Aerostatic assembly equipped with an improved retarding device

Abstract

Aerostatic Assembly Equipped with an Improved Deceleration Device. The invention relates to an aerostatic assembly (1) comprising: - a lifting element (2), - a deceleration device (3) for a payload (4), the deceleration device (3) comprising: a wing (30) forming an aerodynamic surface (30) and intended for decelerating said payload 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 lifting element (2) being connected to the rigid structure (31) to allow the wing (30) to tilt: from an ascending position to allow the ascent of said payload in the atmosphere, to a descending position to ensure the deceleration of said payload in the atmosphere. Figure of The abbreviation: Fig. 1

Description

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

[0001] The present invention relates to an aerostatic assembly designed to be equipped with a braking 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, particularly in the field of meteorology.

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

[0004] Once the desired altitude is reached and the mission accomplished, the aerostatic device is deflated, destroyed, or detached from the payload it carries. A braking device is then activated to slow the payload's descent into the atmosphere.

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

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

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

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

[0009] To this end, the invention relates to an aerostatic assembly comprising:

[0010] - a supporting element,

[0011] - a device for slowing down a load, referred to as the payload, to be transported,

[0012] the retarding device comprising:

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

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

[0015] - a rigid structure coupled to the wing and designed to allow the wing to 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 lifting element allows the ascent of the aerostatic assembly in the atmosphere, by orienting the wing direction, according to an ascent direction of the payload, to allow the ascent of said payload in the atmosphere,

[0018] to a descent position, along a payload descent direction, to ensure the deceleration of said payload in the atmosphere.

[0019] The invention advantageously provides an aerostatic assembly enabling the ascent of a payload, followed by its descent with deceleration in the atmosphere. More particularly, this is made possible by the wing of the deceleration device first assuming an ascent position allowing the lifting element to carry the aerostatic assembly to altitude with minimal aerodynamic resistance on the aerodynamic surface of the wing in the direction of ascent, and then a descent position where the lifting 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 braking device.

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

[0022] It will be understood that the wing direction along the ascent direction is distinct from the wing direction along the descent direction. More specifically, the angle formed between the vertical and the wing direction along the ascent direction is distinct from the angle formed between the vertical and the wing direction along the descent direction.

[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 braking device to tip from the ascending position to the descending position.

[0024] It will be understood that the lifting element can be separated or detached from the rigid structure and / or the braking device and / or the aerostatic assembly. In other In the case of a dull bluff, when the lifting element is separated or detached, it is no longer connected to the rigid structure and / or the retarding device and / or the aerostatic assembly.

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

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

[0027] Preferably, the angle formed between the vertical and the direction of the sail along 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 with respect to a perpendicular horizontal plane H.

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

[0030] For example, "rigid structure" means a structure supporting a payload and able to withstand the aerodynamic stresses it undergoes when falling through the atmosphere.

[0031] The aerodynamic stresses 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 dimensioned 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, including:

[0034] - a face of the aerodynamic surface, which is provided opposite the payload In the descending position, it presents 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 payload 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 linking device via the part central to said rigid structure,

[0040] - the central part of said rigid structure has a central opening intended to be traversed by the linking device and connecting the payload to the supporting 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 includes 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 includes a sheath element designed to be passed through the connecting device linking the payload to the lifting element,

[0045] - the retarder device is devoid of suspension cables,

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

[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 an aerostatic assembly at altitude as defined in the present invention, the method comprising the following steps, for example:

[0050] - destroy the supporting element or release the supporting element from the device retarder, for example separated the supporting element so as to cause the retarder device to tilt from the ascending position to the descending position.

[0051] Advantageously, a step of filling the lifting element with a suitable gas can be provided to allow the aerostatic assembly to rise to altitude.

[0052] Other features and advantages of the invention will become apparent from the following non-limiting description and the accompanying figures which schematically illustrate several embodiments of the invention.

[0053] Fig. 1 represents a perspective view of a retarding device of an aerostatic assembly according to a preferred configuration of the invention.

[0054] Fig. 2 shows a detail of Fig. 1 illustrating the convex nature of the sail

[0055] Fig.3 represents a detail of Fig.1 illustrating the passage, in the retarding device, of a linking device.

[0056] Figures 4a-c [Fig.4a] [Fig.4b] [Fig.4c] represent the tilting of the deceleration device from an ascending position illustrated in [Fig.4a] to a descending 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 includes, among other things, a lifting element 2, such as, for example, a balloon, a retarding device 3 (which will be described in more detail below), and a payload 4, such as, for example, including atmospheric meteorological measurement instruments.

[0059] The payload 4 may include one or more other type(s) of instrument(s) such as one or more of the following: meteorological measurement instruments, instruments for studying atmospheric chemistry, instruments for technology demonstrators or instruments for jettisonable probes.

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

[0061] The retarding 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 slowing down of the payload 4 during the descent into the atmosphere of the aerostatic assembly 1. The wing 30 has an aerodynamic center of pressure 30' forming an equilibrium point of the aerodynamic surface 30 during its descent into the atmosphere.

[0062] The wing 30 is preferably rigid, i.e. non-flexible. A wing 30 may be 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 type material 38.

[0063] The aerodynamic surface 30 of the wing 30 has a contour 30”, not limited to being represented in hexagonal form.

