Qualification Testing Phase of Satellite Structure - Finite Element Analysis for Satellite Structures - page 252

1. The integrity of structure elements with no major deformations.
2. Verifying mounting accuracy of ADCS equipment as described in the following
table. Mounting accuracy is performed after the first phase of static testing.

Verifying the functionality of the secondary structure is performed on the solar
array locking and releasing mechanisms after the second phase of static test.

6.1.3 Test Scheme

The satellite strength mockup is subjected to static strength tests for the below
mentioned design loading cases. During the tests, the design loads are simulated in
the considered cases. The design cases for Egyptsat-1 satellite are as follows:

• Case ''T 1a ''—satellite loading during transportation by automobile transport in a
standard container. The loads in this case exceed the loads of other transpor-
tation cases. The operational g-loads are:

n x ¼ 2; n y ¼ 1 2; n z ¼ 1 : 25;

• Case ''A''—satellite loading with maximal longitudinal g-load during orbital
injection. The operational g-loads are:

n x ¼ 0 : 1 0 : 5; n y ¼ 7 0 : 5; n z ¼ 0 :

In ''T 1a '' case, X-axis is directed along the motion of a transport means, Y-axis is
directed downward, and Z-axis completes the coordinate system to right-handed.
In ''A'' case, Y-axis is directed downward and coincides with the satellite's lon-
gitudinal axis.
The safety factors are adopted to be as follows:

• During autonomous ground operation for static component of g-load SF = 1.5
and for dynamic component SF = 2.0;
• For orbital injection SF = 1.3.

The test is performed on two phases. First phase is a simulation of the operation
loads without applying safety factors. The purpose of this simulation is to study the
effect of transportation and launching loads on mounting accuracy of ADCS
equipment. Second phase is performed by applying safety factors to test func-
tionality of the solar arrays locking and releasing mechanism under more severe
conditions. Each phase consists of two stages. First stage is to simulate trans-
portation conditions, while second phase is to simulate launching ones. Figures 6.3
and 6.4 illustrate the test setup for stage 1 and 2, respectively.