fluctuate. Moreover, because no throttling measures are taken and the gas consumption is large, the pressure relief valve will be in an overshoot state and cannot
regulate the pressure normally. Therefore, throttling measures should be taken to
stabilize the working pressure.
(2) Thrust Experiment With Orifice
According to the thrust requirement of the lateral force device of the aircraft, the
ventilation pressure is about 6:5 MPa and the size of the throttle orifice is
/1:15 $ /1:2 mm. The thrust experimental data are shown in Table 10.2.
The results show that when the throttle orifice is /1:15 $ /1:2 mm and the
working pressure is not less than 6:5 MPa, the thrust generated meets the thrust
requirements of the lateral force device.
Comparing the measured value with the theoretical value, see Table 10.3. The
thrust measured by experiment is less than that by theoretical calculation, which is
caused by pressure loss, flow loss, and velocity loss in pipeline. It shows that the
experimental results are in good agreement with the theoretical analysis.
High pressure
gas source
Pressure gauge 1
Pressure gauge 2
Pressure relief
valve
Experimental cabin
Thrust Sensor
Signal amplifier
Data Acquisition
Computer
Fig. 10.11 Schematic diagram of thrust experimental
Table 10.2 Thrust experimental data of different throttle orifices
Throttle orifice
size/mm
Working
pressure/MPa
Thrust
data/N
Throttle orifice
size/mm
Working
pressure/MPa
Thrust
data/N
/1:1
6.6
4.5
/1:2
6.6
5
/1:15
6.6
4.8
/1:25
6.4
5.6
Table 10.3 Comparison of measured and theoretical values
Throttle orifice size/mm
Working pressure/
MPa
Computational
thrust/N
Experimental
thrust/N
/1:15
6.6
6.94
4.8
174
10 Application of Aerodynamic Technology in Attitude Control …