[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 pressure 30' is not in a plane containing the contour 30" when the aerodynamic surface 30 is convex. The advantage of a convex aerodynamic surface 30, for example along a direction forming an angle of about ten degrees with the horizontal plane H, is to position the aerodynamic center of pressure 30' above the center of mass 40' of the payload 4, thereby providing an aerodynamically stable assembly.

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

[0067] This direction D of wing 30 generally allows for the definition of an orientation direction of the retarding device 3, regardless of the shape of the wing 30.

[0068] For example, in the case of the configuration shown in [Fig.1], 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 to 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 may be possible, for example, to provide a flat aerodynamic surface 30, the direction D of the wing 30 of which passes through both 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 by means of 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 specifically, the retarder device 3 is shown with a high orientation corresponding to the ascent direction DI and a low orientation corresponding to a descent direction 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 previously defined downward direction.

[0074] This particular configuration of the wing 30 ensures resistance to the aerodynamic stresses experienced by the wing's aerodynamic surface 30 during its descent through the atmosphere. In particular, it allows the airflow received by the aerodynamic surface 30 to be evacuated laterally.

[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 part 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 part 31b extends around the aerodynamic center of thrust 30' of the aerodynamic surface 30 of the wing 30

[0078] The central part 31b allows the longitudinal stiffening elements 31a to be connected together by their proximal end 31a.

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

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

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

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

[0083] As shown in [Fig.2], the central part 31b has a base 32 from which extends a plurality of fingers 32a each having an opening 32a' to receive a longitudinal stiffening element 31a.

[0084] In an assembled configuration, the central part 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 traversed by a linking device 5 as will be described below.

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

[0087] With reference to [Fig.3], the aerostatic assembly 1 also includes the linking device 5 (described previously) intended to connect the payload 4 to the lifting element 2, via the central orifice 32a” of the base 32 of the central part 31b.

[0088] By way of non-limitation, the connecting device 5 may include a flexible linear element such as, for example, a flexible mechanical cable, a rope such as a halyard.

[0089] The linking device 5 is advantageously connected to the payload 4, and passes through the central orifice of said base 32, to be connected to the supporting 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 sleeve element or sleeve 30c is advantageously provided on the wing 30 to allow the connecting device 5 to be connected along the wing 30 from the central part 31b.

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

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

[0093] The arrangement of the linkage device 5 connecting the payload 4 to the lifting element 2 via the retarding device 3 advantageously allows the center of mass 40' of the payload 4 and the center of aerodynamic thrust 30' of the aerodynamic surface 30 to be kept aligned in a vertical direction at least in the ascending position and in the descending position of the aerostatic assembly 1.

[0094] With reference now to figures 4a-c, we will now describe a method of deploying at altitude the aerostatic assembly 1 according to the invention.

[0095] As shown in [Fig.4a], the aerostatic assembly 1 comprises the payload 4, the retarding 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 retarding device 3, as previously described.

[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 by means of the lifting element 2.

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

[0100] This configuration advantageously improves the ascent speed of the aerostatic assembly 1 since the aerodynamic stresses experienced by the wing 30 during ascent are minimal due to its intended orientation.

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

[0102] The destruction of the lifting element 2 when it is a dilatable 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 lifting element 2 causes the braking device 3 to tilt into a descent position, allowing the aerostatic assembly 1 to descend into the atmosphere, since the direction D of the wing 30 is oriented along a horizontal direction contained in a horizontal plane at the vertical direction described in the first step, that is, along the descent direction D2 of the payload 4.

[0105] Thus, in this descent position, the retarding device 3 is optimized to ensure a slowed descent into altitude since the aerodynamic stresses suffered 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.1].

[0107] It should be noted in particular that the aerostatic assembly 1 is devoid of suspension lines, i.e., it is devoid of a parachute. The decelerating device 3 according to the invention thus forms a preferred alternative to parachutes.

[0108] Obviously, the invention is not limited to the examples just described, and many modifications can be made to these examples without departing from the scope of the invention. In particular, the various features, forms, variants, and embodiments of the invention can be combined with one another in various ways, provided they are not incompatible or mutually exclusive. Specifically, all the variants and embodiments described above are combinable.

Claims

Demands

1. Aerostatic assembly (1) comprising: - a lifting element (2), - a deceleration device (3) for a load, referred to as the payload (4), to be transported, the deceleration device (3) comprising: - a wing (30) forming an aerodynamic surface (30), the wing being designed to decelerate 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 designed to allow the wing to form said aerodynamic surface (30), the lifting element (2) being connected to the rigid structure (31) so as to allow the wing (30) to tilt: from an ascending position, in which the lifting element (2) allows the aerostatic assembly (1) to ascend into the atmosphere, by orienting the direction (D) of the wing (30),along an ascent direction (D1) of the payload (4), to allow the ascent of said payload in the atmosphere, to a descent position, along a descent direction (D2) of the payload (4), to ensure the deceleration of said payload in the atmosphere.

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

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

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

5. Aerostatic assembly (1) according to the preceding claim, wherein 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 payload 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 linking 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 traversed by the linking 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, wherein the rigid structure (31) comprises a plurality of longitudinal stiffening elements (31a).

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

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