ESA Document - Emits - ESA

s
Altitude (km)
Dynamic Pressure (Pa)
600
500
400
300
200
100
0
300
250
200
150
100
50
Time (s) Altitude (km) Event
0.0 0.000 Vertical Take off
3.0 0.010 Kick turn manoeuvre
6.3 0.045
Starts Gravity Turn (Flight with aoa = 0
degrees)
316.8 74.223 1st Stage Burn Out. End of gravity turn
321.8 75.505 1st Stage Jettisoning
326.8 76.740 2nd Stage First Burn
732.4 98.960 Starts Coast Arc
4199.8 500.219 2nd Stage First Burn
4224.3 500.195 Final Orbit
Table 4-51: MAV ascent trajectory. Sequence of events
Altitude (km)
Velocity (km/s)
1
0.5
0
0 1000 2000 3000 4000 5000
Time (s)
0
0
0 100 200 300 400 500
Time (s)
Dynamic Pressure (Pa)
Heat Flux (kW/m2)
4.5.2 GNC and rendezvous & docking
4
3.5
3
2.5
2
1.5
160
140
120
100
80
60
40
20
Inertial Velocity (km/s)
Heat Flux (kW/m2)
Apogee, perigee altitude [km]
Load Factor (Earth G)
600
500
400
300
200
100
0
2.5
2
1.5
1
0.5
Apogee (km)
Perigee (km)
Thrust (kN)
0 1000 2000 3000 4000
0
5000
Time (s)
HMM
Assessment Study
Report: CDF-20(A)
February 2004
page 366 of 422
300
250
200
150
100
0
0
0 1000 2000 3000 4000 5000
Time (s)
Figure 4-103: Baseline trajectory and flight environment
Load Factor (Earth G)
Total Mass (Tons)
From a GNC point of view, the ascent vehicle will cover two mission arcs:
• Ascent from the surface of Mars
• Rendezvous and docking in Mars orbit with the orbiter
Both phases have an impact in the design of the GNC subsystem. This part of the report is
devoted to the rendezvous phase only.
50
25
20
15
10
5
Thrust (kN)
Total Mass (Tons)