WO1994029171A1 - Unified method for propelling-piloting airships using lateral thrust wind annihilation and ballasting autonomy - Google Patents

Abstract

Method combining, in a unified manoeuvre using one single device, the set of manoeuvres essential to piloting an airship. According to the invention, the device comprises a main pipe (3) longitudinal to the airship, said pipe being fitted in series at the prow with a gas compressor generator and a propulsive extractor at the stern. The differential operating powers of the prow and stern devices, with the latter acting as the propulsive device, thereby induce variable pressures within the pipe, determined by the control system. Said pressures are capable of causing either a pressurized ejection, or, on the contrary suction through the secondary pipes branching from (3) and including valves (5) and terminal outlets (8), and which face outwards of the airship towards the four cardinal points. This twofold possibility also enables, by means of other specific pipe types (13), the gas masses within the airship to be varied, in order to achieve autonomous ballasting and internal pressure compensation in response to outside variations of atmospheric pressure according to altitude.

Description

 UNIFIED PROPULSION PROCESS - STEERING AIRSHIPS IN

ANNIHILATION OF SIDE WIND PUSH AND AUTONOMY OF

THE INTERNSHIP.

The present invention relates to a method capable of replacing by the use of a unified technique the current methods of propulsion and piloting of airships, to which it moreover confers, in addition to the ballast autonomy, the autonomy of maneuver by annihilation of effect of lateral thrust of the winds.

The revival of this old mode of air transport, common in transatlantic flights until the start of the last war, is indeed slowed down, despite its indisputable advantages: comfort, energy and operating savings, both by the inertia of maneuver imposed on the devices by their large volumes, and which only imperfectly resolve the classic methods of piloting by rudders, daggerboards, etc., only by their considerable grip in the side winds, the main handicap to their return to which no effective response seems to have , so far, has been proposed.

The method according to the invention makes it possible to remove these constraints. It provides in fact, according to a first characteristic, that the propulsion and piloting operations, instead of resulting from separate maneuvers carried out using different organs: propellers or reactors for propulsion, rudders, daggerboards, etc., for this which concerns piloting, result from a unified system constituted by the coupling in series, on either side of one (or more) main longitudinal nozzle to the airship, of a gas compressor generator located upstream - or bow - (hereinafter defined by GCP) and an extractor-propellant of this same gas located downstream - or stern - (hereinafter defined by EPR), so that the use in differential powers of the GCP and E.P.R. is likely to determine, within the main nozzle, either an overpressure when the operating power of the G.C.P. is higher than that of E.P.R., i.e. a vacuum when the operating power of E.P.R. is greater than that of the G.C.P.

According to a second characteristic of the invention, the bow compressor generator can supply, instead of a single main nozzle as defined in the first characteristic, two or more main nozzles directly connected in bypass in the immediate vicinity of the generator downstream outlet bow compressor, and located outside of the airship, parallel to its longitudinal axis, this rigid assembly which can constitute the non-deformable and resistant chassis serving to support the structures of the apparatus and the arrangements of the habitable operating volumes. According to a third characteristic of the invention, two (or more) unified systems as defined in the first characteristic can equip the apparatus, the main nozzles of each of these systems being in this case mounted parallel to its longitudinal axis outside of the device, thus constituting a rigid non-deformable chassis as defined in the second characteristic

According to a fourth characteristic of the invention, the main nozzle (s), as defined in the first 3 characteristics, is equipped, in diversion, with secondary nozzles opening out, some of which are equipped with pointed ejection vents, or horizontally in opposite directions port / starboard (W / E), or vertically in directions "opposite Zenith / Ground (N / S), and for others towards the interior of the device. These two types of nozzles are provided with valves, the selective operation of which allows, with regard to the possibilities of overpressure / depression internal to the main nozzle defined in the first characteristic, all types of ejection to the outside (vents) or inside the device (overpressure) or to the on the contrary, suction, either air through the vents, or gas or air internal to the device (vacuum).

According to a fifth characteristic of the invention, the simultaneous ejection of air by all of the vents as defined in the fourth characteristic oriented vertically towards the ground promotes the ascent, the reverse operation promoting the descent, all other clean maneuvers during piloting: turns, front or rear lifting, etc., resulting from similar ejection operations by the vents specifically concerned.

