Yuzhnoye designs components for spacecraft, taking into account latest engineering achievements and meeting basic space technology requirements:
- High reliability
- Compactness
- Minimum power consumption.
The components can be installed with minimum modifications onboard many spacecraft.
Rotation mechanisms
Rotation mechanisms are designed for single actuation during first 50 hours in orbit. They smoothly rotate and lock in operating position the satellite structural components such as
- Solar panels
- Booms with scientific instruments
- Platforms with antennas and scientific instruments.
There are two types of rotation mechanisms:
- With spring drive
- With electromechanical drive.
Basic Specifications
|
Rotation mechanism |
Electromechanical drive |
||||||
|---|---|---|---|---|---|---|---|
|
Angle, deg |
180 | 30 | 90 | 45 | 90 | ||
|
Locating accuracy, ang. min |
±5 |
±30 |
±1 | ±30 | |||
|
Rotation time, s |
600 | 200 | 60 | 150 | 100 | 10 | 30 |
|
Load inertia moment, kg•m2 |
4.7 | 9.5 | 0.6 | 16.8 | 14.3 | 0.3 | 3.6 |
|
Output torque, N•m |
108 | 402 | 108 | 804 | 402 | 33 | 412 |
|
Supply voltage, V |
28 | ||||||
|
Consumption current, A |
0.23 | 1.1 | 0.64 | 1.1 | 0.32 | 0.64 | |
|
Mass, kg |
2.3 | 8.5 | 3.0 | 9.8 | 9.6 | 4.3 | 6.0 |
| Rotation mechanism |
Spring drive |
|||
|---|---|---|---|---|
|
Angle, deg |
180 | 136 | 100 | 180 |
|
Locating accuracy, ang. min |
±30 | ±60 | ||
|
Rotation time, s |
40 | 10 | 20 | |
|
Load inertia moment, kg•m2 |
10 | 34.3 | 25.5 | 14.7 |
|
Output torque, N•m |
2.94 - 1.18 |
1.75 - 1.54 |
6.0 - 2.84 |
1.1 - 0.5 |
|
Mass, kg |
1.6 | 3.6 | 0.88 | 0.34 |
Gravity stabilizers
Gravity stabilizers are used for generation of a required spacecraft inertia ellipsoid ; they are single-actuation mechanisms used during first 10 hours after spacecraft separation from launch vehicle.
Basic Specifications
|
Mass of extended load, kg |
25 | 3 | 12 |
|
Distance between stabilizer seat plane and center of mass of extended load, mm |
17000 | 5000 | 6000 |
|
Extended-load center-of-mass deviation from perpendicular to seat plane, not more than, mm |
400 | 100 | 130 |
|
Boom extension time, s |
600 | 250 | 60 |
|
Drive |
Electromechanical | Spring | |
|
Supply voltage, V |
28 |
28 |
|
|
Consumption current, A |
0.64 | 0.2 | |
|
Total mass, kg |
37 | 4.5 | 20.2 |
Separation Device
Separation device is used for securing separated objects on spacecraft during transportation and injection into orbit, with subsequent separation of the object at a specified velocity. Separation telemetry is transmitted additionally.
Basic Specifications
|
Separation velocity, m/s |
0.45±0.05 |
|
Velocity vector diversion does not exceed, deg |
2 |
|
Separated object mass, kg |
60±5 |
Electromagnetic actuators
Electromagnetic actuators are force-creating elements of spacecraft magnetic attitude control systems. The actuators are used for generation of magnetic dipole moment.
Basic Specifications
|
Nominal magnetic moment, A·m2 |
9 | 18 | 120 | 350 |
|
Rated input at 27 V supply voltage and 25°C, W |
1.6 | 1.8 | 5 | 15 |
|
Mass, kg |
0.35 | 0.5 | 3.8 | 9.8 |
|
Size, mm: |
170 |
250 |
500 |
1000 |
|
Length |
||||
|
Diameter |
22 | 22 | 42 | 55 |
THERMOSTABLE CASE FOR HIGH-RESOLUTION TELESCOPE
The thermostable case for a high-resolution telescope comprises a carbon plastic tube and body. Glued embedded parts (bushes, supports) are made of titanium.
Basic Specifications
|
Size, mm: - height - diameter |
1525 920 |
|
Mass, kg |
108 |
|
Stability of locations of optical elements seats in the working temperature range (20±2)°С: |
|
| - linear displacements, µm | 10 |
| - angular displacements, arcsec | 5 |
THERMAL STABLE-SIZED PANEL HOUSING OF HIGH-RESOLUTION SCANNER
A primary element of load-bearing structure of a scanner is housing in the form of three-dimensional structure consisting of sandwich panels that are mechanically connected and additionally pasted together using angle sections. Tubular and panel casings for mirrors and other structural elements to fasten electronics modules are mounted to the housing.
All panels of the housing have carbon plastic skins and aluminium foil honeycomb filler. To increase structural stiffness, the panels are framed along the perimeter using framing of carbon plastic pipes connected by titanium fittings. Titanium bushes to fasten mirrors, membranes, etc., are pasted in all panels.
Main specifications:
|
Overall dimensions, mm |
1000×800×640 |
|
Mass, kg |
38.5 |
|
Stability of locations of optical elements seats in the working temperature range (20±2)°С: |
20±2 |
|
- linear displacements, µm |
10 |
|
- angular displacements, arcsec |
5 |
SPACECRAFT SOLAR ARRAY HONEYCOMB PLASTIC PANEL
The honeycomb panel is used for installation of solar cells.
The panel remains operational throughout the satellite active life while it is being exposed to space environment.
Basic Specifications
| Specific mass, kg/m2 | 0.8÷1.2 |
| Face run-out flatness over the surface, mm/m, no more than | 1.0 |
| Breaking stress under loads acting in the direction of skin detachment from honeycomb, MPa, no less than | 0.1 |
| Face insulation resistance, MOhm, no less than | 20 |
|
Face and back surfaces optical factors: - solar absorptance - emissivity factor |
0.93 0.77 |
| Warranty period, years, | 8.5 |
| including: | |
| - at intended use | 5 |
| - at manufacture, transportation, storage | 3.5 |
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