Aerostatic assembly equipped with an improved retarder device

Abstract

Aerostatic assembly equipped with an improved retarder device The invention relates to an aerostatic assembly (1) comprising: - a lift element (2), - a retarder device (3) for a payload (4), the retarder device (3) comprising: a wing (30) forming an aerodynamic surface (30 and provided for the retarder of said load in the atmosphere, the aerodynamic surface (30) having a contour (30'') comprising at least two points (30a, 30b) to define a direction (D) of the wing (30), - a rigid structure (31) coupled to the wing (30) to form said aerodynamic surface (30), the lift element (2) being connected to the rigid structure (31) to allow the tilting of the wing (30): from an ascent position to allow the ascent of said load in the atmosphere, to a descent position to ensure the retarder of said load in the atmosphere. Figure of the summary: Fig.1

Description

Title of the invention: Aerostatic assembly equipped with an improved retarder device

[0001] The present invention relates to an aerostatic assembly intended to be equipped with a retarder device. It also relates to a method for deploying such an aerostatic assembly at altitude.

[0002] The use of payloads is known, for example, in the context of scientific missions. These payloads make it possible, for example, to carry out measurements in the atmosphere and / or in the stratosphere, in the field of meteorology in particular.

[0003] Such a payload may be brought to a desired altitude using an aerostatic device, typically a weather balloon.

[0004] Once the desired altitude has been reached and the mission accomplished, the aerostatic device is deflated, destroyed or detached from the payload it is carrying. A retarder device is then activated to slow the descent into the atmosphere of the payload being carried.

[0005] Such a retarding device generally consists of a parachute which can be deployed during descent in order to bring the payload it is carrying to the ground.

[0006] However, such a parachute presents risks of anomalies on opening, in particular caused by the parachute lines. Indeed, given the low density of the air at high altitude, this deployment often leads to the lines becoming tangled due to the absence of sufficient aerodynamic forces.

[0007] The present invention aims to resolve the aforementioned drawbacks by proposing an aerostatic assembly equipped with a retarder device making it possible to avoid the risk of anomalies during its deployment.

[0008] The invention aims to overcome at least one of the drawbacks mentioned by proposing to provide an aerostatic assembly equipped with an improved retarder device.

[0009] For this purpose, the invention relates to an aerostatic assembly comprising:

[0010] - a supporting element,

[0011] - a device for slowing down a load, called a payload, to be transported,

[0012] the retarder device comprising:

[0013] - a wing forming an aerodynamic surface, the wing being provided for the slowing down of said charge in the atmosphere,

[0014] the aerodynamic surface having a contour comprising at least two points, the two points defining a sail direction,

[0015] - a rigid structure coupled to the wing and designed to allow the wing to form said aerodynamic surface,

[0016] the lifting element being connected to the rigid structure so as to allow the wing to tilt:

[0017] of an ascent position, in which the lift element allows the ascent of the aerostatic assembly in the atmosphere, by orienting the direction of the wings, according to a direction of ascent of the payload, to allow the ascent of said load in the atmosphere,

[0018] to a descent position, according to a payload descent direction, to ensure the slowing down of said load in the atmosphere.

[0019] The invention advantageously makes it possible to provide an aerostatic assembly allowing the ascent of a payload, then its descent with slowing down in the atmosphere. More particularly, this is made possible by the wing of the retarder device firstly taking an ascent position allowing the lift element to take the aerostatic assembly to altitude with minimal aerodynamic resistance on the aerodynamic surface of the wing in the direction of ascent, then a descent position where the lift element is destroyed or released to ensure the descent of the aerostatic assembly in the atmosphere with maximum aerodynamic resistance on the aerodynamic surface of the wing in the direction of descent.

[0020] It will be understood that in the descent position the lifting element is destroyed or released from the retarder device.

[0021] Thus, the solution according to the invention offers an economical and reliable solution allowing the sending of probes at altitude in the atmosphere, while allowing their controlled descent into the atmosphere. In this way, the aerostatic assembly according to the invention becomes reusable since the probe is no longer damaged by its fall in the atmosphere as is known from the prior art.

[0022] It will be understood that the sail direction in the direction of ascent is distinct from the sail direction in the direction of descent. More particularly, the angle formed between the vertical and the sail direction in the direction of ascent is distinct from the angle formed between the vertical and the sail direction in the direction of descent.