According to a sixth characteristic of the invention, the simultaneous ejection by a set of vents, starboard for example, under adequate pressure determined by the respective respective powers of operation of the G.C.P. and EPR, of a part of gas or of injected air, annihilate the opposite lateral thrust of the port winds, this operation, transposable to the annihilation of any type of lateral thrust of the winds, being automatable thanks to the electronic equipment and appropriate computing, the overpowered functioning of GCP compared to E.P.R. authorizing, in all cases, the maintenance of the propulsive force essential in E.P.R ..

According to a seventh characteristic of the invention, the mass - or weight - of the lift gas essential at each stage remains invariable during operation, its volume alone varying, by expansion or contraction of the balloons (or envelopes) which contain it, according to pressure and temperature variations (Mariotte law). According to an eighth characteristic of the invention, the upstream compressor generator (s), as defined in the first characteristic, will, according to traditional techniques in Aeronautics:

- or of the "supercharging fan" type: the compressed gas injected upstream is in this particular case essentially constituted by atmospheric air at low temperature, close to ambient

- or of the "reactor" type: the compressed gases injected upstream are in this particular case essentially constituted by burnt gases, at high temperature.

The particular choice of one or the other of these devices characterizing two specific types of exploitation.

According to a ninth characteristic of the invention, the bow compressor generator, chosen in this particular case of the "supercharging fan" type as defined in the eighth characteristic, injects atmospheric outside air under pressure into the main nozzle, without significant overheating. which, independently of the operations defined in fourth, fifth and sixth characteristics, offers the availability of an autonomous renewable ballast. To this end, the internal secondary nozzles defined in the fourth characteristic supply variable masses of air to one or more expandable / retractable envelopes, included inside the invariable volume delimited by the rigid walls of the airship defined below as the lift volume. . These air envelopes, equipped with valves allowing, in certain particular cases, the free communication of the air / ballast which they contain with the atmosphere external to the airship and designed so that their membrane marries, by simple injection of air , without stretching consecutive to an essential overpressure, the internal surface of the lift volume, are in contact by an upper part of their external surface, with the similar lower part of identical envelopes which contain the invariable mass of lift gas as defined in seventh characteristic, so that a permanent equilibrium of pressure exists, through their joined membranes, between the air pressure and the pressure of the lift gas, the "lift volume" permanently representing, the sum of the volumes variables, of the constant mass (weight) of the lift gas, and of the mass (weight) of the air contained in the envelopes, variable according to n cessity load / unload, injection (pressure) or ejection (depression).

According to a tenth characteristic of the invention, the wall of the lift volume has, at certain particular points, leakage orifices and / or openings open to the outside, which allows, by opening air valves defined in ninth characteristic, the use conventional free expansion of gas and air envelopes as defined in seventh and ninth characteristics according to external variations of atmospheric pressure according to altitude. However, remember that the permanent maintenance of a slight internal overpressure relative to the external atmospheric pressure variable according to altitude, promotes better maintenance of the rigidity of the device, compatible with the lightening of the structures.

According to an eleventh characteristic of the invention, the bow injector generator is of the “jet engine” type as defined in the eighth characteristic and the air balloons defined in the ninth characteristic are eliminated, the gases - of high temperature in this case - being directly injected into the lift volume where they come into contact with the balloons containing the invariable mass of lift gas as defined in the seventh characteristic, these injection operations - or conversely of hot gas extraction, being carried out by the play of secondary nozzles with internal outlet defined in the fourth characteristic.

Operation is therefore defined as follows: the airship at rest, on the ground, before takeoff, of maximum total load (Weight) is characterized by flaccid balloons, partially filled with the constant mass of supporting gas (minimum volume) in pressure equilibrium under ambient temperature, with the external atmosphere thanks to the leakage orifices and valves defined in ninth and tenth characteristics. Preparation for takeoff involves the injection of hot gases causing the balloons to swell, the air surrounding them in the lift volume being expelled by the aforementioned leak orifices and valves, this phase continuing until the point d is reached. 'balance (weighing) where the device floats freely at ground level, the continued swelling of the lift gas by heating determining takeoff and piloting according to maneuvers previously defined. We draw attention, in this case, to the fact that the lift gas, preferably chosen lighter than air (helium for example), can, at the limit, be only air, whose density decreases in proportion to the increase in volume resulting from the rise in temperature.

