tree Stump at MSL? Spherical life on Mars? Mars Report Abstract, 1-1.2 Mars Report Sec.2-2.1 Report 2.2-2.4 Report 2.5-2.5.2 Report 2.5.3-2.7 Report 3-4 Report 4.1-4.1.2 Report 5 to 6 Report  7-7.2.1 Report 8 Report 9 Report 10 Report 11 Global Dust Storm Report 12 Report  13-13.2 Report 13.3-13.5 Report 13.6 Report 14-15 Report 15.1 Report 15.2-15.3 Report 15.4-15.6.2 Report 15.6.2.1 - 15.6.2.3 Report 15.6.2.4-15.7 Report 16-16.1 Report 17-20 Report References Rebuttal of REMS Report Running water on Mars MSL Year 0 Weather MSL Yr 2 Winter-Spring Weather MSL Yr 2 Summer Weather MSL Yr 2 Fall Weather MSL Yr 2-3 Winter Weather Adiabatics MSL Hi Temps MSL Low Temps Organic Chem found by MSL Oxygen in Mars Air MSL Day length & Temp Warm winter ground temps 155-Mile High Mars Plume Radiation Diurnal Air Temp Variation Mars Temps Fahrenheit Beagle found JPL/NASA Pressure Mistakes Enter MarsCorrect Sol 370, 1160 & 1161 Histories Mars-Radio-Show JPL Fudges Pressure Curves MSL Temp. ∆ Mast to Ground High & Low Pressures Normalized Mars soil 2% water Moving rock Mars MAVEN MSL Relative Humidity Claim Ashima Concedes Original MSL Weather Record Old MSL Weather Record MSL Summer Weather Pressure Estimate REMS Wind MSL Pressures REMS Reports Curiosity Geology CERN-2013-pics Daylight Math MSL Errors P1 MSL Errors P2 MSL-Chute-Flap MSL daylight Ashima Sols 15 to 111 Ashima Sol 112 to 226 Ashima Sol 227 on New Ashima Sols 270+ MSL Summer to Sol 316 Updated Secrets of Mars Weather Forecast Wind Booms MSL Credibility MSL Temp. Swings MSL Temperatures Sample Analysis at Mars (SAM) VL2 - MSL Ls Comparson Ashima MIT Mars GCM Dust Storm Nonsense Mars Slideshow Moving Sand & Martian Wind 3 DEC12 Press Conf. MSL Press Conf. 15NOV2012 Sol Numbering MSL Pressure Graph to Ls 218.8 MSL Sky Color Mars Sky Color DATA DEBATE! Zubrin's Letter Phoenix Vaisala Vaisala Pressure Sensors Phoenix &MSL Flawed MSL REMS Viking pressure sensors failed MSL landing site Mars Landings Phobos Grunt Martian Air Supersaturation Mars & CH4 Mars and MSL Time Viking Pressure Audit Links Mars Society 2008 Quant Finance Frontiers Home Front. Preface Frontiers Ch. 1 Frontiers Ch. 2 Antimatter Lightning Frontiers Ch. 3 Frontiers Ch. 4 Frontiers Ch. 5 Frontiers Ch. 6 Frontiers Ch. 7 Frontiers Ch. 8 Frontiers Ch. 9 Frontiers Ch 10 Frontiers Ch 11 Frontiers Ch 12 Frontiers Ch 13 Frontiers Ch 14 Frontiers Ch 15 Frontiers Ch 16 Frontiers Ch 17 Frontiers Ch 18 Frontiers Ch 19 Frontiers Ch 20 Frontiers Ch 21 Frontiers Ch 22 World Tour Spring-Break -13 Other Travels Asteroid Impact? ExoMars data Unit Issues Viking Pressures Tavis CADs Landing Long Scale Heights LS of Max/Min Pressures Tavis Report Tavis Failures Lander Altitude Martian Trees? Code Experiment Gedanken Report Mars Nuke? Martian Flares Mach Numbers MOLA (altitude) Original Mars Report Mariner 9 & Pressure Mars  Temps MSL Time MPF Pressure Blog Debates Spring Pendulum Plasma Model Reporting Errors Orbital Parameters Anderson Localization P. 1 Anderson Localization P. 2 Moving rock old Navigating Mars Mars Report Section Links Mars Report Figure Link Gillespie Lake rock outcrop MSL Sol 200 Anomaly Sol 1300&1301 Anomalies Gilbert Levin & Labeled Release Brine on Mars Ceres Lights Yr 1 Table 1 Missing data Mitchell Report Old Mars Report All MPF Temps ExoMars fails Did Spirit find past life? MSL ground temps go haywire OPACITY AT MSL Luminescence on Mars Dust Storms & Microorganisms 2018 Global Dust Storm Links to Sections of the Basic Report

