TNAG-2109-FCO40-3008-Outer-Space-Act-1986-extension-to-Hong-Kong-1990 — Page 85

1.

L

-L

L

indicated in the The required apogee bias shall be

value Use

the final the to

LM-3 and Application

it can be selected 8 months before launch so that incorporated in the final mission analysis.

The standard deviation values of the injection for the orbit parameters are as follows:

Semimajor axis (a) Eccentricity (e) Inclination (i)

Perigee argument (W) Ascending node (n) Perigee altitude (Hp) Apogee altitude (Ha)

Injection Condition

50 km TBD

0.007 deg 0.29 deg 0.14 deg

6 km 94 km

errors

-L

1.2

The spin rate shall be 5.7 rpm + 10% counter-clockwise at rotation (when looking top-down). separation is TBD. These conditions are further defined in Section IV of LM-3 Users Manual.

Orientation

-L

L

1.3

Spacecraft Mass Properties

All Spacecraft Mass properties are preliminary only; final values will be provided after a U.S.

State export licence for the Spacecraft

of

approved.

The spacecraft

Department has been

in the described

following Spacecraft,

sub- but

paragraphs is similar to the client's

has larger fuel tanks.

1.3.1

Mass

The separated mass will not exceed 1325 kg, lift-off mass is the same as the separated mass.

Inertias on Three Axes with Tolerance

and the

L

1.3.2

The

following

define

the inertias

spacecraft axes:

about

the

three

Iz = 500.9 + 5 kg-m2 (369.4 ± 3.69 slug-ft2)

IX = +

445.4 ± 4.4 kg-m2

Iy

= 469.3 ± 4.7 kg-m2

(328.5+ 3.25 slug-ft2)

(346.14 ± 3.47 slug-ft2)

1

ANNEX I

2

:

13