Airship comprising orientable propulsive members and / or carried by a traversing structure

Abstract

An airship (1) with a flexible envelope (2), comprising a propulsion system (3) provided with propulsive members (6, 7, 8, 9) and a mechanism for selectively orienting and / or carrying one or more of said propulsive members. A method for controlling such an airship (1).

Description

DESCRIPTION Title: Airship comprising steerable propulsion organs and / or organs supported by a through-structure technical field

[0001] The invention relates to the field of aerostats, also known as airships.

[0002] The invention is of particular interest for airships with flexible envelopes. The invention can also be implemented in semi-rigid or rigid airships. State of the art

[0003] Soft-envelope airships, also known by the Anglo-Saxon term "blimps", contain a carrier gas, typically helium, which ensures the aerodynamic shape of the envelope.

[0004] Given the flexibility of the envelope, the attachment of the propulsion means generally requires complex attachment systems which tend to increase the drag of the airship.

[0005] More generally, there is a need to improve the aerodynamic performance and maneuverability of conventional soft-envelope airships. Description of the invention

[0006] The invention relates to an airship, or aerostat, comprising an envelope and a propulsion system equipped with one or more propulsion organs.

[0007] Each propulsion unit typically includes a rotating element, which is free to rotate about a respective axis of rotation. For each propulsion unit, the axis of rotation of the rotating element can define an orientation of the propulsion unit relative to the hull.

[0008] According to an advantageous aspect of the invention, the propulsion system may include a drive mechanism configured to change the orientation of one or more of said propulsion organs.

[0009] In other words, the airship of the invention may include one or more steerable propulsion organs enabling the propulsion to be vectored and improving the maneuverability of the airship.

[0010] Without limitation, for one or more of said propulsion devices, said rotating element may be an element such as a propeller or a turbine, for example a two-bladed or three-bladed propeller.

[0011] In a preferred embodiment, each of said propulsion organs comprises a propeller and an electric motor configured to drive this propeller.

[0012] The propulsion organs can typically be supported by structural elements of the airship, thus forming support structures that can be connected directly or indirectly to the envelope.

[0013] In particular, the airship may include one or more support structures, each of which supports one of said propulsion organs.

[0014] In one embodiment, said drive mechanism includes one or more drive members configured to move one or more of said support structures so as to change the orientation of one or more of said propulsion members.

[0015] In other words, the modification of the orientation of a given propulsion organ - and more particularly of the axis of rotation of the rotating element of this propulsion organ - can be ensured by moving this propulsion organ not directly but through a structure supporting this propulsion organ.

[0016] Alternatively, the drive mechanism can be configured to move one or more of the propulsion elements by acting directly on them rather than through a support structure. To achieve this, the propulsion elements can be directly attached to the drive mechanism itself.

[0017] In one embodiment, the airship includes one or more tail fins.

[0018] Without limitation, one or more of said tail assemblies may include one or more moving parts.

[0019] When the airship includes one or more support structures as defined above, one or more of said movable parts may form one or more of said support structures.

[0020] Alternatively, or in addition to one or more of the aforementioned moving parts, one or more moving parts may be configured to move independently of the aforementioned support structures. In other words, the airship may include moving parts that do not form propulsion support structures as defined above.

[0021] In one embodiment, each of said movable elements can form all or part of a rudder or aileron.

[0022] Advantageously, such a rudder or wing can have an aerodynamic shape, presenting for example surfaces that define one or more curvatures.

[0023] In an embodiment in which the airship includes one or more control surfaces (or ailerons), the rotating element of each of the propulsion organs extends downstream of a trailing edge of one of the respective control surfaces (or ailerons).

[0024] Alternatively, the rotating element of each of the propulsion organs can extend upstream of a leading edge of one of the respective control surfaces (or ailerons).

[0025] In one embodiment, each of said drive members is configured to move two respective of said propulsion members or, when the propulsion members are supported by support structures as defined above, to move two respective of said support structures in order to change the orientation of the propulsion members they support.

[0026] In other words, the propulsion organs and their possible support structures can form one or more groups, each group comprising two respective propulsion organs and their possible support structures.

[0027] In one embodiment, the propulsion system comprises two groups of propulsion elements and the drive mechanism comprises two corresponding drive elements. In such an embodiment, a first of said drive elements is configured to move the first two of said propulsion elements and their optional support structures, while a second of said drive elements is configured to move the second two of said propulsion elements and their optional support structures.

[0028] In one embodiment, one or more of said drive elements can each form a drive shaft rotating about a respective axis of rotation. Thus, when the drive mechanism comprises several drive elements, two of said drive elements can each form a drive shaft rotating about a respective axis of rotation.

