Misplaced Pages

MMR06

Article snapshot taken from[REDACTED] with creative commons attribution-sharealike license. Give it a read and then ask your questions in the chat. We can research this topic together.
Soviet sounding rocket
You can help expand this article with text translated from the corresponding article in Russian. Click for important translation instructions.
  • Machine translation, like DeepL or Google Translate, is a useful starting point for translations, but translators must revise errors as necessary and confirm that the translation is accurate, rather than simply copy-pasting machine-translated text into the English Misplaced Pages.
  • Consider adding a topic to this template: there are already 1,022 articles in the main category, and specifying|topic= will aid in categorization.
  • Do not translate text that appears unreliable or low-quality. If possible, verify the text with references provided in the foreign-language article.
  • You must provide copyright attribution in the edit summary accompanying your translation by providing an interlanguage link to the source of your translation. A model attribution edit summary is Content in this edit is translated from the existing Russian Misplaced Pages article at ]; see its history for attribution.
  • You may also add the template {{Translated|ru|ММР-06}} to the talk page.
  • For more guidance, see Misplaced Pages:Translation.

The MMR06 is a Soviet/Russian rocket for meteorological experiments, with a length of 3.48 metres and a total weight of 130 kg. The MMR06 rocket was built in two versions: One version had a conical top, the second one, named MMR06-M, had a detachable free flying top, also called dart. The maximum flight height was about 60 - 80 kilometres. Between 1988 and 1992 62 rockets of the type MMR06-M were launched from the former NVA exercise area Zingst, in order to accomplish wind and temperature measurements in the upper atmosphere.

Technical data of MMR06-M

Total

Total mass 134 ±5 kg
Mass empty 58 kg
Fuel mass 78 kg
Length 4.14 m
 
Distance from end of nozzle to
center of gravity at launch		 1.445 m
Distance from end of nozzle to
center of gravity at burn-out (Brennschluss)		 1.872 m
Distance from end of nozzle to
center of wind pressure		 1 m
 
Axial moment of inertia at launch 0.87 kg/m
Axial moment of inertia at burn-out 0.25 kg/m
 
Equatorial moment of inertia at launch 394.5 kg/m
Equatorial moment of inertia at burn-out 158.5 kg/m
schematic flight path of MMR06-M rocket
schematic flight path of MMR06-M rocket

Aerodynamic coefficients

Cd (drag coefficient) 0.42
Cl (lift coefficient) 20
Cm 34.4
Burn-out velocity 1428 m/s
Rotational velocity of
rocket around own axis		 800 rpm

Rocket engine

Mass with payload 121.8 kg
Mass without payload
with transition piece		 38 kg
Mass without payload
without transition piece		 33 kg
Length with transition piece 2.813 m
Length without transition piece 2.444 m
Time of burn-out 7.2 s - 12 s
Diameter 0.2 m
Wing span 0.6 m
Angle of attack of wings 5' - 40'

Dart

Mass 12.2 kg
Length 1.478 m
Diameter 0.063 m
Distance from end of dart
to center of gravity		 0.78 m
Distance from end of dart
to center of wind pressure		 0.5 m
Axial moment of inertia 0.00752 kg/m
Equatorial moment of inertia 3.48 kg/m
Wing span 0.148 m
Angle of attack between wings
and longitudinal axis		 0°
Velocity at expulsion of probe 3.65 m/s
Aerodynamic coefficients
Cd 0.15
Cl 20
Cm 34.4

Parachute system

Mass 1 kg
Time of expulsion 130 s

Launch sites

Ship

  • Musson
  • Ushakov
  • Ernst Krenkel
  • Priliv
  • Volna

Land

References

  • Wade, Mark. "MMR-06". www.astronautix.com. Retrieved 2024-07-01.
Categories:
MMR06 Add topic