[0023] Preferably, the lifting element is configured to be destroyed and / or released, for example separated from the rigid structure, so as to cause the retarder device to tilt from the ascent position to the descent position.

[0024] It will be understood that the lift element may be separated or detached from the rigid structure and / or the retarder device and / or the aerostatic assembly. In other words dull, when the lifting element is separated or detached, it is no longer connected to the rigid structure and / or to the retarder device and / or to the aerostatic assembly.

[0025] Preferably, the angle formed between the vertical and the direction of sail according to the direction of ascent is zero.

[0026] Preferably, the angle formed between the vertical and the sail direction in the descent direction is at least 30° greater than the angle formed between the vertical and the sail direction in the ascent direction.

[0027] Preferably, the angle formed between the vertical and the direction of sail according to the direction of descent is at least greater than 30°, and advantageously it is between 30° and 90°, even more advantageously, it is equal to 90°.

[0028] It will be understood that the vertical, or vertical direction, is defined relative to a perpendicular horizontal plane H.

[0029] Optionally, by "vertical" is meant the direction of the gravity vector; and by "horizontal plane" is meant a plane perpendicular to the direction of the gravity vector.

[0030] For example, the term "rigid structure" means a structure supporting a payload and capable of resisting the aerodynamic stresses it undergoes when falling through the atmosphere.

[0031] The aerodynamic constraints applied to the rigid structure are for example equal to the weight of the payload to be slowed down.

[0032] Of course, the rigid structure is sized proportionally to the weight and / or volume of the payload intended to be transported.

[0033] Other features have been identified, taken alone or in combination according to any of their technically possible combinations, among which:

[0034] - a face of the aerodynamic surface, which is provided opposite the payload in the descent position, has a convex shape,

[0035] - said rigid structure comprises a central part extending around a center of aerodynamic thrust of the aerodynamic surface,

[0036] - the aerodynamic surface is perforated in an area surrounding the central part of said rigid structure,

[0037] - the payload has a center of mass, and

[0038] said rigid structure is connected to the payload so as to maintain the center of mass of the load and the center of aerodynamic thrust of the aerodynamic surface aligned in a vertical direction,

[0039] - the lifting element is connected to the payload by a connecting device via the part central part of said rigid structure,

[0040] - the central part of said rigid structure has a central orifice intended to be crossed by the connecting device and connect the payload to the lifting element,

[0041] - the connecting device comprises a flexible linear element such as, for example, a flexible mechanical cable, a rope such as a halyard,

[0042] - the rigid structure comprises a fastener by which the connecting device is connected to the supporting element,

[0043] - the rigid structure comprises a plurality of longitudinal elements of stiffening,

[0044] - the rigid structure comprises a sheath element intended to be crossed by the connecting device connecting the payload to the lifting element,

[0045] - the retarder device is devoid of hangers,

[0046] - the central part of said rigid structure is made of polymer, preferably based on polylactic acid (PLA), or based on acrylonitrile butadiene styrene (ABS), or based on glycolized polyester (PETg),

[0047] - alternatively, the central part of said rigid structure is made of metal,

[0048] - the longitudinal stiffening elements are made of carbon fiber, or alternatively in fiberglass.

[0049] The invention also relates to a method for deploying at altitude an aerostatic assembly as defined in the present invention, the method comprising the following steps, for example:

[0050] - destroy the lift element or release the lift element from the device retarder, for example separating the lift element so as to cause the retarder device to tilt from the ascent position to the descent position.

[0051] Advantageously, a step of filling the lift element using an appropriate gas may be provided to enable the aerostatic assembly to rise to altitude.

[0052] Other characteristics and advantages of the invention will appear on reading the non-limiting description which follows and the appended figures which schematically illustrate several embodiments of the invention.

[0053] [Fig.l] [Fig.l] represents a perspective view of a retarder device of an aerostatic assembly according to a preferred configuration of the invention.

[0054] [Fig.2] [Fig.2] represents a detail of [Fig.l] illustrating the convex character of the sail

[0055] [Fig.3] [Fig.3] represents a detail of [Fig.l] illustrating the passage, in the retarder device, of a connecting device.

[0056] Figures 4a-c [Fig.4a] [Fig.4b] [Fig.4c] show the switching of the retarder device from an ascent position illustrated in [Fig.4a] to a descent position illustrated in [Fig.4c].

[0057] In [Fig.4a], an aerostatic assembly 1 is shown according to a preferred configuration of the invention.