This page is, at the moment, a quick data and reference source under construction on 10/26/2016. It shows copies of important data that might be altered with time, and as such it serves for the moment as a record of what was online early in our investigation.

A black smudge on the face of Mars: All that's left of Europe's lander after re-entry ends in fiery explosion on planet's surface.

  • Schiaparelli entered at an altitude of 75 miles and a speed of 13,000 mph (20,900 km/h)
  • However, the signal from the lander confirming it has arrived safely was not received by the telescope
  • New images from Nasa have revealed the spot where the Schiaparelli crash landed on the red planet
  • The probe is thought to have been travelling at more than 186 mph (300 km/h) when it crashed and exploded on impact with the Martian surface

Source: http://www.dailymail.co.uk/sciencetech/article-3860332/Missing-European-craft-crashed-Mars-Nasa-orbiter-spots-Schiaparelli-s-impact-site.html

By Libby Plummer and Abigail Beall For Mailonline

Published: 12:24 EST, 21 October 2016 | Updated: 16:44 EST, 21 October 2016

 

Nasa has pinpointed the location of the ESA's lost ExoMars lander.

New data from the American space agency's Mars Reconnaissance Orbiter has identified new markings on the surface of the red planet that are believed to be related to the Schiaparelli lander's possible crash.

ESA believes that it may have exploded on impact. 

The probe entered the Martian atmosphere at 15:42 GMT (10:42 ET) on 19 October for its 6-minute descent to the surface, but contact was lost shortly before expected touchdown. 

Scroll down from video 

A pair of before-and-after images taken by the Context Camera (CTX) on NASA's Mars Reconnaissance Orbiter on 29 May 2016 and 20 October 2016 show two new features appearing following the arrival of the Schiaparelli test lander module on 19 October 

Data recorded by its mothership, the Trace Gas Orbiter, is currently being analysed to understand what happened during the botched landing.

Images from the Mars Reconnaissance Orbiter (MRO) took pictures of the expected touchdown site in Meridiani Planum on 20 October.

A new image released today shows two new features on the surface of Mars when compared to an image from the same camera taken in May this year.


Read more: http://www.dailymail.co.uk/sciencetech/article-3860332/Missing-European-craft-crashed-Mars-Nasa-orbiter-spots-Schiaparelli-s-impact-site.html#ixzz4NrQ5dYEt
Follow us: @MailOnline on Twitter | DailyMail on Facebook

Source: http://www.popsci.com/nasa-found-pieces-europes-mars-lander

A release from the European Space Agency about the finding is cautious in its language, never spelling out the possibility that the Schiaparelli lander is permanently offline. A small bright patch appears to be the lander's parachute and heat shield, and a larger dark spot, roughly 50 feet by 130 feet, could be the cloud of Schiaparelli's impact. Without active thrusters to slow the descent, the ESA estimates that the lander approached the surface of the planet at a speed of over 180 mph. There is only so much careful language that can obscure an assessment like this: “It is also possible that the lander exploded on impact, as its thruster propellant tanks were likely still full.”

Europe’s ExoMars Trace Gas Orbiter made it to its final destination in full working order, unlike its land-bound companion. Scientists will use photos of the crash site and data relayed from the crashing lander to the orbiter to figure out what went wrong in the landing.

