Mobile units have the following inseparable sub-assemblies: a cylindrical outer envelope with low conicity or even constant section, one or more longitudinal fluidic channels, sensors, and one or more transverse fluidic channels. Each fluidic channel convergent at the inlet and divergent at the outlet to ensure the absorption of the entire frontal fluid vein. The motorizations are engineered for fluidic channeling design and each one controlled by the sensors fitted to measure differential pressures between external and absorbed fluid media. The transverse fluidic channels connected on demand, upstream to the high-pressure outlets of the longitudinal fluidic channels, downstream to pressurized boxes for vertical and directional movements. A set of volumes internal to the external fuselage envelope, not occupied by other devices of the mobile units, structured in technical operating sub-assemblies.
1. Motorized mobile units, other than an airship, comprising of inseparable sub-assemblies:
an outer fuselage envelope with a length greater than a net transverse dimension of the outer fuselage envelope;
at least one motorized internal longitudinal channel and a plurality of motorized internal longitudinal fluidic channels longitudinally crossing the mobile units and incorporated into a volume of the outer fuselage envelope, so as to ensure an internal circulation of a fluid opposing a frontal movement of the mobile units, said at least one motorized internal longitudinal channel or each motorized internal longitudinal fluidic channel being equipped with one or more motorization devices, supplemented by an upstream equipment and a downstream equipment, controlled so that speeds and pressures of an overall flow of the fluid leaving said at least one motorized internal longitudinal channel are greater than speeds and pressures of an incoming flow, each of said plurality of motorized internal longitudinal channels presenting, successively, in a direction of the internal circulation of the fluid;
a set of input portions of convergent sections, a set of intermediate portions of constant section, and a set of final output portions of divergent sections, and an inlet portion of the converging sections in said at least one motorized internal longitudinal channel comprising:
fan-compressors in aeraulic applications or flow accelerators in hydraulic applications; and
differential pressure sensors, between the incoming flow and an external surrounding flow, mounted on a front leading edge separating between the external surrounding flow and a flow admitted into said each motorized internal longitudinal fluidic channel;
each intermediate portion comprising:
propellants from said one or more motorization devices acting directly on a fluid stream channeled by said each motorized internal longitudinal fluidic channel and positioned along an intermediate portion of said each motorized internal longitudinal fluidic channel; and
a longitudinal channeling secondary envelope, which conducts internally, around each motorized fluidic vein, a concentric, damping flow, extending at least over an entire length of said each intermediate portion of said each motorized internal longitudinal fluidic channel;
each final output portion located downstream of said each motorized internal longitudinal fluidic channel of the mobile units, extending from an exit of a corresponding intermediate portion to a rear end of the outer fuselage envelope, and
comprising:
energy sensor devices;
diffusers; and
parallelizers of a flow leaving the corresponding intermediate portion and of a flow channeled by a corresponding longitudinal channeling secondary envelope;
a plurality of non-motorized transverse internal fluidic channels connected at a request of a controller, upstream to said plurality of motorized internal longitudinal fluidic channels at a height of an output of the motorizations devices of said plurality of motorized internal longitudinal fluidic channels or after the energy sensor devices, opening downstream into specific surface areas of the outer fuselage envelope to ensure therein a controlled distribution of flows picked up from said plurality of motorized internal longitudinal fluidic channels and to develop therein controlled lateral thrust forces;
wherein said plurality of non-motorized transverse internal fluidic channels link in a completely internalized manner in the outer fuselage envelope, paths between upstream and downstream ends of said plurality of non-motorized transverse internal fluidic channels comprising variable sections linked to a flow rate of the flows that must be driven by said plurality of non-motorized transverse internal fluidic channels; and
a set of available internal volumes between the outer fuselage envelope and a totality of internal volumes occupied by said plurality of motorized internal longitudinal fluidic channels and said plurality of non-motorized transverse internal fluidic channels, and their associated functional equipment structured in sub-technical sets for operating said mobile units.