[0058] The aerostatic assembly 1 comprises, among other things, a lifting element 2, such as, for example, a balloon, a retarder device 3 (which will be described in more detail below), and a payload 4, such as, for example, comprising atmospheric meteorological measuring instruments.

[0059] The payload 4 may comprise one or more other type(s) of instrument(s) such as one or more of: meteorological measuring instruments, atmospheric chemistry study instruments, technological demonstrator instruments or droppable probe instruments.

[0060] In [Fig. 1], an embodiment of a retarder device 3 intended to equip the aerostatic assembly 1 is shown.

[0061] The retarder device 3 comprises a rigid structure 31 and a wing 30, the wing 30 having an aerodynamic surface 30. The wing 30 is advantageously designed to allow the payload 4 to be slowed down during the descent into the atmosphere of the aerostatic assembly 1. The wing 30 comprises an aerodynamic center of thrust 30' forming a point of equilibrium of the aerodynamic surface 30 during its descent into the atmosphere.

[0062] The wing 30 is preferably rigid, that is to say not flexible. It is possible to provide a wing 30 made of rigid sheet metal, preferably of low thickness, for example less than 2 millimeters, or alternatively a wing made of composite fabric, preferably carbon or fiberglass, or alternatively a wing made of Skytex 38 type material.

[0063] The aerodynamic surface 30 of the wing 30 has a contour 30”, non-limitingly represented in a hexagonal shape.

[0064] This contour 30'' comprises at least two points 30a, 30b opposite each other with respect to the aerodynamic thrust center 30' of said surface and / or with respect to a plane P passing through the aerodynamic thrust center 30' of said surface.

[0065] Advantageously, the aerodynamic center of thrust 30' is not in a plane containing the contour 30” since the aerodynamic surface 30 is convex. The advantage of a convex aerodynamic surface 30, for example in a direction forming an angle of about ten degrees relative to the horizontal plane H, is to position the aerodynamic center of thrust 30' above the center of mass 40' of the payload 4, in order to provide an aerodynamically stable assembly.

[0066] These two points 30a, 30b define a direction D of sail 30 passing through each of them, and, depending on the shape of said surface, also through the center of aerodynamic thrust 30' of said surface.

[0067] This direction D of the wing 30 generally makes it possible to define a direction of orientation of the retarder device 3, regardless of the shape of the wing 30.

[0068] For example, in the case of the configuration shown in [Fig.l], since the aerodynamic surface 30 is convex (as will be described in more detail in this configuration of the invention), the direction D of the wing 30 passes through two points 30a, 30b opposite each other with respect to the plane P without passing through the aerodynamic center of thrust 30'.

[0069] In another configuration of the invention not described, it will be possible, for example, to provide a flat aerodynamic surface 30, the direction D of the sail 30 of which passes both through each of the two points 30a, 30b, as well as through the aerodynamic center of thrust 30'.

[0070] The aerodynamic surface 30 of the wing 30 is maintained in its shape using the rigid structure 31 to which it is coupled.

[0071] With reference to [Fig.2], the retarder device 3 is shown oriented in a descent configuration. More particularly, the retarder device 3 is shown in a high orientation corresponding to the direction of ascent DI and a low orientation corresponding to a direction of descent D2 of the aerostatic assembly 1 as a whole.

[0072] The direction of ascent DI and the direction of descent D2 correspond to vertical directions.

[0073] A preferred and non-limiting configuration of the invention is shown here, in which the aerodynamic surface 30 has a convex shape on the side of its face 30'” provided opposite the payload 4 in the descent position, i.e. its face 30'” oriented towards the low direction previously defined.

[0074] This particular configuration of the wing 30 makes it possible to ensure resistance to the aerodynamic stresses that the aerodynamic surface 30 of the wing 30 undergoes during its descent into the atmosphere. In particular, it makes it possible to evacuate laterally the flow of air received by the aerodynamic surface 30.

[0075] The rigid structure 31 comprises a plurality of longitudinal stiffening elements 31a distributed around the aerodynamic thrust center 30' of the aerodynamic surface (30) 30.

[0076] As shown in [Fig.2], each stiffening element 31a extends from a proximal end 31al coupled to a finger 32a of a central portion 31b of the rigid structure 31 to a distal end 31a2 coupled to a reinforcement element 30e of the rigid structure 30 so as to keep the aerodynamic surface 30 taut.