Says the European Space Agency:

Since the module’s descent trajectory was observed from three different locations, the teams are confident that they will be able to reconstruct the chain of events with great accuracy. The exact mode of anomaly onboard Schiaparelli is still under investigation.

If the lander is truly dead, as its scattered parts on the Martian surface seem to indicate, there is still science to do in learning how, exactly, it happened, and how to ensure ESA's Mars rover, launching in 2020, doesn't meet the same fate. Science is an iterative process, and for every great leap for humankind, there are several other, less successful hops, and even some tragic fumbles, that we had to learn from first.

Schiaparelli's fuel tanks are filled

http://exploration.esa.int/mars/57282-schiaparellis-fuel-tanks-are-filled/

02 February 2016 16:52

The hazardous task of fuelling Schiaparelli, the ExoMars 2016 entry, descent, and landing demonstrator module, has been safely completed at Baikonur. The module now has sufficient fuel on board to power the thrusters it will use while descending through the Martian atmosphere in October this year.

 

Operators in protective gear while fuelling Schiaparelli. Credit: ESA -T. Walloschek

The 600 kg Schiaparelli module is equipped with nine thrusters, clustered in groups of three. These will be activated about 1.3 km above the surface of Mars to slow the spacecraft down to less than 2 km/h when about 2m above the surface. At this point, the thrusters will be switched off and the module will drop to the ground.

The thrusters are powered by hydrazine, and the hazardous task of filling the fuel tanks with this toxic fuel and the successive pressurisation of the propellant tanks to launch pressure was completed on Sunday evening, by a dedicated team from Thales Alenia France who are in Baikonur specifically to take care of fuelling the module.

There are three 17.5 litre (4.623011 gallon ) tanks on Schiaparelli. Each of these was filled with about 15 kg (33.0693 pounds) of hydrazine. But hydrazine on its own is not sufficient and the spacecraft also needs helium for its pressure regulated propulsion system to function.

A high-pressure helium tank on the module had been filled with 15.6 litres of helium and brought to flight pressure (at approximately 170 bar pressure) before the hydrazine fuelling. This helium is used to pressurise the propellant tanks and bring the propulsion system to the correct operating pressure.

While on the ground, closed pyro valves prevent the propellant from reaching the thrusters. Once in space, when the thrusters are eventually needed, the pressurised helium will be released into the propellant tanks to "push" the hydrazine into the propellant feed lines and towards the combustion chambers where the fuel will be ignited and forced out of the thruster nozzles. That process relies inherently on the helium pressure upstream of the hydrazine, which is maintained, via a pressure regulator, to the required operating pressure.

Supplies for fuelling. Credit: ESA - B. Bethge

Fuelling operations began on Thursday when Schiaparelli was moved from the clean tent area of the cleanroom, where it had been for the other preparatory activities, into the dedicated fuelling area. Preparations and safety checks were carried out on Friday and the actual hydrazine fuelling was done on Saturday, taking about two hours to complete the fuel transfer. On Sunday, the system was brought up to launch pressure, and by Sunday evening Schiaparelli could be declared to be fully fuelled and was ready to be brought back to the main cleanroom.

The fuelling team will be busy for another few days as they take care of decontaminating the fuelling equipment so that it can be transported back to Cannes.

An operator in protective gear while working near Schiaparelli. Credit: Thales Alenia Space/Imag[IN]

Now that Schiaparelli has been fuelled additional safety precautions will be implemented for all activities that are carried out in the vicinity of the module.

In practice, the presence of the hazardous fuel onboard Schiaparelli means that anyone working close by will need to carry a gas mask and wear an anti-acid protective suit. All personnel working in the cleanroom have had special safety training for what to do in case of a declared emergency, and as an additional safety measure, hydrazine detectors will be placed around the spacecraft.