[0029] Preferably, but not exclusively, the axis of rotation of one of the drive shafts may be perpendicular or oblique to the axis of rotation of the other of said drive shafts.

[0030] According to another advantageous aspect of the invention, the airship may include a reinforcement structure, also called a through structure, having one or more cross members which each extend into a chamber formed by the envelope and which are each connected to the envelope by respective connecting members.

[0031] The crossbeams can advantageously be connected to each other by an additional connecting element.

[0032] In an embodiment in which the airship includes one or more drive elements, one or more of said crossbeams may be configured to receive and / or to guide one or more of said drive elements.

[0033] Without limitation, such a cross member may have a tubular geometry, in order to receive and guide a drive element in the form of a shaft.

[0034] Such an embodiment is particularly advantageous when a drive element thus guided is configured to move two propulsion elements of the same group.

[0035] In a preferred embodiment, the envelope is flexible.

[0036] In other words, the airship of the invention can be a "blimp" type aerostat.

[0037] The airship of the invention can alternatively have a semi-rigid or rigid envelope.

[0038] The invention also relates to a method for controlling an airship as defined above.

[0039] This process may include a step of changing the orientation of one or more of said propulsion organs using said drive mechanism.

[0040] The control method of the invention can typically be implemented to achieve a hover or to move the airship around a yaw axis and / or a pitch axis.

[0041] The various embodiments and aspects of the invention can be combined or implemented independently of each other.

[0042] For example, in one embodiment, the airship includes one or more steerable propulsion organs and lacks a through-structure as defined above. In another embodiment, the airship includes a through-structure as defined above, independent of the propulsion system. As yet another, non-limiting example, the airship may include a through-structure as defined above carrying one or more non-steerable propulsion organs.

[0043] Other advantages and features of the invention will become apparent from the detailed, non-limiting description that follows. Brief description of the figures

[0044] The detailed description that follows refers to the attached drawings on which: - Figure 1 is a schematic perspective view of an airship according to the invention, the airship comprising a tail assembly with movable parts, as well as a propulsion system equipped with four tiltable propulsion organs; - Figure 2 is a schematic view of part of an airship such as that in Figure 1, showing a drive mechanism for a propulsion organ, this mechanism comprising a shaft cooperating with a support structure for the propulsion organ; - Figure 3 is a schematic perspective view of an internal reinforcement structure of an airship such as that of Figure 1 and of a drive mechanism for the airship's propulsion organs, this mechanism comprising shafts housed in tubes of the reinforcement structure; - Figure 4 is a schematic perspective view of part of the reinforcement structure of Figure 3; - Figure 5 is a schematic view of part of the airship in Figure 1, showing the first two of said propulsion organs inclined relative to the configuration of Figure 1; - Figure 6 is a schematic view of part of the airship in Figure 1, showing two seconds of said propulsion organs inclined relative to the configuration of Figure 1.

[0045] Common references are used across the different figures to designate identical or analogous elements. Detailed description of implementation methods

[0046] The figures include a reference frame defining orthogonal directions D1, D2 and D3.

[0047] Figure 1 shows an aircraft 1 according to the invention.

[0048] In this example, aircraft 1 is a blimp with a flexible envelope 2.

[0049] As is known in itself, envelope 2, also called the hull, can typically include a gas-tight fabric forming a chamber which receives a carrier gas capable of maintaining the aerodynamic shape of envelope 2. The carrier gas can be helium.

[0050] The airship 1 extends globally along an axis Al which in this example is parallel to the direction D2.

[0051] Figure 1 shows more specifically a rear part of the airship 1, towards the right of Figure 1, which in this example includes a propulsion system 3 and a tail assembly 4.

[0052] Of course, airship 1 may include other components not shown in Figure 1, for example one or more additional propulsion components which may be arranged on a forward part of airship 1.

[0053] The airship 1 typically includes an electronic system (not shown) designed to ensure the distribution and management of energy necessary for its operation, in particular to distribute electrical energy to the propulsion system 3.

[0054] As is known in itself, such an electronic system can be carried on a gondola (not shown) of the airship 1.

[0055] In the embodiment of Figure 1, the propulsion system 3 comprises four propulsion elements 6, 7, 8 and 9.

[0056] With reference to Figure 2, the propulsion unit 7 in this example comprises a two-bladed propeller 11 which is mobile in rotation around an axis of rotation A7, as well as an electric motor 12 to drive the propeller 11 in rotation around the axis A7.

[0057] In this example, the propulsion unit 7 is supported by a structure 14 called a support structure.

