Chapter 10
Application of Aerodynamic Technology
in Attitude Control of Aerocraft
Since the emergence of aircraft attitude control technology in 1952, it has been
common to use jet reaction force for attitude control of airplane or satellite, but it is
rare to use jet reaction force for missile aircraft. Attitude control of missile vehicle
includes attitude stabilization and attitude maneuver, which can realize pitch, yaw,
and roll of missile vehicle. The former is to maintain the existing attitude, while the
latter is to redirect the missile from one attitude to another. At present, the attitude
control of aircraft mostly adopts aerodynamic control and thrust vector control. The
former is based on the principle of relativity of motion and the basic law of gas
flow, using rudder surface and air resistance to control flight direction. Its control is
related to flight speed, flight altitude, and the shape of the aircraft. The flight altitude
of the aircraft is limited in the atmosphere, and it is difficult to satisfy the attitude
control under the condition of low speed and low dynamic pressure. The latter
controls the flight of aircraft by deflecting the nozzle, changing the direction of
exhaust gas from engine, and realizes the attitude control by utilizing thrust generated by engine. However, the design of this type of attitude control structure is
complex, and the sealing requirements for the rotating or swinging parts of the
nozzle are high.
In this chapter, the attitude control method of aircraft using jet lateral force is
introduced, including the structure of aerodynamic system, control method, aircraft
direction control scheme, and key technology. The thermodynamic and dynamic
models of Laval nozzle are emphatically established, and the distributions of
velocity field, pressure field, and temperature field inside Laval nozzle are analyzed,
which can be used as theoretical basis for nozzle structure design and process
design.
© Springer Nature Singapore Pte Ltd. and Shanghai Scientific
and Technical Publishers 2020
Y. Yin, High Speed Pneumatic Theory and Technology Volume II,
https://doi.org/10.1007/978-981-15-2202-4_10
163
Application of Aerodynamic Technology
in Attitude Control of Aerocraft
Since the emergence of aircraft attitude control technology in 1952, it has been
common to use jet reaction force for attitude control of airplane or satellite, but it is
rare to use jet reaction force for missile aircraft. Attitude control of missile vehicle
includes attitude stabilization and attitude maneuver, which can realize pitch, yaw,
and roll of missile vehicle. The former is to maintain the existing attitude, while the
latter is to redirect the missile from one attitude to another. At present, the attitude
control of aircraft mostly adopts aerodynamic control and thrust vector control. The
former is based on the principle of relativity of motion and the basic law of gas
flow, using rudder surface and air resistance to control flight direction. Its control is
related to flight speed, flight altitude, and the shape of the aircraft. The flight altitude
of the aircraft is limited in the atmosphere, and it is difficult to satisfy the attitude
control under the condition of low speed and low dynamic pressure. The latter
controls the flight of aircraft by deflecting the nozzle, changing the direction of
exhaust gas from engine, and realizes the attitude control by utilizing thrust generated by engine. However, the design of this type of attitude control structure is
complex, and the sealing requirements for the rotating or swinging parts of the
nozzle are high.
In this chapter, the attitude control method of aircraft using jet lateral force is
introduced, including the structure of aerodynamic system, control method, aircraft
direction control scheme, and key technology. The thermodynamic and dynamic
models of Laval nozzle are emphatically established, and the distributions of
velocity field, pressure field, and temperature field inside Laval nozzle are analyzed,
which can be used as theoretical basis for nozzle structure design and process
design.
© Springer Nature Singapore Pte Ltd. and Shanghai Scientific
and Technical Publishers 2020
Y. Yin, High Speed Pneumatic Theory and Technology Volume II,
https://doi.org/10.1007/978-981-15-2202-4_10
163