Surface plasmon DC pulse attitude control and propulsion assisting system for hypersonic aircraft

Abstract

The invention relates to a surface plasmon DC pulse attitude control and propulsion assisting system for a hypersonic aircraft, and belongs to the technical field of aircraft power. Four pairs of electrode strips arranged at upper, lower, left and right parts are vertically spaced apart and embedded in the outer surface of the aircraft in the motion direction; each pair of electrode strips consists of an IN1 electrode strip and an IN2 duality electrode strip; propulsion assisting and attitude control can be realized by virtue of surface plasmon DC pulses of the aircraft; two sets of DC pulse plasmon drives are driven; the surface of the hypersonic aircraft is divided into four parts comprising the upper, lower, left and right parts; each of the parts is provided with two kinds of electrodes which are IN1 and IN2 electrodes; the two electrodes of each set are contrary to each other in voltage, pulse and polarity; and a double-DC pulse plasmon drive is driven. A DC pulse plasmon driven PWM modulation system takes an AT89S52 single-chip microcomputer as a control core, and consists of a command input module, an LED display module and a DC pulse power amplification drive module, thereby realizing digital precision control, completely changing the propulsion mode of the aircraft, saving more energy, eliminating the source of surface resistance of the aircraft in principle, and achieving great development potential.

Description

technical field [0001] The invention relates to a hypersonic vehicle surface plasma DC pulse attitude control auxiliary propulsion system, which belongs to the technical field of aerodynamics. Background technique [0002] Technical difficulties of hypersonic vehicles: (1) Power system: currently used is a jet engine, which usually consists of an inlet, a compressor, a combustion chamber, a turbine and an exhaust nozzle. Since the high-temperature turbine is installed on the same shaft as the compressor, it also drives the compressor to rotate, thereby repeatedly compressing the inhaled air. The high-temperature and high-pressure gas flowing out of the high-temperature turbine continues to expand in the tail nozzle, and is discharged backward at high speed from the tail nozzle. This velocity is much greater than the velocity of the airflow entering the engine, creating a reactive thrust against the engine, propelling the aircraft forward. Due to the complexity of the mecha...

AI Technical Summary

Problems solved by technology

The main disadvantages of ablative heat protection are single use and aerodynamic shape change due to ablation

The latter will affect the stability, landing point accuracy and reentry maneuver flight of the reentry spacecraft, as well as the lift resistance, stability and maneuverability of the cruise vehicle

[0006] Judging from the current situation, after the hypersonic vehicle reaches a certain speed, it encounters a technical bottleneck. Due to the existence of the thermal barrier, the energy of the engine is greatly consumed, and it becomes more and more difficult to further increase the speed of motion.

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