V—2 ROCKETS—KRAUSE 
over most of the trajectory. In addi- 
tion there have been cases where a 
definite yaw and pitch have been ob- 
served. The exact knowledge of the 
missile’s attitude after burn-out is not 
complete at present but is the subject 
of an intensive study. 
Fi igure 1 shows me trajectory of the 
V-2 as it was plotted for a firing on 
March 7, 1947. A study of this tra- 
TRAJECTORY 
ALTITUDE ABOVE SEALEVEL IN KILOMETERS 
of SE iia 0 
HOR 19, 20,20, Pa nfQ. 0 g 
IN KILOMETERS 
191 
ing and adjusting the equipment. It 
is not a standard device but usually 
undergoes special modification for each 
flight, depending on the particular ex- 
periments involved. 
Data Recovery 
Two general methods of data re- 
covery are used. One involves tele- 
metering (radio transmissions of data 
ALTITUDE AND VELOCITY VS. TIME 
50 100 150 200 250 300 350 400 
TIME AFTER LAUNCHING IN SECONDS 
7 MARCH TRAJECTORY INFORMATION 
Ficure 1. Trajectory curves for March 7, 1947, flight. 
jectory brings out a second shortcom- 
ing of the rocket in general, that is 
the short time that it spends in free 
space. It can be seen, for example, 
that the time the rocket spends above 
50 km. is about 5 minutes. It is there- 
fore necessary to complete all experi- 
ments in this limited time. 
To conduct work in the V—2 it was 
necessary to design and build a special 
warhead with access doors for install- 
817369—49——14 
from the missile to the ground); the 
other involves direct recording of in- 
formation on film or other recorders, 
followed by physical recovery of the 
equipment after impact. 
Of these two general methods by far 
the more successful has been that of 
telemetering. The telemetering sys- 
tem which has been employed in all 
V-2 firings is a 23-channel pulse time 
modulated system designed at the 