According to a twelfth characteristic of the invention, and in the particular case as defined in eleventh characteristic, the total elimination of the lift gas balloons can be envisaged, the apparatus operating in this case according to the principle of hot air balloons, by injection and / or removal of hot gases, with a density lower than that of air, directly inside the lift volume, control is always carried out according to specifications defined by all of the characteristics from 1 to 6.

According to a thirteenth characteristic of the invention (not illustrated), a ballast / load shedding system external to the apparatus makes it possible to define an original possibility of anchoring to the ground after landing. To this end, the variable air or gas masses as defined above in ninth and eleventh characteristics inflate or deflate, depending on the maneuver, an external expandable / retractable chamber housed in a peripheral cell with a flat surface ("anchoring surface") integral with the structures, which equips the device from below, and is perforated, inside the perimeter delimited by the cell of one or more vents as defined in characteristics 4, 5 and six. This chamber closed on itself in the manner of an automobile inner tube, of diameter, perimeter length and resistance compatible with the intended use, deflated at altitude and therefore entirely housed in its cell (load shedding), is inflated under appropriate pressure by injecting air or gas through the play of "specific nozzles" for landing (ballasting) and its lower generator, which therefore extends beyond the cell, comes into contact with the ground. The air or gas inlet valves are then closed and the atmospheric air included in the volume delimited by the underside of the "anchoring surface", the ground, and the peripheral chamber, is sucked in by the vents that equip the anchoring surface, resulting in a plating on the ground by atmospheric pressure. Possible side winds are annihilated as defined in the sixth characteristic.

The reverse maneuvers: deflating the envelope and ejecting through the lower vents, are carried out during takeoff.

The accompanying drawings illustrate the invention.

Figure 1 shows in longitudinal and transverse sections the theoretical implementation of the method according to the invention.

With reference to these drawings, the bow compressor generator (1) injects under pressure into a single main nozzle (3) the gas or air which is taken up and ejected rearward by the doll's propellant extractor (2). Secondary nozzles (4) derived from the main nozzle (3) and provided with valves (5) pass through the rigid external wall (6) of the lift volume (7) by vents (8) oriented towards the four opposite points ZENITH - Ground - Port - Starboard, the main nozzle (3) is in this case internal to the lift volume (7).

2 shows, in section along a horizontal median plane, a variant of the method according to the third characteristic of the invention comprising two main nozzles (3) parallel to the lift volume (7), equipped with secondary nozzles (4) (only the horizontal nozzles (4) E / O (port / starboard) with reference to Figures I are illustrated) provided with valves (5) and vents (8), equipped at the head with two bow compressor injectors (1) and terminated in stern by two identical port / starboard stern thrusters (2). The assembly defined by the external elements 1-3-2 is integral with the wall (6) by a rigid longitudinal connection system (9), and constitutes a rigid and resistant frame serving as a support for the walls (6) of the lift volume (7) and for the specific arrangements of the habitable volumes (passengers - crew - freight - fuel, etc.) reserved for operation, not illustrated in the drawing .

FIG. 3 represents, according to a horizontal median plane, a variant of the method according to the second characteristic. The bow compressor generator (1) in this case feeds two secondary nozzles (3) connected as close as possible to the downstream outlet of the reactor (1) and positioned outside the device in accordance with the specifications defined in FIG. 2.

Figure 4 shows in vertical cross section the variant of the process defined in Figures 2 and 3 (only the port side is illustrated, the starboard being symmetrical).

With reference to this drawing, the main lateral nozzles (3) provided with their secondary nozzles (4) equipped with valves (5) and end vents (8) directed towards the four directions defined in the fourth characteristic, are integral with the wall (6) of the lift volume (7) by a rigid fixing system (9) which can extend laterally on the periphery of the wall (6) or be limited, according to the requirements determined by the technique, at certain points individuals.

