From Wikipedia, the free encyclopedia
RD-810 (РД-810) Country of origin
Ukraine Designer
Yuzhnoye Design Bureau Manufacturer
Yuzhmash Application First Stage Status In development Propellant
LOX /
RP-1 Mixture ratio 2.65 Cycle
Staged Combustion Chamber 1 Thrust, vacuum 2,105 kN (473,000 lbf ) Thrust, sea-level 1,876 kN (422,000 lbf ) Chamber
pressure 18 MPa (2,600 psi)
Specific impulse , vacuum 335.5 s (3.290 km/s)
Specific impulse , sea-level 299 s (2.93 km/s)
Gimbal range 8 Dry weight 2,800 kg (6,200 lb) References
[1]
[2]
[3]
[4]
The RD-810 (РД-810 ) is a
Ukrainian
liquid propellant rocket engine burning
LOX and
Kerosene (
RG-1 ) in a
staged combustion cycle .
[4] It has a single combustion chamber that provides
thrust vector control by
gimbaling of the nozzle in two axis by +/- 8°. It is being designed in
Ukraine by
Yuzhnoye Design Bureau for the prospective first stage propulsion of the
Mayak rocket family.
[4]
[2]
The RD-810 as well as the
RD-801 are being designed based on the work of the
RD-8 vernier and the maintenance and improvement of the
RD-120 engines. The RD-810 can be used stand alone on a Mayak or could be used in a module of four called RD-810M to replace the
RD-170 on the
Zenit .
[2]
See also
Mayak – Prospective
Ukrainian launch vehicle family for which the RD-810 is being developed.
RD-801 – A smaller engine of the same family designed by Yuzhnoe.
SCE-200 – An
Indian rocket engine of equal specifications which might be based on the RD-810 blueprints.
Yuzhnoe Design Bureau – The RD-810 designer bureau.
Yuzhmash – A multi-product machine-building company that's closely related to Yuzhnoe and would manufacture the RD-RD-810.
References
External links
Liquid fuel
Cryogenic
Hydrolox (
LH2 /
LOX )
China
Europe
India
Japan
Russia
USA
Methalox (
CH4 /
LOX )
Semi- cryogenic
Kerolox (
RP-1 /
LOX )
China
India
Russia
NK-15
NK-33, 44
RD-58
RD-0105, 0109
RD-0107, 0108, 0110
RD-0110R
RD-0124
RD-107, 108, 117, 118
RD-120
RD-170, 171
RD-180
RD-191, 151, 181
RD-193
S1.5400
Spain
Ukraine
USA
Storable
Hypergolic (
Aerozine ,
UH 25 ,
MMH , or
UDMH /
N2 O4 ,
MON , or
HNO3 )
China
Europe
India
Israel
North Korea
Russia
17D61
RD-0202 to 0206, 0208 to 0213
RD-0207, 0214
RD-0216, 0217, 0235
RD-0233, 0234
RD-0236
RD-0237
RD-0243 to 0245
RD-0255 to 0257
RD-215 to 219
RD-250 to 252, 261, 262
RD-253, 275
RD-263, 268, 273
RD-270
S5.92
S5.98M
Ukraine
USA
Other
Solid fuel
China
Europe
India
Iran
Israel
Japan
USA
* Different versions of the engine use different propellant combinations
Engines in italics are under development