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Liquid-fuel Rocket Engine

Thermoelectric Converter DT 27

  • Purpose: Temperature measurement of aggressive (liquid oxygen) and non-aggressive liquids and gases (naphthyl) units of liquid engines of rocket and space technology products.
  • Estimated production / delivery time (months): 6
  • Flight qualification of the product: Yes
ParameterValue
Range of measurements, ° C-196/+600
Limits of permissible deviations of TEDS from NSKHK (L), ° С, (for tolerance classes 2, 3 according to GOST R 8.585-2000) in the temperature measurement range: 1. -196 / -100 °С; 2. St. -100 / + 100 °C; 3. -40 / + 360 °C; 4. St. + 360 / + 600 °С1. ±(1,5+0,01 |t|); 2. ±2,5; 3. ±2,5; 4. ±(0,7+0,005 |t|)
Limits of permissible deviations of TEDS from NSH HA (K), ° С (for tolerance classes 2, 3 according to GOST R 8.585-2000) in the temperature measurement range: 1. -196 / -167 ° С; 2. -167 / + 40 ° C; 3. -40 / + 333 ° C; 4. St. + 333 / + 600 ° С1. ±(0,015 |t|); 2. ±2,5; 3. ±2,5; 4. ±(0,0075 |t|)
Thermal inertia index Ꚍ0,63, s, not more than0,2
Weight, kg, not more0,15

Features:

  • extended temperature range;
  • high reliability under the influence of vibration, shock, temperature, humidity;
  • maintains operability when exposed to aggressive environments with a temperature of 600 °C due to the use of special alloys in the design;
  • analog output;
  • design has been developed that provides high vibration and shock resistance at the cable termination site.

Version: thermoelectric converter (TC) consists of a sensitive element placed in the housing, a cable jumper and a connector. The sensitive element is based on a thermocouple cable with mineral insulation TU 16-505.757.