Methylsilane CH6Si seems to have some useful properties for rocket fuel:

• High hydrogen content, 6 atoms per molecule, 13% of overall mass,
• High combustion energy, -2612KJ/mol or 56.8 MJ/kg (better than methane 55MJ/kg),
• Decent liquid density, 0,628kg/l, (better than liquid methane 0.422kg/l), 11% higher hydrogen content per volume than liquid hydrogen itself,
• non cryogenic, self pressurizing storage, 14 bar of pressure at 21°C, critical temperature 79.3°C,
• low average molar mass of gaseous stoichiometric combustion products 21.7g/mol (better than methane 23.2 g/mol). Fuel rich combustion has even lower average gas mass because CH6Si decompose to SiC and 3xH2.

But there are some drawbacks:

• solid particles of SiO2 and traces of SiC in exhaust, but less solid residue in exhaust than in solid fuels,
• possible pyrophoric in high humidity atmosphere, but non pyrophoric in standard conditions,
• non toxic but harmful to inhalation and skin exposure.

Considering all of data, they show promise, but are there any works related to it's use in rocketary?

Methylsilane CH₆Si seems to have some useful properties for rocket fuel:

• high hydrogen content, 6 atoms per molecule, 13% of overall mass;
• high combustion energy, -2612 KJ/mol or 56.8 MJ/kg (better than methane 55 MJ/kg);
• decent liquid density, 0,628 kg/l (better than liquid methane 0.422 kg/l); 11% higher hydrogen content per volume than liquid hydrogen itself;
• non cryogenic, self pressurizing storage, 14 bar of pressure at 21°C, critical temperature 79.3°C;
• low average molar mass of gaseous stoichiometric combustion products 21.7 g/mol (better than methane 23.2 g/mol). Fuel rich combustion has even lower average gas mass because CH₆Si decomposes to SiC and 3H₂.

But there are some drawbacks:

• solid particles of SiO₂ and traces of SiC in exhaust, but less solid residue in exhaust than in solid fuels;
• possibly pyrophoric in high humidity atmosphere, but non pyrophoric in standard conditions;
• non toxic, but harmful to inhalation and skin exposure.

Considering all of data, they show promise, but are there any works related to its use in rocketry?

Methylsilane CH6Si seems to have some useful properties for rocket fuel:

• High hydrogen content, 6 atoms per molecule, 13% overall,
• High combustion energy, -2612KJ/mol or 56.8 MJ/kg (better than methane 55MJ/kg),
• Decent liquid density, 0,628kg/l, (better than liquid methane 0.422kg/l), 11% higher hydrogen content per volume than liquid hydrogen itself,
• non cryogenic, self pressurizing storage, 14 bar of pressure at 21°C, critical temperature 79.3°C,
• low average molar mass of gaseous stoichiometric combustion products 21.7g/mol (better than methane 23.2 g/mol). Fuel rich combustion has even lower average gas mass because CH6Si decompose to SiC and 3xH2.

But there are some drawbacks:

• solid particles of silicon dioxide SiO2 in exhaust, but less solid residue in exhaust than in solid fuels,
• possible pyrophoric in high humidity atmosphere, but non pyrophoric in standard conditions,
• non toxic but harmful to inhalation and skin exposure.

Considering all of data, they show promise, but are there any works related to it's use in rocketary?

Methylsilane CH6Si seems to have some useful properties for rocket fuel:

• High hydrogen content, 6 atoms per molecule, 13% of overall mass,
• High combustion energy, -2612KJ/mol or 56.8 MJ/kg (better than methane 55MJ/kg),
• Decent liquid density, 0,628kg/l, (better than liquid methane 0.422kg/l), 11% higher hydrogen content per volume than liquid hydrogen itself,
• non cryogenic, self pressurizing storage, 14 bar of pressure at 21°C, critical temperature 79.3°C,
• low average molar mass of gaseous stoichiometric combustion products 21.7g/mol (better than methane 23.2 g/mol). Fuel rich combustion has even lower average gas mass because CH6Si decompose to SiC and 3xH2.

But there are some drawbacks:

• solid particles of SiO2 and traces of SiC in exhaust, but less solid residue in exhaust than in solid fuels,
• possible pyrophoric in high humidity atmosphere, but non pyrophoric in standard conditions,
• non toxic but harmful to inhalation and skin exposure.

Considering all of data, they show promise, but are there any works related to it's use in rocketary?

Methylsilane CH6Si seems to have some useful properties for rocket fuel:

• High hydrogen content, 6 atoms per molecule, 13% overall,
• High combustion energy, -2612KJ/mol or 56.8 MJ/kg (better than methane 55MJ/kg),
• Decent liquid density, 0,628kg/l, (better than liquid methane 0.422kg/l), 11% higher hydrogen content per volume than liquid hydrogen itself,
• non cryogenic, self pressurizing storage, 14 bar of pressure at 21°C, critical temperature 79.3°C,
• low average molar mass of gaseous combustion products 21.7g/mol (better than methane 23.2 g/mol)

But there are some drawbacks:

• solid particles of silicon dioxide SiO2 in exhaust, but less solid residue in exhaust than in solid fuels,
• possible pyrophoric in high humidity atmosphere, but non pyrophoric in standard conditions,
• non toxic but harmful to inhalation and skin exposure.

Considering all of data, they show promise, but are there any works related to it's use in rocketary?

Methylsilane CH6Si seems to have some useful properties for rocket fuel:

• High hydrogen content, 6 atoms per molecule, 13% overall,
• High combustion energy, -2612KJ/mol or 56.8 MJ/kg (better than methane 55MJ/kg),
• Decent liquid density, 0,628kg/l, (better than liquid methane 0.422kg/l), 11% higher hydrogen content per volume than liquid hydrogen itself,
• non cryogenic, self pressurizing storage, 14 bar of pressure at 21°C, critical temperature 79.3°C,
• low average molar mass of gaseous stoichiometric combustion products 21.7g/mol   (better than methane 23.2 g/mol). Fuel rich combustion has even lower average gas mass because CH6Si decompose to SiC and 3xH2.

But there are some drawbacks:

• solid particles of silicon dioxide SiO2 in exhaust, but less solid residue in exhaust than in solid fuels,
• possible pyrophoric in high humidity atmosphere, but non pyrophoric in standard conditions,
• non toxic but harmful to inhalation and skin exposure.

Considering all of data, they show promise, but are there any works related to it's use in rocketary?