[0077] The central portion 31b extends around the aerodynamic center of thrust 30' of the aerodynamic surface 30 of the wing 30

[0078] The central part 31b makes it possible to connect the longitudinal stiffening elements 31a together by their proximal end 31 al.

[0079] The longitudinal stiffening elements 31a may be, for example, made of carbon fibers.

[0080] To couple these longitudinal stiffening elements 31a to the wing 30, it will be possible to provide sheaths 30c (shown in dotted lines) associated with the wing 30, and into which these longitudinal stiffening elements 31a are threaded.

[0081] For example, these 30c sheaths can be made of the same material as the sail.

[0082] The 30c sheaths can be made of composite fabric, preferably carbon or made of fiberglass, or alternatively made of Skytex 38 type fabric.

[0083] As shown in [Fig.2], the central portion 31b comprises a base 32 from which extends a plurality of fingers 32a each having an opening 32a' for receiving a longitudinal stiffening element 31a.

[0084] In an assembled configuration, the central portion 31b and the longitudinal elements 31a are held fixed together.

[0085] The base 32 of the central part 31b also has a central orifice 32a” in its center intended to be crossed by a connecting device 5 as will be described below.

[0086] The central part 31b of said rigid structure 31 may be made of polymer material, preferably based on polylactic acid (PLA).

[0087] With reference to [Fig. 3], the aerostatic assembly 1 further comprises the connecting device 5 (described previously) provided for connecting the payload 4 to the lifting element 2, this via the central orifice 32a” of the base 32 of the central part 31b.

[0088] In a non-limiting manner, the connecting device 5 may comprise a flexible linear element such as, for example, a flexible mechanical cable, a rope such as a halyard.

[0089] The connecting device 5 is advantageously connected to the payload 4, and passes through the central orifice of said base 32, to be connected to the lifting element 2 by means of a hook 30d, also forming a reinforcement element 30e for holding the stiffening element 31a, the hook 30d being provided at the end of a longitudinal stiffening element 31a.

[0090] A sheath element or sheath 30c is advantageously provided on the wing 30 to enable the connecting device 5 to be connected, along the wing 30, to the attachment 30d from the central part 31b.

[0091] Alternatively, the sheath element 30c could be replaced by a fiberglass tube configured to be crossed by at least a portion of the connecting device 5.

[0092] It will be noted in particular that the payload 4 has a center of mass 40' shown in [Fig.4a].

[0093] The arrangement of the connecting device 5 connecting the payload 4 to the lift element 2 via the retarder device 3 advantageously makes it possible to maintain the center of mass 40' of the payload 4 and the center of aerodynamic thrust 30' of the aerodynamic surface 30 aligned in a vertical direction at least in the ascent position and in the descent position of the aerostatic assembly 1.

[0094] Referring now to figures 4a-c, a method of deploying at altitude the aerostatic assembly 1 according to the invention will now be described.

[0095] As shown in [Fig.4a], the aerostatic assembly 1 comprises the payload 4, the retarder device 3 and the lifting element 2, for example a balloon.

[0096] The lifting element 2 can be connected to the payload 4 via the retarder device 3, as described previously.

[0097] In a first step of this deployment method, the lifting element 2 is filled with a suitable gas, for example helium.

[0098] This filling allows the aerostatic assembly 1 to rise in altitude via the lifting element 2.

[0099] The arrangement according to the invention then makes it possible to arrange the wing 30 of the retarder device 3 in an ascent position allowing the ascent of the aerostatic assembly 1 in the atmosphere while orienting the direction D of the wing 30 according to the ascent direction DI of the payload 4 corresponding to a vertical direction.

[0100] This configuration advantageously makes it possible to improve the ascent speed of the aerostatic assembly 1 since the aerodynamic constraints undergone by the wing 30 during ascent are minimal due to its intended orientation.

[0101] In a second step of the method, the lifting element 2 is destroyed, or else released from the attachment 30d of the retarder device 3.

[0102] The destruction of the support element 2 when it is an expandable balloon occurs when the envelope of the balloon reaches its maximum volume, this occurs for example at a predetermined altitude when the external pressure is low.

[0103] When the lifting element 2 is a non-expandable balloon, the separation is for example carried out by a mechanical or pyrotechnic device remotely controlled from the ground.