[0058] The propulsion organs 6, 8 and 9 of figure 1 are in this example similar to the propulsion organ 7, the description of figure 2 applying by analogy to propulsion organs 6, 8 and 9.

[0059] Thus, with reference to Figure 1, each of the propulsion organs 6, 7, 8 and 9 has an axis of rotation A6, A7, A8 or A9, respectively, and is supported by a support structure 13, 14, 15 or 16, respectively.

[0060] In the non-limiting embodiment of Figure 1, the support structures 13, 14, 15 and 16 are each formed by a respective movable part of the tail assembly 4.

[0061] Each of the movable parts 13, 14, 15 and 16 comprises in this example a leading edge 21, a trailing edge 22, a proximal end 23 and a distal end 24 (see figure 2).

[0062] With reference to Figure 1, the tail assembly 4 also includes in this example four fixed parts 33, 34, 35 and 36, which are integral with the envelope 2.

[0063] The fixed parts 33, 34, 35 and 36 and the movable parts 13, 14, 15 and 16 thus form four subsets of the tail assembly 4, a first subset being formed by the parts 13 and 33, a second subset being formed by the parts 14 and 34, a third subset being formed by the parts 15 and 35, and a fourth subset being formed by the parts 16 and 36.

[0064] In this example, the fixed parts 33, 34, 35 and 36 define the roots of the tail assembly subassemblies 4.

[0065] For each of the tail assembly subassemblies 4, the moving part and the fixed part are arranged relative to each other in such a way as to allow movement of the moving part relative to the fixed part.

[0066] In the configuration illustrated in Figure 1, for each of the movable parts 13, 14, 15 and 16, the leading edge and trailing edge are spaced apart along the direction D2, the distal end forms a wingtip of the corresponding sub-assembly of the tail assembly 4, while the proximal end of the movable part is arranged opposite the corresponding fixed part.

[0067] In this example, each of the tail assembly subassemblies 4, in particular each of the movable parts 13, 14, 15 and 16, has an aerodynamic shape, for example a symmetrical biconvex profile.

[0068] In this description, the movable parts 13, 14, 15 and 16 of the tail assembly 4 are also called rudders or ailerons or stabilizers.

[0069] With reference to figure 3, the airship 1 in this example includes a reinforcement structure 40.

[0070] The reinforcement structure 40 here includes two cross members 41 and 42 in the form of tubes which can be made of carbon.

[0071] By way of example, when the airship 1 is assembled, the cross member 41 extends parallel to the direction DI and the cross member 42 extends parallel to the direction D3. The cross members 41 and 42 are thus perpendicular to each other.

[0072] Cross members 41 and 42 are also slightly offset from each other along the direction D2, so as to come into contact with each other by their external surface at a central part of the structure 40.

[0073] With reference to figure 4, the cross members 41 and 42 are in this example connected to each other by a connecting member 43.

[0074] The connecting element 43 is configured to maintain the crossbeams 41 and 42 in the arrangement illustrated in figures 3 and 4 when the airship 1 is in flight.

[0075] With reference to figures 2 and 3, the crossbeams 41 and 42 each extend inside the envelope 2, in this case into the chamber of the airship 1, so that the ends 41A / 42A of each of the crossbeams 41 and 42 each open out of the envelope 2 through respective openings in the envelope 2.

[0076] With reference to Figure 2, the envelope 2 is here equipped with four annular flanges 45 (only one of them being visible in this figure) each arranged at the level of one of the respective openings of the envelope 2. The flanges 45 carried by the envelope 2 are intended to cooperate with connecting members 46 which are connected to the cross members 41 and 42 in order to ensure their connection with the envelope 2 (see also Figure 3).

[0077] Sealing can typically be improved by interposing sealing elements (not shown), such as O-rings, between the flanges 45 and the connecting elements 46.

[0078] Such a reinforcement structure 40 allows the attachment points of the envelope 2 to be stressed in a balanced way, in this example via the flanges 45 which fulfill the function of transmitting mechanical forces.

[0079] In the embodiment of figures 1 to 3, the propulsion system 3 includes shafts 51 and 52 forming a drive mechanism for the propulsion organs 6, 7, 8 and 9.

[0080] The drive mechanism is designed to change the orientation of the propulsion components.

[0081] In this example, trees 51 and 52 each extend within one of the respective crossbeams 41 and 42.

[0082] Thus, in the configuration of Figure 3, the shaft 51 extends around an axis A51 which is parallel to the direction D1, while the shaft 52 extends around an axis A52 parallel to the direction D3.

[0083] The ends of the shaft 51 are configured to open out of the cross member 41 to be connected respectively to the control surfaces 13 and 14, while the ends of the shaft 52 are configured to open out of the cross member 42 to be connected respectively to the control surfaces 15 and 16.

