Questions tagged [solid-fuel]
Questions about solid fuels. The rockets that use them, the fuels that are burned, and the vendors that make them.
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What should be the fuel mass of a hypersonic (Mach 7) rocket using APCP fuel that would deliver a 50 gram payload?
Well, I used this rocket calculator besides asking ChatGPT and BingGPT and both gave me similar answers where the amount of fuel would be around 300 to 4000 grams of APCP fuel. And 30 to 100 grams for ...
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Computing Flight Characteristics for Different Propellant Grain Geometries?
Consider the following image:
I am interested in mathematically accounting for some of these different geometries but have had little success so far in finding how this can be done. The first thought ...
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What is the A in the mass flow rate formula for solid rocket propellants? How do I get the chamber pressure? [closed]
I believe the mass flow rate formula for solid rocket motors is:$$\dot{m}=p_pA_br$$ What is $A_b$ in this case. Is it the cross-sectional area of the hole in the grain? What is there is a nozzle? What ...
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How do you find the propellant mass needed to reach an specified altitude? (altitude at end of burn plus altitude during coast)
This question is basically entirely explained in the title, but I'll explain it more so this question doesn't get shut down. Basically, does anyone have an equation to find the propellant mass(solid) ...
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Can Solid Rockets (Aluminum-Ice) have an advantage when designing light space-tug for LEO?
This is a new subject for Space Industry – heavy spacecraft (1200-ton) in LEO that have to burn hundreds of tons of propellant to get going to their destination.
It looks inefficient to launch 7+ fuel ...
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SLS SRB sound suppression system
The Shuttle, in addition to the water deluge system, used a series of red nylon bags filled with water at the base of each SRB for additional sound suppression. Does the SLS, whose boosters produce ~...
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For Shuttle SRB solid fuel perforations, what is the shape of the double-truncated-cone?
I understand the 11-point star perforations in the solid fuel in the top-most SRB section. Several articles say that the remaining sections had a double-truncated-cone perforation.
Is my illustration ...
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How do spin-stabilized rockets conduct gravity turns?
I was reading this NTRS document about a spin-stabilized solids-only small launcher. The paper mentions that the proposed design (called 428A) will be spin-stabilized during launch and gravity turn. ...
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Why was a solid fuel rocket chosen as the 3rd stage for the Europa Clipper launch?
According to Wikipedia https://en.wikipedia.org/wiki/Star_48#Use_on_New_Horizons a solid fuel Star 48 “kick stage” was chosen as the 3rd stage in the launch of Europa Clipper.
Solid fuel rockets have ...
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"Semi" hybrid rocket? Throttleable solid fuel rocket?
Are there any published examples of "hybrid" rockets that used a propellant grain of mixed solid fuel and oxidizer where the injected component was only needed to sustain the burn without ...
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Thrust to weight of large solid fuel boosters
I have been looking at examples of large solid fuel rocket boosters or first stages used for space launch, such as P80, the Space Shuttle SRB, the various versions of Graphite-Epoxy-Motor, the solid ...
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Why do the walls of a solid rocket booster not glow red hot?
After ignition the walls of the SRB are separated from the "reaction chamber" by solid rocket fuel. But as the burn progresses, more and more fuel is used up and so the isolation from the ...
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What is the most powerful solid rocket fuel (highest isp) and it's combustion temperature
I wanted to know what the most power full solid rocket fuel is. I do not mean theoretical once like metallic hydrogen.
Are solid rocket fuel mixtures prepared in a non-ideal mixture? In other words, ...
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Paraffin wax in solid motors
Paraffin wax is often used in (at least hypothetical) hybrid motors, mostly with N2O or HTP. Could it not, however, be used in a conventional configuration? Running at O/F of 12.4, 60 bar chamber ...
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What is the difference between the solid fuel Boosters of the Shuttle and Artemis?
The Shuttle boosters had 4 segments and Artemis has 5. What are the differences in total mass, thrust and burn time? Is the thrust profile (thrust over time) the same?