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Rocket Flight dynamic scheme
X, Y Coordinate system from Center Gravity, X‐local horizont
Xc, Yc Start coordinate system
Xc, Yc Start coordinate system
XA,YA Air‐dynamic force projections
V Rocket velocityV Rocket velocity
H Rocket flight altitude
P Rocket engine thrustP Rocket engine thrust
L Distance from start point
R Radius of EarthR Radius of Earth
mg Weight of rocket
φ Pitch angle ‐ between rocket axisφ Pitch angle between rocket axis and local horizont
α Angle of attack
3
θ Trajectory angle ‐ between velocity vector and local horizont
Payload mass m pl kg
The principal parameters of Launch Vehicle: m pl, kg
Initial launch mass m 0, kgPropellant type Liquid Solid
High - boiling or Low-boilingOxydizer + Fuel:
Amil +Heptyl Oxigen+HydrogenOxigen+Kerosyne
Cellulose Nitrate or Mixtured
g y
Engine thrust P, Nuton
Specific Impulse Is = P / propellant consumption m/secIs = P / propellant consumption, m/sec
2900….3300 m/s 4000…4500 m/s
2700…2900 m/sec
Number of stages NNumber of stagesUsually: N = 2…..3
Initial thrust / weight ratio n0 = P /m 0 g0Pitch angle as function of ( )Pitch angle as function of time φ = φ (t)Relative mass characteristics (statistics) Propellant Section mass characteristics a ps
Rocket engine relative mass eng
Name LV, stage Propellant P Is m eng Rocket
The typical examples of rocket engines
Thrust in vacuum, N
Specific impulse in vacuum, m/s
mass, kg engine relative mass
eng, gr/NStatistic Amil + Heptyl 3 000-3 300 0,8-1,2RD-253 Proton, I stage Amil + Heptyl 1 635 000 3 040 1 280 0,8RD-0212 Proton, III stage Amil+ Heptyl 482 000 3 210 550 1,1
RD 261 C l 2 3 4 A il + H t l 2 800 000 2 990RD‐261 Cyclone-2 , 3, 4 Amil + Heptyl 2 800 000 2 990
Statistic O2 + kerosyne 3 020-3 500 1,05-1,2
RD-107 Soyuz, I stage O2 + kerosyne 1 000 000 3 020 1 160 1,16
RD-170 Energia, I stage O2 + kerosyne 8 000 000 3 310 10 700 1,34
RD 191 A I t O2 k 2 080 000 3 300 2 200 1 06RD-191 Angara, I stage O2 + kerosyne 2 080 000 3 300 2 200 1,06
Statistic H2 + O2 4 460-4 500 1,5-1,8
RD-0120 Energia, II stage H2 + O2 2 000 000 4 460 3 450 1,7
Rocket engine mass characteristics:
eng =meng / P = f (P) Rocket engine relative mass [ gr/N ]eng =meng / P = f (P) Rocket engine relative mass [ gr/N ]
Asdaslkjlk
6
RD 261
Engine for the first RD 855gstage of Cyclone LV Steering engine
for the first stage of Cycloneof Cyclone
PropellantsPropellants AmilAmil + + HeptylHeptyl PropellantsPropellants AmilAmil + + HeptylHeptylPropellantsPropellants AmilAmil + + HeptylHeptylVacuum thrustVacuum thrust , , N N 2 800 000 N 2 800 000 N Vacuum specific impulse, Vacuum specific impulse, m/sm/s 29902990Total burn duration, sTotal burn duration, s 115115
PropellantsPropellants AmilAmil HeptylHeptylVacuum thrustVacuum thrust , , N N 350 000 N 350 000 N Vacuum specific impulse, Vacuum specific impulse, m/sm/s 29202920Total burn duration, s 12Total burn duration, s 1277
Propellant Section mass characteristics: a m m ll t ti / ll t aps = m ps / m pr propellant section mass / propellant
mass
10
Thrust / Weight Ratio: n0
LV Name N m0 P0 nNNumber of stages
m0
Stage initial mass ,t
P0
Engine Thrust in vacuum, kN
n0
Initial Thrust/Weight ratio
P t 3 m o I= 716 0 9 520 1 33Proton 3 m o I= 716,0m o II= 260,0m o III= 94,0
9 5202 330
613
1,330,900,65
Zenit-2 2 m o I= 460,0 7 257 1,58Zenit 2m o II= 103,0 912 0,89
Soyuz 3 m o I= 306,0m o II= 96,0
III 32 0
4 065941304
1,330,980 95m o III= 32,0 304 0,95
Cosmos-3M 2 m o I= 109,0m o II= 22,5
1 480158
1,360,72
Rockot (SS-19) 2 m o I= 107,0 1 880 1,78Rockot (SS 19) 2 ,m o II= 19,7 255
,1,29
Dnepr (SS-18) 3 m o I= 211,0m o II= 53,7
III 6 3
4 610775
8
2,181,350 12m o III= 6,3 8 0,12
Average for statistics
I stageII stage
III stage
1,25…2.00,7…0.90,3…0,6
11
g , ,
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