|
 The devices are used for fixing
the parts that separate from the launch vehicle and they also can be used for attachment and subsequent separation of the spacecraft
by an electric command.
The pyrolocks solve the problem of separation of some launch vehicle (LV) parts from the LV if those parts have
executed their function during the flight.
The pyrolocks make no negative effect on the required cleanliness of the ambient environment in the process of their operation including
the separation process. The pyrolocks are of small mass, their reliability is high (P>0.99995) verified by their experimental
development and also at practical injection of "Meteor-3M" spacecraft into the orbit using pyrolock 00.2617.0005.0000.00.0.
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| Name | Axial operational load KN
Not more than | Minimum destructive axial load KN
Not less than |
Pulse on the object separated N.s±1N.s | Time from signal supply till execution of the function S
Not more than |
Type of electric igniter | Initiation current for each of two bridges of the electric igniter, A |
Reliability
Not less than | Mass of the device, kg |
Mass of part of the device that remains on the object separated, kg |
Pyrolock
00.2617.0005.0000.00.0 | 102,9 | 156,8 | 9,8…14,7 | 0,013 |
EVP-19 | 2 | 0,99995 | 0,65 | 0,15 |
Pyrolock
Ě18 | 103,0 | 157 | 3,5 | | 0,4 |
Pyrolock
Ě14 | 49,0 | 78,4 | 0,999985 | 0,25 | 0,06 |
Pyrolock
00.5436.0005.0000.06.0 | 30,0 | 45 | 3 | 0,99995 | 0,11 | 0,015 |
Yuzhnoye SDO can adapt the structures of the pyromechanical devices for the required operational
conditions according to the user's request. |
Development of company
