The impeller contains some motor components.

According to the invention, the spacecraft (1) includes at least one solid propellant motor (10-14) and at least one electric thruster (20-24).

A rocket motor may contain the solid propellant.

The projectile (1) is translated in respect of the rocket motor (10) by means of a pyrotechnic charge (2) before the rocket motor (10) is initiated.

Passive venting apparatus and method for a rocket motor or ordnance device (10) containing propellant or explosive material (14) enclosed in a case (12), which presents an explosion hazard when subjected to external heat.

The second turbine engine includes a second engine core and a second propulsor disposed about a second propulsor axis parallel to the first propulsor axis.

According to the invention, an engine and a method for adjusting a control or drive system have corresponding characteristics.

The first turbine engine includes a first engine core that drives a first propulsor disposed about a first propulsor axis.

Solid-propellant rocket – A solid-propellant rocket or solid rocket is a rocket with a rocket engine that uses solid propellants.

Said propulsion system has a first jet turbine engine and a second jet turbine engine (22, 24).

The aerosol propellant may be a hydrofluoroalkane propellant.

The aerosol propellant may be a hydrofluoroolefin propellant.

The aerosol propellant may be a hydrofluoroalkane propellant.

The aerosol propellant may be a hydrofluoroalkane propellant.

For example, the thruster can be a monopropellant, bipropellant, or hybrid thruster.

Each propulsor includes a propulsor turbine and one of a fan and a propeller.

The propulsion unit is an azimuthing thruster with a propeller 3 mounted on a capsule 6.

A power device, the prototype for which can be found in any reaction device, for example a hydraulic propeller.

The present invention relates to an adjustment device for adjusting the pitch angle of the propeller blades (4) of a propeller pump (1) and a propeller pump incorporating such a device.

A propeller guard section (120) for guarding the outer circumference of the propeller (500) is provided at the aircraft body (100).

A propellant gas discharge system (21) supplies propellant gas into the pressure chambers (36, 38).

A system for uniformly distributing propellant gas in a Hall-effect thruster (10) (HET) includes an anode (42, 42') and a porous material gas distributor (60, 89) (PMGD).

Each compartment may have the same propellant.

The third pressure is substantially equal to the vapour pressure of the propellant at ambient temperature at the instantaneous volume of the vaporised propellant, and at the third pressure the syringe contains liquid propellant.

The thruster valve (19) allows or prevents the supply of propellant to the ion source (3) and the neutralizer (5).

The container is charged with propellant (40).

The gas propellant is filled in the igniter chamber.

In addition, a compatible propellant may be employed.

The bypass is operable to: intake a portion of propellant from a tail of the body, conduct the portion of propellant along an outer surface of the body, and discharge the portion of propellant in front of the body.

The propellant is generated by a chemical reaction.

The arrangement comprises an azimuthing propulsion unit (6) and operating equipment for turning said azimuthing propulsion unit to steer the vessel.

The propulsion unit is moveable with respect to the boat hull adjusting a thrust vector of the propulsion unit In another aspect, the high-speed boat may include a hull having fore and aft portions The fore portion includes multiple sponsons.

The invention also relates to a marine vessel using the inventive propulsion unit.

The invention relates to a rotor with integrated blading, especially for a propulsion unit on which rotor blades are arranged circumferentially and extend in an essentially radial manner.

The invention also concerns an aircraft equipped with at least one such propulsion unit.

Children in genocide: extreme traumatization and the ‘affect propellor’.

Similar designations include nerd and propellor head.

Shall not be used as aerosol propellant for any use.

The current trend is to reduce the amounts of aerosol propellant in the atmosphere.

An aerosol propellant comprises a methylene-chloride-in-water water/out emulsion comprising water, methylene chloride and a surfactant and a propellant gas soluble in methylene chloride.

The container may be a bag-on-valve type of device, with the aerosol propellant outside of the medicament bag, such that the medicament does not come into contact with the propellant.

It is used as an aerosol propellant in various industries.