3results about How to "Reduce heat flow" patented technology

The invention belongs to the field of hypersonic active flow control, and discloses a drag reduction and heat protection system and method for a hypersonic aircraft, and the method combines two active flow control methods of energy deposition and magnetofluid flow control. The excellent drag reduction characteristic of energy deposition can bring a good drag reduction effect to an aircraft, meanwhile, energy deposition can serve as an auxiliary ionization technology, and the magnetic control effect of magnetic fluid flow control is improved by improving the fluid conductivity; due to the outstanding thermal protection performance of magnetic fluid flow control, an excellent thermal protection effect is brought to the aircraft after heat flow increase in a part of time periods caused by the energy deposition process is treated; meanwhile, the problems of resistance impact and oscillation caused by pulse energy deposition are fully inhibited under the action of the magnetic field Lorentz force; by the adoption of the method, a better hypersonic speed drag reduction and heat protection effect is achieved, the resistance borne by the hypersonic speed aircraft can be effectively reduced, the heat protection capacity of the aircraft is improved, and the method has wide application prospects.

This invention relates to a drag-reducing and heat-cooling device combining a partitioned base with a liftable central structure. The device includes a central base structure, a peripheral base structure, a drive mechanism, and a cold air flow control system. The central base structure comprises an arc-shaped surface and a lifting rod. The arc-shaped surface is located at the center of the peripheral base structure surface. When the lifting rod is compressed, the arc-shaped surface remains flush with the peripheral base structure, forming an integrated heat shield. The cold air flow control system includes a gas pipeline, a cold air storage cylinder, and an ejector device. Cold air is uniformly injected from the ejector device through the gas pipeline and the lifting rod onto the surface of the central base structure, forming a gas film. The drive mechanism is located inside the reentry capsule and drives the lifting rod to extend or retract into the reentry capsule, thereby raising or lowering the arc-shaped surface of the central base structure. This invention effectively reduces the impact of heat flow while reducing aerodynamic load, improving the safety and reliability of reentry.

The invention provides a temperature calibration method and device for different reaction plates, and the method comprises the steps: enabling a temperature sensor to pass through a through hole in a plug, enabling a lead of the temperature sensor to be tightly attached to the inner wall of a reaction hole in a spiral manner, enabling a temperature measurement head on the temperature sensor to be in contact with the bottom of the reaction hole, and enabling the temperature measurement head to be in contact with the bottom of the reaction hole; the upper part of the reaction hole is plugged by a plug, and an insulating layer is arranged outside the wire; putting the reaction plate of which the reaction holes are plugged with the temperature sensors into to-be-tested equipment, setting a heating program of the to-be-tested equipment, and starting to run; and transmitting and processing the real-time temperature signal of the bottom of the reaction hole by the temperature measuring head to obtain a real-time temperature value. The device can adapt to different reaction plates, and the temperature measurement accuracy can be improved.