Mathematics – Logic
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.688v&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Mathematics
Logic
Scientific paper
Martian meteorological lander (MML) is dedicated for landing onto the Mars surface with the purpose to carry on the monitoring of Mars atmosphere condition at a landing point during one Martian year. MML is supposed to become the basic element of a global net of meteorological mini stations and will permit to observe the dynamics of Martian atmosphere parameters changes during a long time duration. The main scientific tasks of MML are as follows: -study of vertical structure of Mars atmosphere during MML descending; -meteorological observations on Mars surface during one Martian year. One of the essential factor influencing to the lander design is descent trajectory design. During the preliminary phase of development five (5) options of MML were considered. In our opinion, these variants provide the accomplishment of the above-mentioned tasks with a high effectiveness. Joined into the first group, variants with parachute system and with Inflatable Air Brakes+Inflatable Airbag are similar in arranging of pre-landing braking stage and completely analogous in landing by means of airbags. The usage of additional Inflatable Braking Unit (IBU) in the second variant does not affect the procedure of braking - decreasing of velocity by the moment of touching the surface due to decreasing of ballistic parameter Px. A distinctive feature of MML development variants of other three concepts is the presence of Inflatable Braking Unit (IBU) in their configurations (IBU is rigidly joined with landing module up to the moment of its touching the surface). Besides, in variant with the tore-shaped IBU it acts as a shock- absorbing unit. In two options, Inflatable Braking Shock-Absorbing Unit (IBSAU) (or IBU) releases the surface module after its landing at the moment of IBSAU (or IBU) elastic recoil. Variants of this concept are equal in terms of mass (approximately 15 kg). For variants of concepts with IBU the landing velocity is up to50-70 m/s. Stations of last three options are much more reliable in comparison with MML of first and second options because their functional diagram is realized by operation of 3-4 (instead of 8-10 for MML of first and second concepts) executive devices. A distinctive moment for MML of last three concepts , namely for variants 3 and 5, is the final stage of landing stipulated by penetration of forebody into the soil. Such a profile of landing was taken into account during the development of one of the landing vehicles for the "MARS-96" SC. This will permit to implement simple technical decisions for putting the meteorological complex into operation and to carry out its further operations on the surface. After comparative analysis of 5 concepts for the more detailed development concepts with parachute system and with IBU and penetration unit have been chosen as most prospective. However, finally, on the next step the new modification of the lander (hybrid version of third and fifth option with inflatable braking device and penetrating unit) has been proposed and chosen for the next step of development. The several small stations should be transported to Mars in frameworks of Scout Mars mission, or Phobos Sample Return mission as piggyback payload.
Pichkhadze Konstantin
Polyakov Alexander
Vorontsov Victor
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