On the Formation of Nitrogen Oxides During the Combustion of ...

C.1 Key Data of Experimental Setup
50
Deceleration level g
30
10
−10
4.6 4.8 5.0 5.2 5.4 5.6 s
Time t
Figure C.2: Deceleration of Drop Capsule Inside Deceleration Container (reprinted from
Ref. [104]). Time t is indicated with t 0 referring to the capsule release. The nominal
microgravity time of the ZARM drop tower is 4.74s. The catapult operation
mode was not used here [104].
solid propellant booster, boost adapter, S-30 second stage booster, payload,
and service system. Figure C.3 shows a typical acceleration profile of the VSB-
30 vehicle. Spin stabilization is achieved by using canted fins with a boost
motor, resulting in a roll rate of up to 3.0 rps at burnout. De-spin is started 56 s
after lift-off by a yo-yo mechanism (cf. Fig. C.3, x- and y-axis) and normally
stops 64 s after lift-off. The static loads caused by the spin of 3Hz can be calculated
based on the radial distance of the experiment components from the
z-axis [143, 272]. The vibrational loads inside the experimental payload remain
below an integrated RMS value of 3 g 0 in the spectrum of 15 to 2000 Hz.
Nonetheless, the payload components as well as the whole experiment module
are designed for 7.5 g 0 RMS for qualification and for 5.6 g 0 RMS for acceptance
on all three axes [66, 143, 196, 272].
Re-entry loads are generated during the re-entry phase of the sounding rocket
module (Figure C.4). The static loads during this phase can reach up to 50 g 0 in
each direction depending on the re-entry conditions of the payload at an altitude
of about 40 km and the center of gravity (COG). Against this background,
the design load for static acceleration should be in the range of 50 to 60 g 0 . The
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