The distance between the end of each of the horizontal lateral vents and the opposite leading edge of the wall (6) determines the width of lateral horizontal stabilizing fins (10) defined by their upper / lower faces (11), between which the main nozzles (3) are positioned as well as the control valves (5) which are fitted to the secondary nozzles (4), of which only the vents (8) open to the outside, on the upper / lower faces (11) for as regards the vertical vents, and on the thinned leading edges of the fins (10) as regards the lateral vents.

The upper / lower faces (11) of the lateral fins (10) are integral with the wall (6) by fixing elements (12).

Figure 5 shows schematically in perspective the shape of the device conditioned according to the method defined by Figures 2 and 4. We recognize in particular the bow compressor generators (1), stern thruster extractors (2), the vents (8) vertical upper, and lateral horizontal of the port wing (10).

FIG. 6 represents, in partial transverse vertical section (port side with reference to drawings 2 and 3) the connection point of a secondary nozzle (13) intended for supplying the variable air masses defined in ninth and tenth characteristics in the description and not shown, for simplification of the description and diagrams, in drawing 4. It appears, in this drawing, that the secondary nozzle (13) provided with its control valve (14) connected in bypass on the main lateral nozzle (3) between two points of bypass of the external secondary nozzles (4), injects or extracts in the expandable / retractable envelope (15) located inside the lift volume delimited by the walls (6) the air (16) thanks to the differential powers of the bow booster fan (1) and stern EP (2 ). The epidermis (15) of the air envelope is in contact, by design, at its lower part with the lower internal face of the wall (6) and at its upper median part, with the lower median part of the expandable / retractable envelope (17) which contains a constant / invariable mass of lift gas (18), the upper external surface of the epidermis of the envelope (17) being by design in contact with the upper internal face of the wall (6).

It is evident from the diagram that the lift volume (7) is the invariable sum of the variable volumes of the masses, air variable (16) and invariable of the lift gas (18), this volume 7 = 16 - f- 18 being held by the wall (6) which delimits it. The communication with the external atmosphere defined in tenth characteristic is established by leakage orifices (19) and cooling outlets (20) of the nozzles (3) which equip the lower surface (11) of the side fins (10).

The conventional use in free expansion without overpressure of the envelopes (16) and (17) in the face of variations in pressures of the external atmosphere is possible thanks to a valve (21) whose opening allows direct communication of the air ( 16) with the outside atmosphere. In this particular case, the valve (21) is open and the valves (14) closed, the envelope (15) inflating / deflating freely as a function of the external variations in atmospheric pressure which cause, according to the same pressure variations, the variations volume opposites of the lift gas (18) contained in the expandable / retractable envelope (17). The transition to piloting under controlled pressure is effected by closing the valve (21) and operating the valve (14). The lift gas supply system (18) is not illustrated, so as not to complicate the drawing.

FIG. 7 represents, in vertical cross section identical to the previous one, the ballasting / load shedding device by hot gas detailed in eleventh characteristic. With reference to this drawing, the hot gases emitted by the bow reactors (1) are directly injected, by the operation of the secondary nozzles (13) valves (14), into the lift volume (7), devoid of this case of air balloons (envelopes) defined in FIG. 6, and come directly into contact with the balloons (17) containing the lift gas (18) (maintained in the high position by their lower density), the volume of which increases or decreases as a function of the heating or cooling operations resulting from the injections or aspirations of the hot gases. Recall that the surplus hot gas, during the injection for reheating, is evacuated by the valves (21) (open) and orifices of leak (19) / vents (20), the intake of fresh outside air for cooling taking place in an identical manner, the lift gas (18) remaining, in all cases, in pressure equilibrium through the membrane ( 17) with the outside atmospheric pressure.

The manufacture of airships designed according to the application of the process is now possible thanks to the use of current materials combining lightness, mechanical and / or thermal resistance.

The light alloys derived from aluminum will logically be used for the production of the chassis that constitutes all of the nozzles (3), (4), (13), the availability of valves (5) and (14) and valves (21 ) as defined in the explanatory drawings, as well as the automation of their operation by computer according to the requirements of the operation: external atmospheric pressure, speed and force of the lateral winds (anemometers), expulsion or selective injection of air or hot gas depending on the desired goal (turn, ascent, descent, annihilation of side winds, etc.) not otherwise posing any problem given the current state of computer technology. Extensive use of composite plastics (epoxy carbon fiber laminate reinforced with rigid foam for example) combining strength and lightness may also facilitate the production of the wall (6) of the lift volume, this preference however not excluding the possibility of to design a type of entirely metallic device resulting from the assembly of thin laminated profiles positioned on transverse arches perpendicular to the longitudinal axis, secured on either side of the longitudinal connecting elements (9) - Figures 2 to 5, nor even the traditional design of flexible envelopes stretched in force over the said hoops.