 

 

 

Schiaparelli EDM lander
Maquette EDM salon du Bourget 2013 DSC 0192.JPG
Model of Schiaparelli lander at the 2013 Paris Air Show
 
Mission type Mars lander / technology demonstrator
Operator ESA · Roscosmos
COSPAR ID 2016-017A
SATCAT № 41388
Website exploration.esa.int/mars/46124-mission-overview/
Mission duration Planned: 2 to 8 sols[1]
 
Spacecraft properties
Manufacturer Thales Alenia Space
Launch mass 600 kg (1,300 lb)
Dimensions Diameter: 2.4 m (7.9 ft)
Height: 1.65 m (5.4 ft)
 
Start of mission
Launch date 14 March 2016, 09:31 UTC
Rocket Proton-M/Briz-M
Launch site Baikonur Site 200/39
Contractor Khrunichev
 
Mars lander
Landing date Planned: 19 October 2016
Landing site Planned: Meridiani Planum

 

Source: https://en.wikipedia.org/wiki/Schiaparelli_EDM_lander#Loss_of_the_lander

Loss of the lander

The Schiaparelli lander attempted an automated landing on 19 October 2016, but the signal was lost unexpectedly a short time before the planned time of the landing.[4][26] ESA's Mars Express and NASA's Mars Reconnaissance Orbiter (MRO) and MAVEN listened for the lander's signal.[4] Initial analysis of returned telemetry (600 megabytes of data[27]) suggests that the heat shield and parachute deployment worked as expected, but the parachute was released too soon. In addition, the subsequent rocket thrusters firing lasted about 3 seconds instead of the expected 30 seconds, so a soft landing appears not to have occurred.[28][29]

 

Martian gravity: 3,711 meters per second squared.

SIMILAR CRASH FOR MARS POLAR LANDER IN 1999. SOURCE: http://www.telegraph.co.uk/science/2016/10/20/exomars-lander-may-have-crashed-on-mars-after-parachute-and-retr/

The parachute should have released at an altitude of 4,000 feet before thrusters fire to slow the craft down from 150mph to 2.4mph so it can land gently. But data suggested the parachute had been jettisoned too early, before the probe had slowed sufficiently. Although thrusters did fire to slow the descent, they did not burn for as long as expected which could also have left the craft hurtling towards the ground at high speed.

In Nasa's 1999 Mars Polar Lander mission the retrorockets fired too early at the same stage causing the spacecraft to crash land. 

Mr Acoomazzo said it was ‘definitely a possibility’ that the probe had been accelerating too fast as it hit the surface.

“The data have been partially analysed and confirm that the entry and descent stages occurred as expected, with events diverging from what was expected after the ejection of the back heat shield and parachute,” he said.

“This ejection itself appears to have occurred earlier than expected, but analysis is not yet complete. That’s definitely a possibility (that is was accelerating too fast).

“It could be that these parachute phases has been terminated too early then we were far too high, or we have a behaviour that has led the lander to be far too low.

“We saw the thrusters fired for a few seconds, but much shorter than we were expecting. We can’t say if they all fired but we will be able to see that in the coming weeks.

 

 

Oct 25, 2016: NASA states ,"Exactly what happened to the Schiaparelli lander is not yet known. ESA scientists hypothesize the module crashed when its thrusters were turned off prematurely. Instead of floating to a soft landing using thrusters, the lander dropped up to 2.5 miles at a speed of 184 mph (296.119 km/h). If the thrusters were not operational, then the module would have crash landed with a full load of fuel. The fuel would have exploded on impact, producing the large cloud of surface debris that was seen on the MRO footage. Read more: http://www.digitaltrends.com/cool-tech/esa-exomars-lander-explosion/#ixzz4O6TvtQAd Follow us: @digitaltrends on Twitter | digitaltrendsftw on Facebook"

THE PARACHUTE SYSTEM DESIGN (SOURCE: AIAA 2009-2975)

The parachute system design is driven by the limited altitude between where the probe decelerates to a Mach number compatible with parachute deployment (Mach below 2.1 and a maximum dynamic pressure of 910Pa) and the surface – as little as 5 km. The reaction control system ensures final velocity control to provide safe and robust lander release conditions. The RCS definition is closely linked to the parachute capability and Descent Module GNC strategy. Descent velocity is optimized at 45 m/s (100.662 mph or 162 kph). The RCS GNC performance is characterized by its high throttle modulation capability and low response time. The system relies on 4 Aerojet MR-80B engines fed by hydrazine with a He pressurized system.

