Vehicle description

tech description

Table adapted from Semyonov (ed.), 1995, p. 22.

Parameter	Value or Characteristic
Launch mass of MRKK, tonnes	2400
Payload mass, tonnes	105
Max total useful power in flight, million hp	170
Propellants – Block Ts	Oxygen–Hydrogen
Propellants – Block A	Oxygen–Kerosene
Launch vehicle height, meters	60
Launch vehicle width, meters	18
Block Ts length, meters	58.1
Block Ts diameter, meters	7.7
Block A length, meters	38.3
Block A diameter, meters	3.9
Total engine thrust, tonnes-force	4000/3500**
Block Ts engine thrust, tonnes-force	(190.0/142.5)** × 4
Block A engine thrust, tonnes-force	806/640**
Block Ts specific impulse (vacuum), seconds	454
Block A specific impulse, seconds	336/308**

* Values are rounded within possible deviations. ** Numerator — at sea level, denominator — in vacuum.

Table adapted from Semyonov (ed.), 1995, p. 48.

Parameter	Value
Max launch mass, tonnes	105
Payload mass, tonnes	30
Landing mass (nominal), tonnes	82
Landing mass (maximum), tonnes	87
Return payload mass (nominal), tonnes	15
Return payload mass (maximum), tonnes	20
Crew – early flight tests (with ejection seats)	2
Crew – maximum (without ejection seats)	10
Flight duration (nominal), days	7
Flight duration (maximum, with extra tanks), days	30
Orbital inclination range, degrees	50.7-110
Working circular orbit altitude, km	250-500
Maximum orbit altitude, km	1000
Orbital maneuvering engine (DOM) thrust (vacuum), tonnes-force	8.8
G-load at ascent to orbit (maximum)	3
G-load at atmospheric reentry (nominal trajectory)	1.6
Lift-to-drag at hypersonic speeds	1.5
Lift-to-drag at low subsonic speeds	5
Max lateral maneuver range during descent, km	1700
Landing speed – average (at landing mass 82 t), km/h	312
Landing speed – maximum, km/h	360
Landing speed - during 1988 orbital flight, km/h	263 ¹
Overall length, meters	36.37
Fuselage length, meters	30.85
Fuselage width (maximum), meters	5.5
Height on ground, meters	16.35
Wingspan, meters	23.92

Bibliography