The operation of valves (5) and (14) automated by computer could, in the event of an incident, require manual intervention. In this case, a port / starboard side inspection sheath, not illustrated, can be envisaged inside the enlarged space of the side fins (10) located in the vicinity of the connection to the wall (6) between the points (12) ( see drawings 4, 6 and 7).

FIG. 8 represents the assembly of the rigid lateral structures above defined by a set of parallel transverse spacers (22), perpendicular to the nozzles (3), defining between them equal volumes in which the air envelopes will be housed ( 15) and lift gas (17) defined in Figures 6 and 7. These spacers (22) are joined to the parallel nozzles (3) by the connecting pieces (9).

Figure 9 shows in perspective the connection of the spacers (22) (consisting for example of section I whose intermediate vertical face is perforated for weight gain) with the nozzle (3) by a jaw system (9) enclosing d on the one hand the nozzle (3) and on the other the upper and lower faces of the spacer (22).

RECTIFIED r ϋiάE (RULE 91) FIG. 10 represents the assembly in cross section, perpendicular to the nozzles (3), of the intermediate rectiHgne part, defined in FIG. 8, delimited by the two parallel main external nozzles (3).

Side rails (23), made of a profile identical to that of the spacer (22), are assembled laterally perpendicularly on either side of the spacers (22) and constitute the support of the upper and lower walls (6) lift volume.

Figure 11 shows the same assembly in longitudinal section. We note there, in addition to the spacers (22), the side members (23) and the connecting pieces (9), the longitudinal openings defined by the spacing of the side members (23) corresponding to the height of the spacers, which constitute, with the perforations of the side members, the leakage openings (19) defined in the tenth characteristic and shown diagrammatically in FIGS. 6 and 7.

The straight beams (23) logically extend into the bow and stern and constitute the curved ends of the chassis which will support the upper and lower spherical segments of the bow and stern ends of the lift volume.

FIG. 12 shows in section the intermediate element (24) which is necessarily in this case (curved ends of bow and stern) situated parallel to the upper and lower beams (23) which enclose it on all of its upper faces / lower.

The support frame of the upper and lower walls (6), constituting the lift volume, will be provided, at specific points not illustrated, with openings intended for the passages of the secondary nozzles (13) putting the main external nozzles (3) into communication and the envelopes (15) containing the variable air masses defined in the ninth characteristic, or injecting the gases at high temperature directly into the lift volume in the case defined in the eleventh characteristic.

Figure 13 shows schematically, in cross section, the principle of realization of the lift volume, consisting of two opposite half-volumes, fixed on either side of the side members (23), preferably made to obtain a minimum weight , in resin / carbon fiber composite, this laminate currently defining the best weight / mechanical strength ratio, or in flexible and resistant film stretched over a rigid skeleton defining the shape in the case of permanent operation under internal overpressure as defined in the tenth characteristic. In all cases, the wall support framework will consist of a series of opposite parallel arches on either side of the profiles (23) defined in Figures 10, 11 and 12.

To obtain less resistance to lateral winds, the longitudinal connection of the arches will have an acute angle, preferably in the conventional circular shape

SCURED SHEET (RULE 91) used, the connection of two opposite arcs (25), each 120 ^° open at the center, the peculiarity of which lies in the fact that the medium (S) of each arc is the geometric center of the opposite arc, s' logically imposing in this case.

Figure 14 shows in perspective and in cross section the type of profile that can be envisaged for the production of the arches (25). The suggested U-section presents, by its vertical parallel edges a better resistance to expansion and buckling, the upper surface, which will face outwards, will serve as support for the final covering.