2. The mobile units of claim 1 , wherein the motorization devices of said each motorized internal longitudinal fluidic channel are elongated or with integrated motors, and are placed directly in the corresponding motorized internal longitudinal fluidic channel or in compartments arranged laterally thereto, each motorization device comprising:
a front turbine, a pump, or a combination of the front turbine and the pump to generate an incompressible traversed surrounding fluid, thereby to provide an effect of flow accelerators;
an accelerator-compressor acting on a frontal fluid vein entering at a front of said each motorized internal longitudinal fluidic channel to provide a compressible surrounding fluid;
an accelerator motor acting on a fluid stream in transit in the intermediate portion of said each motorized internal longitudinal fluidic channel; and
a turbine-diffuser-expander-and parallelizers acting on the fluid stream ejected from the final output portion of divergent section of said each motorized internal longitudinal fluidic channel.
3. The mobile units of claim 1 , wherein, for aeraulic applications, said at least one motorized internal longitudinal channel or said each motorized internal longitudinal fluidic channels comprise one or more elongated motorization devices extending over the entire length of a corresponding intermediate portion of said each motorized internal longitudinal fluidic channels; and wherein the aeraulic applications being aeronautics.
4. The mobile units of claim 1 , wherein said at least one motorized internal longitudinal channel or in a corresponding output portion of said each motorized internal longitudinal fluidic channels comprise a plurality of parallelization devices to control motorization flows to optimize a rear propulsive efficiency by slowing down the fluid by: parallelization of fluid streams being ejected at a rear of the mobile units providing a diffuser effect, minimizing turbulent and thermal energy losses; and optionally installing the parallelization devices in the input portions of said motorized internal longitudinal fluidic channels in application to hydraulic or mixed media.
5. The mobile units of claim 1 , wherein:
the outer fuselage envelope comprises a plurality of motorized internal longitudinal channels with different lengths and parallel to each other;
a front inlet section of the outer fuselage envelope is equal to a sum of the input portions of said plurality of motorized internal longitudinal fluidic channels of a multi-channel construction and an output section of the outer fuselage envelope is equal to a sum of the output portions of said plurality of motorized internal longitudinal fluidic channels;
a number of incoming motorized internal longitudinal fluidic channels is different from a number of outgoing motorized internal longitudinal fluidic channels allowing intermediate flows of said incoming and outgoing internal longitudinal fluidic channels to mix and be associated; and
said plurality of motorized internal longitudinal fluidic channels are subdivided either into secondary longitudinal fluidic channels whose corresponding controlled flows contribute to permanent effects of at least one of thermal and acoustic insulation, or into secondary transverse fluidic channels, connected on demand, downstream of engines, which allow a development of lateral forces controlled on specific surfaces of the outer fuselage envelope.
6. The mobile units of claim 1 , further comprising a leading edge for an entry of the fluid into said each motorized internal longitudinal fluidic channel or a set of leading edges for said plurality of motorized internal longitudinal fluidic channels; wherein for each leading edge:
an angle formed between a profile of the outer fuselage envelope and a profile of a first channeling part of said plurality of motorized internal longitudinal fluidic channels is a minimum of 5 degrees; and
a front edge of said each leading edge is not necessarily perpendicular to a longitudinal axis of the mobile units and has a non-linear or sinusoidal profile.
7. The mobile units of claim 1 , further comprising at least one compartment or a plurality of compartments structured between the outer fuselage envelope and said at least one motorized internal longitudinal channel or said plurality of motorized internal longitudinal fluidic channels and said plurality of non-motorized transverse internal fluidic channels to form: a steering or trajectory control cell and technical compartments; and wherein all compartments are thermally, acoustically and vibratory insulated from motors and internal fluidic channels.
8. The mobile units of claim 1 , further comprising an outer sheath envelope in which is fixed one or more incorporated objects, which can be motorized, the outer sheath envelope comprising:
an outer surface of the outer sheath envelope defining an outer fuselage contour of the mobile units;
an inner surface of the outer sheath envelope defining, with outer surfaces of said one or more incorporated objects, an input portion, an intermediate portion and an output portion of at least one motorized internal longitudinal fluidic channel;
a motorization device associated with said one or more incorporated objects participates in an acceleration and circulation of a fluid flow from a front of an internal channel formed to a rear thereof by the flow accelerators.
9. The mobile units of claim 8 , wherein said at least one motorized internal longitudinal fluidic channel comprises a plurality of successive inlet sections, forming sub-channels, arranged in an overlapping and stepped from a most upstream end of said one or more incorporated objects, towards both said outer fuselage envelope and the downstream of the mobile units which can go beyond a termination of said one or more incorporated objects.
