It s been 71 days since my brother died, and I don t know if I m doing well over there?

It's been 71 days since my brother died, in fact, if he's over there, no one on our side knows whether it's good or not, and I hope that if he's over there, it will always be good.

It is said that the more you miss him here, he will be very uncomfortable over there, the happier you are, the better he is, because he doesn't want you to be in a bad mood over there, people can't be resurrected after death, although that's what to say, but we can't control our thoughts and thoughts, when you have reached the end of your life, you will meet, what it looks like over there, I don't know, however, some people can go over there, and they can help you go to see if your relatives are doing well.

Now that your brother has passed away, it is right to miss him and miss him as a relative, but if the sadness is excessive, then there is no need.

Think about this thing, the past is over, don't think too much, you should live a good life, live a good life, so that it can be better.

I know you miss your brother very much, like my brother died, it's been seven years, and I don't know how my brother is doing over there? That's what we live and think about for them.

I think you can know how you miss your loved ones, but you should turn your grief into strength and finish what your brother has not done.

Who knows if you are doing well or not, as long as you are alive, he will be well.

When people die, there is nothing, and there is no such thing as having a bad life over there.

Those who have passed away will be fine, please stop grieving and cheer up.

71 days after his brother's death, you will indeed miss him very much, and you will also think that he should be very good or not, don't worry. Otherwise, he will give you a dream.

Don't think so much about people who have passed away.

Discharge cooling is another type of convection cooling. Unlike regenerative cooling, the coolant used for exhaust cooling absorbs heat to the thrust chamber and is discharged out of the combustion chamber instead of entering the combustion chamber to participate in combustion. Direct drain coolant reduces the thrust chamber specific impulse, so the coolant flow for drain cooling needs to be minimized while only using drain cooling at the outlet section of the nozzle that is relatively less heated.

There is also radiative cooling, in which the heat flow is transferred from the combustion products to the thrust chamber, and then the heat is radiated by the thrust chamber wall to the surrounding space. Radiative cooling is characterized by simplicity and small structural mass. It is mainly used in the extension section of large nozzles and the thrust chamber of small thrust engines using high-temperature resistant materials.

When cooling in the thrust chamber of the tissue, a relatively low temperature liquid or gas protective layer is established on the surface of the thrust chamber wall to reduce the heat flow to the thrust chamber wall, reduce the wall temperature, and achieve cooling. Internal cooling is mainly divided into three methods: internal cooling (shield cooling), membrane cooling and diaphoretic cooling of head tissues. After the internal cooling measures are adopted in the thrust chamber, the mixing ratio near the wall of the combustion chamber is different from the optimal mixing ratio in the central area (in most cases, the near-wall layer rich in fuel is used) due to the need to reduce the temperature of the protective layer, resulting in the uneven distribution of the mixing ratio along the cross-section of the combustion chamber, so that the combustion efficiency is reduced to a certain extent.

Membrane cooling is similar to shield cooling in that it cools the thrust chamber wall by establishing a uniform and stable coolant film or air film protective layer near the inner wall surface, except that the coolant used to establish the protective layer is not injected by the injector, but is supplied through a special cooling belt. The cooling band is generally arranged in a cross-section of the combustion chamber or the convergence section of the nozzle. There can be several cooling bands along the length of the combustion chamber.

In order to improve the stability of the membrane, the coolant often flows through the gaps or small holes in the cooling belts, and when sweating is used, the thrust chamber wall or part of the inner wall is made of porous material with a pore diameter of tens of microns. Porous materials are usually sintered with metal powders or pressed with metal mesh. In this case, the number of pores per unit area is increased by making the micropores in the material as evenly distributed as possible.

The liquid coolant penetrates into the inner wall, creating a protective film that reduces the density of the heat transferred to the wall. When the flow rate of liquid coolant used for sweat cooling is above a certain threshold, a liquid film is formed near the wall of the thrust chamber. When the coolant flow rate is below the critical flow, the inner wall temperature will be higher than the coolant boiling point at the current pressure, and some or all of the coolant will evaporate, forming an air film.

In addition to the above thermal protection, there are other thermal protection methods such as: ablation cooling, thermal insulation cooling, hot melt cooling and composite protection of chamber walls. 3. Thermal protection scheme of high enthalpy gas generator Based on the above methods and the actual situation, the thermal protection method of high enthalpy gas generator is obtained.

The combustion chamber of a high-enthalpy gas generator differs from that of a liquid rocket engine, eliminating the front thrust chamber part, making its structure simpler and more effective. Then, the thermal protection involved is the thermal protection part of the combustion chamber wall. As the fuel enters the combustion chamber, it quickly decomposes and releases large quantities.

Or you go and see it and come back in a few days