Solid ablation type magnetic plasma thruster
A magnetic plasma and thruster technology, applied in the field of plasma, can solve the problems of difficult miniaturization and integration, slow thrust response speed, complicated gas supply system, etc., and achieves easy integration, improved propulsion performance, and reduced overall The effect of weight and cost
Pending Publication Date: 2019-08-16
NAT UNIV OF DEFENSE TECH
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Problems solved by technology
[0004] Aiming at the problems of complex gas supply system, slow thrust response speed, severe cathode ablation and difficulty in miniaturization and integration in the prior art, the object of the present invention is to provide a solid ablation type magnetoplasma thruster device
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[0034] In order to make the purpose, technical solutions and advantages of the present disclosure clearer, the present invention will be further described in detail below in conjunction with specific embodiments and according to the accompanying drawings. It should be noted that, in the drawings or descriptions in the specification, the content not described and some English abbreviations are the content well known to those of ordinary skill in the art. Some specific parameters given in this embodiment are only for demonstration, and the values can be correspondingly changed to appropriate values in different implementations.
[0035] Such as Figure 1-3 The solid ablation magnetoplasma thruster shown includes components such as cathode body 1, anode body 2, solid propellant 3, power supply and spark plug 5, and these components effectively realize the ablation of solid propellant 3 and ionize to generate plasma Body, and plasma accelerated ejection and other processes, s...
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The invention provides a solid ablation type magnetic plasma thruster. The solid ablation type magnetic plasma thruster comprises a cathode body, an anode body, a solid propellant, a power supply anda spark plug, wherein the cathode body and the anode body are electrically connected to the power supply; an ablation cavity and a discharge cavity are enclosed between the cathode body and the anodebody; the solid propellant is positioned in the ablation cavity, and the two ends of the solid propellant are separately connected to the cathode body and the anode body at the two ends of the ablation cavity; a through hole which penetrates through the solid propellant from one end, corresponding to the anode body, of the ablation cavity to one end, corresponding to the cathode body, of the ablation cavity is formed in the solid propellant; the through hole communicates with the discharge cavity through a connecting channel; the spark plug is arranged in the connecting channel and is electrically connected to the power supply; and accelerating magnetic fields are arranged in the discharge cavity. Plasmas are subjected two twice accelerating processes, so that propelling performance is further effectively improved. The solid ablation type magnetic plasma thruster is applied to the field of aerospace technology and plasmas.
Description
technical field [0001] The invention relates to the field of aerospace technology and plasma, in particular to a solid ablation type magnetic plasma thruster. Background technique [0002] As a high-power space electric propulsion device, the magnetoplasma thruster mainly uses electromagnetic force and aerodynamic force to accelerate plasma to generate thrust. Compared with other electric propulsion devices, the magnetoplasma thruster has high exhaust velocity, high thrust, high efficiency and light weight, and has more advantages in the fields of large spacecraft orbit elevation, interplanetary flight and deep space exploration. [0003] However, magnetoplasma thrusters generally use hydrogen and lithium vapor as propellants, but hydrogen and lithium vapor are prone to chemical reactions in air, which has certain risks. At the same time, the use of gas propellant, the magnetic plasma thruster needs to be equipped with a device for storing gas propellant and a complex gas s...
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Login to View More IPC IPC(8): F03H1/00
CPCF03H1/0081
Inventor 欧阳吴建军张宇程玉强吴必琦杜忻洳李健谭胜
Owner NAT UNIV OF DEFENSE TECH