SuomiKaataa2

Hypergolic vs non hypergolic ignition in rocket engines An early hypergolic-propellant rocket engine, the Walter 109-509A of 1942–45; source: Wiki Hypergolic ignition uses propellants that ignite on contact, eliminating the need for a separate igniter, whereas non-hypergolic ignition requires an external ignition source like an electric spark or pyrotechnic to start the combustion. Hypergolic systems are simpler, more reliable for multiple restarts, and can use storable, room-temperature propellants. Non-hypergolic systems, often using cryogenic propellants like liquid oxygen, offer higher performance but require more complex ignition hardware. Common pairs of non-hypergolic propellants are LOX/RP-1, LOX/LH2 and LOX/CH4. Thruster with Igniter vs. Hypergolic Ignition   How ignition works? In the case of hypergolic ignition, the fuel and oxidizer components of a propellant spontaneously ignite upon contact, eliminating the need for an external ignition source. This characteristic sim...

Kerosene as Rocket Fuel, RP-1 Kerosene, specifically highly refined kerosene like RP-1, is a common rocket fuel, called RP-1 (Rocket Propellant-1). RP-1 is a mixture of long chain hydrocarbons that has been purified to remove unstable or contaminant components.  RP-1 fuel. Source: Wiki RP-1 is a refined petroleum distillate similar to aviation kerosene but processed to strict specifications. Compared to ordinary kerosene it contains fewer unsaturated compounds and has tighter limits on impurities and sulfur.  Specific properties of RP-1: Density: At ambient temperatures (around 15°C to 20°C), RP-1's density is about 810 kg/m³ (0.81 g/cm³). Density is a key factor in rocket design for determining the volume of fuel needed.  Freezing Point: RP-1's freezing point is well below normal operating temperatures, -60°C or lower. This is a desirable property for a storable propellant, as it doesn't require cryogenic temperatures like liquid hydrogen.  Boiling Range: As a compl...

Rocket fuel oxidizers Rocket propellants are substances that produce the necessary reaction mass to generate thrust when expelled from a rocket engine.  The energy required can either come from the propellants themselves, as with a chemical rocket, or from an external source, as with ion engines.  Most commonly, propellants are chemical mixtures of a fuel and an oxidizer.  An oxidizer is a chemical that provides the oxygen or the chemical equivalent needed for fuel to burn. Rockets must carry their oxidizer because space doesn't have atmospheric oxygen.  That is a difference between a car engine and a rocket engine. A Delta IV Heavy during liftoff. The rocket is launched using liquid hydrogen and liquid oxygen cryogenic propellants. Source: Wiki. A car engine burns fuel with atmospheric oxygen and converts that energy into rotating power to turn the wheels, while a rocket engine carries its own fuel and oxidizer to produce hot exhaust gases, which are expelled at hig...

Hydrogen as rocket fuel Hydrogen, especially in its liquid form, is an effective and widely used rocket fuel known for its high energy efficiency and clean combustion, which produces only water vapor. However, it requires cryogenic storage in extremely insulated vessels due to its very low boiling point, leading to large tank sizes and significant boil-off issues that increase costs and complexity. Despite these challenges, hydrogen's high specific impulse and environmental benefits continue to make it a key propellant, particularly for upper stages, with ongoing research into even more powerful forms like metallic hydrogen.  Using liquid hydrogen as a rocket fuel! Liquid hydrogen (LH 2 ) is the liquid state of the element hydrogen. Hydrogen is found naturally in the molecular H 2  form. Hydrogen is a colorless, odorless, non-toxic gas at standard temperature and pressure, while liquid hydrogen is its ultra-cold, condensed state, requiring temperatures of -253°C or lower....

ZhuQue-2 ZhuQue-2 (ZQ-2) is developed by Chinese company LandSpace. It is the first orbital-class launch vehicle which used liquid methane and liquid oxygen (methalox) as fuel. It is a medium-sized, two-stage rocket with a 3.35-meter diameter fairing, designed to carry payloads of 4,000-6,000 kg to sun-synchronous or low Earth orbits, respectively.  After an initial failure in December 2022, its second flight in July 2023 successfully reached orbit, making it a historic milestone.  ZhuQue-2; source: LandSpace After a nominal flight, the second stage of the rocket reached a Sun-synchronous orbit (SSO) with a perigee of 431 km (~268 mi), an apogee of 461 km (~286 mi), and an inclination of 97.3 degrees. Zhuque-2 has a liftoff weight of 216 tonnes and uses 4 TQ-12 methalox engines in the first stage, each with a thrust of 67 tonnes-force (660 kN). The second stage uses one vacuum-optimized TQ-12 with a thrust of 80 tonnes-force (780 kN) in combination with a TQ-11 engine (8 tonne...

Methane as Rocket Fuel The highest specific impulse chemical rockets use liquid propellants (liquid-propellant rockets). They can consist of a single chemical, which is called a monopropellant, or a mix of two chemicals, which is called bipropellants. Bipropellants can be further divided into two sub-categories: hypergolic propellant, which ignites when the fuel and oxidizer make contact, and non-hypergolic propellant which requires a source of ignition. For a chemical rocket, the highest specific impulse means the most propellant-efficient engine, producing either the most thrust for a given amount of propellant, or providing the desired thrust with less propellant. A higher specific impulse equals to a higher effective exhaust velocity, allowing the rocket to achieve a greater change in momentum from the same propellant mass. This efficiency is primarily determined by the propellant chemistry. For the best result, the usual combination is liquid hydrogen and liquid oxygen. Until now....