6 results about "Monopropellant" patented technology

The application discloses an on-orbit use method of a green single-component thruster, and the single-component thruster structure comprises five parts of an injector, an anti-inversion functional material, a catalytic bed, a nozzle and a thermal control assembly, wherein the thermal control assembly comprises an armored heater, an armored thermistor and a multilayer thermal insulation assembly. The application provides the on-orbit use method of the green single-component thruster containing the anti-inversion functional material, and solves the technical problem of the warm start life of the green single-component thruster through reasonable working condition design, and the green single-component thruster is successfully applied to micro-nano satellites.

A system for generating hot, high-pressure exhaust gas for thrust includes an energetic powder monopropellant, wherein each particle of powder is comprised of a combination of oxidizer and fuel in a ratio suitable for combustion; and a rocket motor for combusting the monopropellant, said rocket motor comprising a container for storing the monopropellant, and a unitary feeder-combustor, wherein the unitary feeder-combustor is configured to feed the powder monopropellant from the container and to combust the powder monopropellant therein without consumption of air, thereby generating hot, high-pressure exhaust gas, generating thrust.

The invention provides a regenerative cooling nitrous oxide single-component thruster thermal management method and system, and relates to the technical field of aerospace propulsion, and the method comprises the steps: obtaining catalytic bed temperature distribution and propellant flow data, obtaining a thermal state parameter through nonlinear mapping, and obtaining a thermal state parameter; the rotational flow intensity is determined, main inlet axial flow and auxiliary inlet tangential flow are coordinated to form a rotational flow field, a thermal boundary layer is destroyed through rotational flow, so that heat exchange is enhanced, and the heat exchange state is determined; the flow distribution proportion of the main inlet and the auxiliary inlet is dynamically adjusted through a self-adaption PID control algorithm in combination with the inner wall face heat flow and a catalytic bed temperature signal, and the real-time flow proportion is obtained; and predicting a thermal runaway risk level through a fuzzy logic decision maker based on the ratio, updating control parameters and re-executing flow regulation according to the thermal runaway risk level, forming closed-loop management, and realizing efficient and reliable thermal management of the thruster. The thermal management accuracy and reliability of the thruster under variable working conditions are improved.

The application provides a hydroxylamine nitrate-based monopropellant and a preparation method thereof, and comprises the following components with mass percentage: HAN: 50%-70%; alcohol: 14%-25%; functional additive: 14%-35%; and water: 1%-5%; wherein the functional additive comprises high-energy additive and cosolvent additive, the mass percentage of the high-energy additive is 13.5%-34.8%, and the mass percentage of the cosolvent additive is 0.2%-0.5%. The hydroxylamine nitrate-based monopropellant provided by the application has the characteristics of green, low toxicity, high specific impulse performance, low sensitivity, clean and non-polluted combustion products and the like.

A system for generating hot, high-pressure exhaust gas for thrust includes an energetic powder monopropellant, wherein each particle of powder is comprised of a combination of oxidizer and fuel in a ratio suitable for combustion; and a rocket motor for combusting the monopropellant, said rocket motor comprising a container for storing the monopropellant, and a unitary feeder-combustor, wherein the unitary feeder-combustor is configured to feed the powder monopropellant from the container and to combust the powder monopropellant therein without consumption of air, thereby generating hot, high-pressure exhaust gas, generating thrust.

The invention discloses an automatic catalyst filling system for a single-component thrust chamber. The automatic catalyst filling system comprises a material taking device, a catalyst storing and taking device and a vibration device, wherein the material taking device takes out a thrust chamber and decomposition chamber assembly and places the thrust chamber and decomposition chamber assembly on the catalyst storing and taking device or the vibration device; the catalyst access device pours a catalyst with a set weight into the thrust chamber and decomposition chamber assembly; and the vibration device is used for knocking and vibrating the thrust chamber decomposition chamber assembly. According to the invention, automatic filling of the catalyst in the thrust chamber is realized, so that the production efficiency is improved, the labor intensity is reduced, and the quality consistency of products is improved.