[0084] In this embodiment, each of the shafts 51 and 52 is configured to be driven in rotation around the corresponding axis A51 or A52 by a respective servomotor type actuator.

[0085] Figure 2 schematically illustrates one possible, but not limiting, location of one of these actuators 55, in this case intended to drive the shaft 51. The actuator 55 is here positioned outside the casing 2 and the cross member 41. Alternatively, the actuators can be housed in the cross members 41 and 42 or in another structure of the airship 1.

[0086] The actuator 55 shown in Figure 2 allows the shaft 51 to rotate around the axis A51. During its rotation, the shaft 51 is guided by the cross member 41, via guiding elements such as bearings (a single bearing 56 is visible in Figure 2). A rotation of the shaft 51 simultaneously moves the control surfaces 13 and 14 by a corresponding rotation around the axis A51, resulting in a corresponding change in the arrangement of the propulsion elements 6 and 7, and in particular the inclination or orientation of the axes A6 and A7.

[0087] Similarly, the actuator (not shown) associated with shaft 52 allows the shaft to rotate around axis A52. During its rotation, shaft 52 is guided by cross member 42, for example via guide elements such as bearings (not shown). A rotation of shaft 52 simultaneously moves control surfaces 15 and 16 by a corresponding rotation around axis A52, resulting in a corresponding change in the arrangement of propulsion elements 8 and 9, and in particular the inclination of axes A8 and A9.

[0088] Without limitation, the airship 1 may be designed to allow each of the shafts 51 and 52 to rotate a full turn around their axis A51 or A52. In other words, the propulsion elements may be vectored through 360°. A maximum range of angular rotation may be provided, for example, 360°, or 180°, or 90°, or any other value.

[0089] By way of non-limitation, the propulsion elements 12 / 55 of the propulsion system 3 and the tail assembly 4 can be connected to the electronic system of the airship 1 by cables (not shown) arranged on an external surface of the envelope 2. Taking into account the movement of the control surfaces and propulsion elements, the connection may be provided to define a play in the cables and / or may implement elements such as rotating electrical collectors (not shown).

[0090] The airship 1 of the invention makes it possible in particular to maintain the propulsion organs without using guy wires, which makes it possible to reduce drag.

[0091] In this example, which is by no means exhaustive, the DI direction is vertical and, in the configuration illustrated in Figure 1: - the propulsion unit 6 and the rudder 13 form a movable sub-assembly located vertically upwards, - the propulsion unit 7 and the rudder 14 form a movable sub-assembly located vertically downwards, - the propulsion unit s and the rudder 15 form a movable sub-assembly located horizontally on one side (e.g. left), and - the propulsion unit 9 and the rudder 16 form a movable sub-assembly located horizontally on a second side (e.g. right).

[0092] With reference to the initial configuration shown in Figure 1, the position of the propulsion units 6 and 7 and the control surfaces 13 and 14—that is, the vertical movable subassemblies—typically allows control of the position of the airship 1 around a yaw axis. For example, to move the airship 1 around the yaw axis, the propulsion units 6 and 7 and the control surfaces 13 and 14 can be moved from the initial configuration to that shown in Figure 5.

[0093] Furthermore, the position of the propulsion units 8 and 9 and the control surfaces 15 and 16—that is, the horizontally movable sub-assemblies—typically allows control of the airship 1's position around a pitch axis or of its altitude. For example, hovering can be achieved by arranging the propulsion units 6 and 7 and the control surfaces 13 and 14 in the configuration shown in Figure 6, specifically by tilting them 90° from their initial configuration. As another example, the airship 1 can be moved around its pitch axis by moving the propulsion units 6 and 7 and the control surfaces 13 and 14 from their initial configuration to the configuration shown in Figure 6.

[0094] In addition to the relative orientation of the propulsion organs and control surfaces, the various propulsion organs can be controlled in such a way as to produce differential thrust, in particular vertically and / or horizontally.

[0095] Thus, pitch control can be achieved in whole or in part by generating a differential thrust on the vertical axis, that is to say by controlling the propulsion organs 6 and 7 so that they generate different thrust forces from each other.

[0096] Similarly, yaw control can be achieved in whole or in part by generating differential thrust on the horizontal axis, i.e. by controlling the propulsion organs 8 and 9 so that they generate different thrust forces from each other.

[0097] The invention also makes it possible to remedy an engine failure. For example, in the event of a failure of the propulsion unit's engine 8, the resulting asymmetry can be compensated for by increasing the thrust generated by the propulsion unit 9, and the resulting sideslip angle can be corrected by acting on the vertical axis. As another example, in the event of a failure of one of the actuators 55, a differential thrust can be generated on the moving sub-assembly controlled by the other actuator.