 

 

 
Hydrazine
Skeletal formula of hydrazine with all explicit hydrogens added
Spacefill model of hydrazine
Stereo, skeletal formula of hydrazine with all explicit hydrogens added
Ball and stick model of hydrazine
Sample of hydrazine hydrate.jpg
Hydrazine hydrate
Names
Systematic IUPAC name
Hydrazine[2]
Other names
Diamine;[1] Diazane;[2] Tetrahydridodinitrogen (N—N)
Properties
N
2H
4
Molar mass 32.0452 g mol−1
Appearance Colorless, fuming, oily liquid[3]
Odor ammonia-like[3]
Density 1.021 g cm−3
Melting point 2 °C; 35 °F; 275 K
Boiling point 114 °C; 237 °F; 387 K
miscible[3]
log P 0.67
Vapor pressure 1 kP (at 30.7 °C)
Acidity (pKa) 8.10 (N2H5+)[4]
Basicity (pKb) 5.90
1.46044 (at 22 °C)
Viscosity 0.876 cP
Structure
Triangular pyramidal at N
1.85 D[5]
Thermochemistry
121.52 J K−1 mol−1
50.63 kJ mol−1
Hazards
Flash point 52 °C (126 °F; 325 K)
24 to 270 °C (75 to 518 °F; 297 to 543 K)
Explosive limits 1.8–99.99%
IDLH (Immediate danger)
 Ca [50 ppm][3]

Rocket fuel

 
Anhydrous hydrazine being loaded into the MESSENGER space probe. The technician is wearing a safety suit.

Hydrazine was first used during World War II as a component in rocket fuel mixtures. A 30% mix by weight with 57% methanol (M-Stoff in German) and 13% water was called C-Stoff by the Germans.[16] The mixture was used to power the Messerschmitt Me 163B rocket-powered fighter plane. Hydrazine was also used as a propellant with the German high test peroxide T-Stoff oxidizer. Unmixed hydrazine was referred to as B-Stoff by the Germans, a designation also used later for the methanol/water fuel for the V-2 missile.

Hydrazine is used as a low-power monopropellant for the maneuvering thrusters of spacecraft, and was used to power the Space Shuttle's auxiliary power units (APUs). In addition, monopropellant hydrazine-fueled rocket engines are often used in terminal descent of spacecraft. Such engines were used on the Viking program landers in the 1970s as well as the Phoenix lander and Curiosity rover which landed on Mars in May 2008 and August 2012, respectively.

In all hydrazine monopropellant engines, the hydrazine is passed by a catalyst such as iridium metal supported by high-surface-area alumina (aluminium oxide) or carbon nanofibers,[17] or more recently molybdenum nitride on alumina,[18] which causes it to decompose into ammonia, nitrogen gas, and hydrogen gas according to the following reactions:[19]

  1. 3 N2H4 → 4 NH3 + N2
  2. N2H4 → N2 + 2 H2
  3. 4 NH3 + N2H4 → 3 N2 + 8 H2

Reactions 1 and 2 are extremely exothermic (the catalyst chamber can reach 800 °C in a matter of milliseconds,[17]) and they produce large volumes of hot gas from a small volume of liquid,[18] making hydrazine a fairly efficient thruster propellant with a vacuum specific impulse of about 220 seconds.[20] Reaction 3 is endothermic and so reduces the temperature of the products, but also produces a greater number of molecules. The catalyst structure affects the proportion of the NH3 that is dissociated in Reaction 3; a higher temperature is desirable for rocket thrusters, while more molecules are desirable when the reactions are intended to produce greater quantities of gas[citation needed].

Other variants of hydrazine that are used as rocket fuel are monomethylhydrazine, (CH3)NH(NH2) (also known as MMH), and unsymmetrical dimethylhydrazine, (CH3)2N(NH2) (also known as UDMH). These derivatives are used in two-component rocket fuels, often together with dinitrogen tetroxide, N2O4. These reactions are extremely exothermic, and the burning is also hypergolic, which means that it starts without any external ignition source.[21]