Each final hoop will be made by assembling (not shown) sections taking account of the radius. As an example, let us point out that a radius of 30 meters would define a device 30 meters high in the center, for a width between nozzles (3) of around 50 meters, these dimensions being of the order of those of the last large ones. Zeppelins used. The hoops will be mechanically fixed (not shown) on either side of the side members (23) (Figures 11 and 12), this assembly can be done at the particular point defined by Figures 9 and 10, or any other place that technology would impose.

FIG. 15 shows in perspective a type of rectilinear profiles (26) used for coating the rectilinear longitudinal intermediate part defined in FIG. 8, the lateral vertical edges are of the same height as their counterparts (25) in FIG. 14, the upper free parts end, whose length equals half the width of the arch 25, connecting face to face by the top of the support arch 25.

FIG. 16 shows in longitudinal section the connection of the covering profiles (26) and support arch (25). With reference to the drawing, this assembly is carried out for the upper part by bolting (27) and copolymerization at interfaces (29) with the resin constituting the laminate and for the vertical edges by the positioning of angles (28) produced in the same laminate and fixed. also by bolting (27) and copolymerization at interfaces (29).

FIG. 17 represents this same assembly in horizontal section. With reference to this figure, the covering profiles (26) are joined to the support arch (25), on its external surface, by bolting (27) and copolymerization at the interface (29) and on the perpendicular vertical edges of the arches ( 25) and coating profiles (26) by interposing an angle iron (28), U-shaped, joined to the profiles and arches by the same technique of copolymerization (29) and bolting (27).

This assembly (29) (27) extends over the entire length of the covering profiles (26) of which it secures the contiguous vertical edges, as it appears in this figure. Figure 18 shows schematically, in perspective, the realization of this first stage of production (upper bow). With reference to this figure, it appears that the bow and stern coverings will be fixed on the one hand on the last vertical arch (25), on the other hand on the rounded horizontal end of the frame (23) defined in Figure 12 .

FIG. 19 represents, in external perspective, a type of module in the form of spherical segments which will be used for coating the spherical parts of the bow and stern.

With reference to this figure, the intermediate module (30) has, at its connection part with the last vertical arch (25), a free part which will be positioned, on the terminal arch (25), opposite the last rectilinear profile coating (26) similar to the process detailed in Figure (17). This module (30) also has on its three other sides vertical edges which will be joined to similar edges of the terminal modules (31), equipped, as far as they are concerned, with four vertical edges.

FIG. 20 represents, in perspective seen from the inside, the modules (30) and (31) defined above, the connections being made by union of their contiguous vertical edges, by the process of copolymerization interfaces and bolting above defined, this type of connection constituting, in addition, thanks to the double thickness which characterizes it, a system of longitudinal and transverse reinforcement of the ends of the device.

It follows from this study that the wall (6) initially defined is constituted by the assembly of the various elements (25) (26) and modules (30) (31), including the vertical edges, projecting inside the 'device, could damage, during operation, the air and gas envelopes (15) and (17) defined in Figures 6 and 7. The interior surface of the wall will therefore be leveled by the application (not illustrated), by projection or bonding of a light and rigid foam with a thickness equal to the height of the edges, further improving the mechanical strength of the assembly. However, it should be emphasized that the manufacturing process detailed in the present study only represents a possibility of implementing the method according to the invention and does not in any way eliminate other techniques, in particular the use of light metals for the manufacture of the lift volumes, the use of so-called "honeycomb" materials, the constitution of walls by the injection technology of rigid foam expandable between two parallel surfaces, or the conventional process of laying a flexible wall stretched on rigid skeleton.

Likewise, the form chosen to illustrate our example does not eliminate any other form which the production of an apparatus in accordance with the specifics of the process would impose.

RECTIFIED SHEET (RULE 91)