10. The mobile units of claim 1 , wherein a subset of or all of said plurality of motorized internal longitudinal fluidic channels incorporates non-compact, soundproof motorizations, which directly or indirectly drive turbines that provide electrical resources to:
an indirect drive of the fan compressors;
drive electric motors of said plurality of motorized internal longitudinal fluidic channels; and
control devices.
11. The mobile units of claim 1 , wherein a surface of the outer fuselage envelope comprises, in predetermined areas, flat boxes:
fully integrated into a volume of the outer fuselage envelope;
pressurized and supplied, on demand, either by diversion of a part of outgoing flows, captured after motorization, at high pressure, into said plurality of non-motorized transverse internal fluidic channels, or by air boosters, and
provided with a multitude of fluid exhaust points, regularly distributed, each acting as a mini or micro-nozzle, which locally and globally develop lateral thrust forces which are applied to said mobile units.
12. The mobile units of claim 1 are without wheelsets for take-offs and landings in vertical mode or in a slid tangential mode and is piloted on a pressurized fluidic cushion.
13. The mobile units of claim 11 , wherein:
flat surface areas of the outer fuselage envelope being equipped with the pressurized flat boxes and fed by said plurality of non-motorized transverse internal fluidic channels, whose flows controlled on demand, develop on said mobile units lateral, directional and distributed thrust forces, the combinations of which effectively obtain effects of:
a vertical take-off, while flows produced by one or more of said plurality of motorized internal longitudinal fluidic channels are totally directed towards said plurality of non-motorized transverse internal fluidic channels;
a permanent guidance, by controlled activation of the pressurized flat boxes;
a progressive transfer of propulsive power available in a horizontal movement by controlled activation of motorized internal longitudinal fluidic channels not requested during the vertical take-off, or by progressive reduction of the flows implemented in said plurality of non-motorized transverse internal fluidic channels and by controlled redirection of the flows towards an exit of a motorized internal longitudinal fluidic channel which produce the flows; and
a permanent or impulsive adjustment of trajectories traveled, by controlled activation of devices implemented for the vertical take-off and for an omnidirectional guidance.
14. The mobile units of claim 1 , in aeronautical applications, passes from a subsonic mode, to a supersonic mode, to a stratospheric mode then to a suborbital mode by a progressive injection, from the stratospheric mode, of pure oxygen on board or of an oxidizer other than oxygen to the motorization devices, which are internal motor propulsion devices; and wherein in the subsonic and supersonic modes, the oxidizer, not on board pulsed in the external surrounding flow traversed is the oxygen of the air, so that the mobile units of a suborbital or space launcher are freed from carrying oxidizer in launch phases that consume much of the oxygen.
15. The mobile units of claim 1 are structured as an association of centrally piloted mobile units, made autonomous in stages, comprising:
central mobile units, for ultimate use, reusable or not;
the mobile units being laterally associated with the central mobile units, independent, mounted symmetrically with respect to a main axis of the central mobile units, detachable and recoverable, to form a mobile launch unit from:
one module to single use, detachable from the central mobile units, the mobile launch unit being a satellite or a space shuttle, the central mobile units being recoverable; or
a transport cell at a suborbital altitude integrated to the central mobile units, provided for a rapid return to Earth; and
wherein the mobile units assembled in a single launcher for a vertical take-off and landing in a slipped mode on a pressurized fluidic cushion.
16. The mobile units of claim 1 , wherein the outer fuselage envelope comprises at least one of the following retractable equipment: wings, rudders, fins, temporary support devices on the ground, sensors protruding from and outside the outer fuselage envelope, retractable motorized devices to enable an initiation of a movement perpendicular to a main longitudinal axis of the mobile units, and device for temporary or permanent, total or partial protection of front entrances of the mobile units against objects carried by the incoming flow automatically operated under an impulse of a detector.
17. The motorized mobile units of claim 1 , wherein a ventral face of the outer fuselage envelope is flattened.
18. The motorized mobile units of claim 1 , wherein said energy sensor devices are turbines and associated electrical generators.
19. The motorized mobile units of claim 1 , wherein the motorization devices are internal motor propulsion devices.
20. The motorized mobile units of claim 1 , wherein a front section of the outer fuselage envelope is larger than a rear section of the outer fuselage envelope.