[0104] The destruction or separation of the lift element 2 causes the retarder device 3 to tilt into a descent position allowing the descent of the aerostatic assembly 1 into the atmosphere, since the direction D of the wing 30 is oriented in a horizontal direction included in a plane horizontal to the vertical direction described in the first step, i.e. according to the direction of descent D2 of payload 4.

[0105] Thus, in this descent position, the retarder device 3 is optimized to ensure a slowed descent to altitude since the aerodynamic constraints undergone by the wing 30 during the ascent are maximum due to its intended orientation.

[0106] The controlled descent of the aerostatic assembly 1 can be advantageously improved by opening the aerodynamic surface 30 in a zone Z surrounding the central part 31b, as shown in [Fig.l].

[0107] It will be noted in particular that the aerostatic assembly 1 is devoid of suspension lines, that is to say that it is devoid of a parachute. The retarder device 3 according to the invention then forms a preferred alternative to parachutes.

[0108] Obviously, the invention is not limited to the examples which have just been described and numerous adjustments can be made to these examples without departing from the scope of the invention. In particular, the different characteristics, forms, variants and embodiments of the invention can be associated with each other in various combinations insofar as they are not incompatible or mutually exclusive. In particular, all the variants and embodiments described above can be combined with each other.

Claims

Claims

1. Aerostatic assembly (1) comprising: - a lift element (2), - a retarder device (3) for a load, called a payload (4), to be transported, the retarder device (3) comprising: - a wing (30) forming an aerodynamic surface (30), the wing being provided for the retarder of said load in the atmosphere, the aerodynamic surface (30) having a contour (30”) comprising at least two points (30a, 30b), the two points (30a, 30b) defining a direction (D) of the wing (30), - a rigid structure (31) coupled to the wing (30) and provided to allow the wing to form said aerodynamic surface (30), the lift element (2) being connected to the rigid structure (31) so as to allow the tilting of the wing (30): from a climbing position, in which the element lift (2) allows the ascent of the aerostatic assembly (1) in the atmosphere, by orienting the direction (D) of the wing (30),according to a direction of ascent (Dl) of the payload (4), to allow the ascent of said load in the atmosphere, to a descent position, according to a direction of descent (D2) of payload (4), to ensure the slowing down of said load in the atmosphere.,

2. Aerostatic assembly (1) according to the preceding claim, in which the lift element (2) is configured to be destroyed and / or released, for example separated from the rigid structure (31), so as to cause the retarder device (3) to tilt from the ascent position to the descent position.

3. Aerostatic assembly (1) according to one of the preceding claims, wherein a face (30”) of the aerodynamic surface (30), which is provided facing the payload (4) in the descent position, has a convex shape.

4. Aerostatic assembly (1) according to one of the preceding claims, wherein said rigid structure (31) comprises a central portion (31b) extending around an aerodynamic center of thrust (30') of the aerodynamic surface (30).

5. Aerostatic assembly (1) according to the preceding claim, in which the aerodynamic surface (30) is perforated in a zone (Z) surrounding the central part (31b) of said rigid structure (31).

6. Aerostatic assembly (1) according to the preceding claim, wherein the payload (4) has a center of mass (40'), and said rigid structure (31) is connected to the payload (4) so ​​as to maintain the center of mass (40') of the load and the center of aerodynamic thrust (30') of the aerodynamic surface (30) aligned in a vertical direction.

7. Aerostatic assembly (1) according to any one of claims 4 to 6, wherein the lifting element (2) is connected to the payload (4) by a connecting device (5) via the central part (31b) of said rigid structure (31).

8. Aerostatic assembly (1) according to claim 7, wherein the central part (31b) of said rigid structure (31) has a central orifice (30a”) provided to be crossed by the connecting device (5) connecting the payload (4) to the lifting element (2).

9. Aerostatic assembly (1) according to any one of claims 7 or 8, wherein the connecting device (5) comprises a flexible linear element such as, for example, a flexible mechanical cable, a rope such as a halyard.

10. Aerostatic assembly (1) according to any one of the preceding claims, in which the rigid structure (31) comprises a plurality of longitudinal stiffening elements (31a).

11. Method for deploying at altitude an aerostatic assembly (1) according to any one of the preceding claims, the method comprising the following steps: - destroying the lift element (2) or releasing the lift element (2), for example separating the lift element from the retarder device (3) so as to cause the retarder device (3) to tilt from the ascent position to the descent position.

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