IS SA / / EP

Claims

1) Unified propulsion process - Pilotage of airships in annihilation of lateral thrust of the winds and ballast autonomy, characterized in that all of these functions result from the use of a unified system constituted by the coupling in series of share and on the other side a longitudinal main nozzle to the device, a gas compressor generator (1) located upstream (bow) and a propellant extractor (2) located downstream (stern) capable of operating at differential powers, so that the bow generator (1) delivers under pressure through the main nozzle (3) the gases to the stern extractor (2) which assumes the propulsion function, an operating power of (1 ) greater than that of (2) assuming, according to the need defined by the maneuver, the availability of an overpressure internal to the nozzle (3), an operating power of (1) less than that of (2) inducing, on the contrary , int depression erne to the nozzle (3). 2) Method according to claim 1 characterized in that the main bow generator (1) feeds two or more main nozzles (3), derived directly in the immediate vicinity of the downstream outlet of the generator (1), located parallel to the outside, on either side of the device, and each equipped with a stern thruster extractor (2) Figure 3- 3) Method according to claim 1 characterized in that two unified systems equip the device, the main nozzles (3) mounted parallel to the outside (port / starboard) constituting, by the set of spacers (22), side members ( 23) and connecting parts (9) a rigid frame supporting the superstructures represented by the lift volume (6) and possibly, the habitable operating volumes (piloting, passengers, freight, etc.) fig 2, 8, 9 , 10.11. 4) Method according to claims 1 to 3 characterized in that the (the) main nozzle (3) is equipped, in derivation of secondary nozzles, provided with valves, and opening, for some (4 - Nanne 5 Fig from 1 to 4 ) outwards by vents (8) directed towards the 4 cardinal points (Ν (Zenith) - S (Sol) - E (starboard side) - O (port side)) and for others (13 - Valves 14 - Fig 6 and 7) towards the inside of the airship, for specific uses defined below. 5) Method according to claims 1 to 4 characterized in that the control is carried out by selective ejection by certain vents (8) specifically concerned, of the excess pressurized gas resulting from the operation of the bow generator (1) at a higher power RECTIFIED SHEET (RULE 91) to that of the stern thruster extractor (2). The TRIBORD turn, for example, will result from the opening of the only valves (5) supplying the antagonistic vents of port bow and starboard stern, this maneuver carried out thanks to the central control computer which logically equips the device, being transposable to all 5 piloting, in particular EDGE turn, bow lift for ascent, stern lift for descent, contribution to ascent by simultaneous ejection by all the vents oriented towards the ground (N / S), contribution to the descent by the simultaneous ejection of upward-oriented vents (S / N), etc. The set of valves 14 is in this case closed, the propellant extractor maintaining its propulsive function. 3.0 6) A process according to claims from 1 to 5 characterized in that any lateral thrust of winds is annihilated by the opposing thrust resulting from the simultaneous ejection of gas supercharged by all of the vents located on the opposite face (port vents for starboard wind, for example) the operating power of the bow compressor generator (1) compared to the stern thruster extractor (2) nevertheless allowing, in this 15 cases, maintenance of a propellant thrust in (2). 7) Method according to the invention characterized in that the mass - or weight - of the lift gas remains constant throughout the duration of operation, its volume alone varying according to pressure and / or temperature variations imposed by the control (laws of Mariotte). 8) Method according to the invention characterized in that two particular modes of realization - hence, of exploitation - depend on the type of bow compressor generator (1) selected for the equipment of the apparatus. This G.C.P. will indeed be: - either of the "booster fan" type; the gas injected under pressure into the nozzle (3) is in this case essentially air, at low temperature close to ambient, - either of the "reactor" type; in this case, the gas injected under pressure into the nozzle (3) essentially consists of gas burnt at high temperature. 9) Device according to claim 8 characterized in that the bow compressor generator (1) is of the supercharger type, the gas injected under pressure in this case consists essentially of outside air, without significant increase in temperature, which gives the possibility of varying, by injection or ejection of air from or towards 0 the external atmosphere, the mass and pressure of a variable volume of air (16) contained in one (or more) expandable and / or retractable envelope ( 15) included inside the invariable volume (7) said lift volume delimited by the walls (6) of the device, and supplied by the channel of specific nozzles (13), derived from the main nozzle (3) and provided with operating valves (14), the air envelopes equipped with valves (21) authorizing, as necessary, the communication of the ballast air that they contain with the external atmosphere being designed so that the external surface of their membrane (15) marries without stretching consecutive to an essential overpressure the internal surface of the wall ( 6) "lift volume" (Fig. 6). 