[0098] The invention thus makes it possible to increase flight safety and improve propulsion efficiency, responsiveness, particularly during maneuvers requiring high precision of execution, as well as autonomy.

[0099] The invention is, of course, not limited to the embodiment illustrated in Figures 1 to 3. In particular, parts 13, 14, 15, and 16 can form not movable control surfaces but fixed stabilizers, the drive mechanism in this case being designed to move the propulsion elements independently of such stabilizers, for example, by attaching the propulsion elements directly to the ends of shafts 51 and 52 or, more generally, to the drive mechanism. Alternatively, the propulsion elements can be functionally independent of any stabilizer, the airship being able, of course, to include one or more stabilizers arranged on other parts of the airship.

[0100] In one embodiment variant, the airship is devoid of the reinforcing structure 40, the drive mechanism of the propulsion organs being able to be carried by a structure external to the envelope.

[0101] More generally, the airship can be configured to move one or more propulsion elements independently of any other moving parts of the airship. For example, in a variant of the embodiment shown in Figure 1, the airship may include a mechanism configured to independently control one or more of the propulsion elements and one or more of the moving parts of the tail assembly.

[0102] In the preceding description, the propulsion elements are arranged in two sub-assemblies, one extending horizontally and the other vertically when the airship is in the initial configuration of Figure 1. Of course, another orientation of the propulsion elements can be envisaged, for example with a 45° offset around the axis Al compared to the example in Figure 1. The propulsion elements can thus be arranged in two sub-assemblies, each extending obliquely from the vertical when the airship is in its initial configuration.

[0103] The propulsion units can also be actuated by a drive mechanism configured to drive each of the propulsion units independently of the other propulsion units, for example by means of servomotors each associated with one of the respective propulsion units.

[0104] The propulsion devices can of course be different from those described above, including for example a three-bladed propeller, or even an electric turbine.

[0105] In one embodiment variant, the airship may include a reinforcement structure, or through structure, receiving one or more elements carrying one or more non-steering propulsion organs, such elements being in this case fixed relative to the through structure, or formed by it.

[0106] Furthermore, the invention can be implemented on a rigid or semi-rigid envelope airship.

Claims

DEMANDS 1. Airship (1) comprising an envelope (2) and a propulsion system (3) provided with one or more propulsion organs (6, 7, 8, 9), each of the propulsion organs (6, 7, 8, 9) comprising a rotating element (11) such as a propeller movable in rotation about a respective axis of rotation (A6, A7, A8, A9) which defines an orientation of the corresponding propulsion organ with respect to the envelope (2).

2. Airship (1) according to claim 1, wherein the propulsion system (3) comprises a drive mechanism configured to change the orientation of one or more of said propulsion organs (6, 7, 8, 9).

3. Airship (1) according to claim 2, comprising one or more support structures (13, 14, 15, 16) which each support one of said propulsion members (6, 7, 8, 9), said drive mechanism comprising one or more drive members (51, 52) configured to move one or more of said support structures (13, 14, 15, 16) so as to change the orientation of one or more of said propulsion members (6, 7, 8, 9).

4. Airship (1) according to any one of claims 1 to 3, comprising one or more tail fins (4).

5. Airship (1) according to claims 3 and 4, wherein one or more of said tail assemblies (4) comprise: - one or more movable parts forming one or more of said support structures (13, 14, 15, 16), and / or - one or more movable parts which are configured to be actuated independently of said support structures.

6. Airship (1) according to any one of claims 3 to 5, incorporating the features of claim 3, wherein each of said drive members (51, 52) is configured to move two respective of said support structures (13, 14, 15, 16), and preferably wherein two of said drive members (51, 52) each form a drive shaft rotating about a respective axis of rotation (A51, A52), the axis of rotation (A51) of one of the drive shafts (51, 52) being preferably perpendicular to the axis of rotation (A52) of the other of said drive shafts (51, 52).

7. Airship (1) according to any one of claims 1 to 6, comprising a reinforcement structure (40) having one or more cross members (41, 42) each extending into a chamber formed by the envelope (2) and each connected to the envelope (2) by respective connecting members (46), the cross members (41, 42) preferably being connected to each other by an additional connecting member (43).

8. Airship (1) according to claims 6 and 7, wherein one or more of said crossbeams (41, 42) are configured to receive, and preferably to guide, one or more of said drive members (51, 52).

9. Airship (1) according to any one of claims 1 to 8, wherein the envelope (2) is flexible.

10. Method for controlling an airship (1) according to any one of claims 1 to 9.

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