ESA Document - Emits - ESA
ESA Document - Emits - ESA ESA Document - Emits - ESA
s HMM Assessment Study Report: CDF-20(A) February 2004 page 372 of 422 During this phase, the chaser will make a change of plane manoeuvre to correct the differences. Table 4-52 shows a simulation in which chaser and target are separated by a true anomaly of 12.2 degrees. Target Chaser Semi major axis (km) 3897.515 3843.515 Eccentricity 0 0 Inclination (degrees) 47 45 RAAN (degrees) 269.0307 267.0307 Argument of perigee (degrees) 25.956687 25.956687 True anomaly (degrees) 122.28026 110 Table 4-52: Simulation results The result of the plane change manoeuvre can be seen in Figure 4-108. Z (m) 3 2 1 0 -1 -2 -3 4 x 10 6 x 10 6 2 Master and Flyer Trajectories 3D in Corotating Frame 0 Y (m) -2 -4 -4 -2 0 X (m) 4 2 x 10 6 Master Flyer Figure 4-108: Plane change manoeuvre results The corresponding inclination plot can be seen in Figure 4-109. This change of plane has a first Impulse at 1593 seconds. The corresponding DeltaV is negligable. Then a second Impulse is given at 1617 seconds with the following DeltaV of [27 115 -82] m/s
s Inclination (deg) 47.5 47 46.5 46 45.5 The total dV is143.5 m/s. Master and Flyer Inclination Evolution Master Flyer 45 0 2000 4000 6000 Time (s) 8000 10000 12000 4.5.2.4.1.1 Intermediate rendezvous Figure 4-109: Inclination evolution HMM Assessment Study Report: CDF-20(A) February 2004 page 373 of 422 After any plane change, the chaser is at 50 km below the target and at 140 km behind it. A Hohmann transfer is executed to move the Orbiter towards the MAV, from a point 20 km behind the target and in V-bar (see Figure 4-110). For the intermediate rendezvous, a trade-off was mad between several substrategies: • To place the MAV above and ahead drifts backwards towards the target • To place the MAV below and behind drifts in front of the target • To place the MAV below and ahead drifts the MAV in from of the orbiter Finally, the last substrategy was selected: To place the MAV below and ahead. It is a quick transfer based on Shuttle guidance to ISS docking port that has very good manual backup features. After the Hohmann manoeuvre, a tangential transfer in V-bar is executed to place the chaser 1 km ahead of the target maintaining it still in V-bar. At that point a station keeping is commanded and a series of test start. These hold points will allow the astronauts to verify the authorisation to proceed for the next phase. The hold point is expensive in terms of fuel. It accounts for for the following tasks: • Checking out subsystems. • Occurrence for the sub-solar angle: Earth-orbiter-Sun angle more than 5 degrees. • Communication with Earth for the ATPs (Authorisation to Proceed) to the next point.
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s<br />
HMM<br />
Assessment Study<br />
Report: CDF-20(A)<br />
February 2004<br />
page 372 of 422<br />
During this phase, the chaser will make a change of plane manoeuvre to correct the differences.<br />
Table 4-52 shows a simulation in which chaser and target are separated by a true anomaly of<br />
12.2 degrees.<br />
Target Chaser<br />
Semi major axis (km) 3897.515 3843.515<br />
Eccentricity 0 0<br />
Inclination (degrees) 47 45<br />
RAAN (degrees) 269.0307 267.0307<br />
Argument of perigee (degrees) 25.956687 25.956687<br />
True anomaly (degrees) 122.28026 110<br />
Table 4-52: Simulation results<br />
The result of the plane change manoeuvre can be seen in Figure 4-108.<br />
Z (m)<br />
3<br />
2<br />
1<br />
0<br />
-1<br />
-2<br />
-3<br />
4<br />
x 10 6<br />
x 10 6<br />
2<br />
Master and Flyer Trajectories 3D in Corotating Frame<br />
0<br />
Y (m)<br />
-2<br />
-4<br />
-4<br />
-2<br />
0<br />
X (m)<br />
4<br />
2<br />
x 10 6<br />
Master<br />
Flyer<br />
Figure 4-108: Plane change manoeuvre results<br />
The corresponding inclination plot can be seen in Figure 4-109. This change of plane has a first<br />
Impulse at 1593 seconds. The corresponding DeltaV is negligable. Then a second Impulse is<br />
given at 1617 seconds with the following DeltaV of [27 115 -82] m/s
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