10) Device according to claim 9 characterized in that the wall (6) of the lift volume is open to the external atmosphere by leakage orifices (19) and contains, in addition to one (or more) air envelope (15), one (or more) lift gas envelope (17) constituted according to the same criteria as the air envelope, the epidermis of the gas (17) and air (15) envelopes being in contact, respectively, with the upper parts and lower of the inner surface of the wall (6) of the lift volume, and joined in their middle part, so that the controlled variations in pressure of the variable mass of ballast air (16) induce identical variations in pressure of the invariable mass of the lift gas, through the adjoining surfaces of the epidermis (15) and (17), (fig- 6). It should be noted that the continuous operation of a slight overpressure, internal to the envelopes (15) and (17), relative to the external atmospheric pressure varying according to the altitude, promotes the lightening of the structures compatible with good maintenance of the rigidity, while assuming the availability of a variable ballast-air (16) the availability of a valve (21) which allows the free communication of the air contained in the envelope (15) with the external atmosphere, making however possible the conventional exploitation in free expansion of the lift gas in front of the external variations of atmospheric pressure, the return to the system in controlled pressure being done by closing of the valve (21) (Fig. 6). 11) Device according to claims from 1 to 8, characterized in that the bow compressor generator (1) is of the "jet engine" type, and that the lift volume (7) is only equipped with only lift gas balloons (17) the internal secondary nozzles (13) opening in this case directly into the lift volume (7), equipped with leakage orifices (19) and valves (21), fig. 7. 12) Method according to claims 4 and 11, characterized in that the injection - or extraction - of hot gas by means of the valves 14 / nozzles 13 - at atmospheric pressure thanks to the existence of the leak orifices (19) and valve (21) (open), directly in contact with the casing (17) induces either an increase or a decrease in temperature of the lift gas (18) determining, or an increase in its volume by expansion of the casing (17) (the outside air and the excess hot gas being in this case expelled by the leakage orifices (19) and valve (21)). on the contrary, a decrease in volume by shrinkage of the envelope (17) (the fresh outside air in this case being sucked in by the same orifices (19) and valve (21)), these opposite maneuvers determining either a lightening (ascent) or a weighting (descent) of the entire apparatus, the other piloting operations being maintained in accordance with claims 1, 5 and 6 by virtue of the appropriate operating overpower of the reactor (1) FIG. 7. 13) Method according to claims 11 and 12 characterized in that the lift gas (18), preferably chosen from gases "lighter than air" (helium for example) can be, ultimately, air , the density of a gas, at constant pressure, decreasing as a function of its volume increase proportional to the temperature. 14) Method according to claim 12 characterized in that the lift volume 7 (Fig. 7) is entirely devoid of gas envelopes 17 (process not shown), lightening operations (load shedding) or weighting (ballasting) resulting exclusively from injection or removal of hot gases, according to the "Hot Air Balloon" principle. 15) Method (not illustrated) according to claims from 1 to 14, characterized in that a peripheral cell with a flat surface (anchoring surface), perforated with vents (8) oriented towards the ground and secured from below , structures of the device, encloses a resistant expandable / retractable envelope, closed on itself in the manner of a car inner tube, which, deflated at altitude (load shedding) is made heavier for the descent (ballast) by injection of compressed air (or gas) through the play of specific nozzles (13 / valves (14), its lower generator, which therefore overflows from the cell, coming into contact with the ground during landing The inlet valves (14) and valve (21) are then closed and the atmospheric air trapped between the underside of the anchoring surface, the casing and the ground is sucked in by the vents (8) causing a plating. on the ground by atmospheric pressure, the undesirable effects of lateral winds were They are therefore annihilated in accordance with claim 6. The reverse maneuver is carried out for the ascent: deflation of the envelope and, ejection of air by the vents causing a vertical upward thrust. 16) Device for implementing the method according to any one of claims from 1 to 14, characterized in that the rigid outer wall consists of sections (26), modules (30) (31), joined by their edges external by copolymerization (29), bolting (27) and angles (28) stiffened by projection or gluing of rigid foam, adjusted on support hoops (25), integral with a frame (23/24) equipped with spacers (22) , and connected to the parallel external nozzles (3) by connection pieces (9), the side fins (10) whose walls (11) surround the main nozzles (3) equipped fEUl-lE R-CTlFK ^ Gl- 91) secondary nozzles (3) and (13) being connected longitudinally to the walls (6) by a connection system (12).