Flight system comprising pivotable propulsion modules

Abstract

The present invention relates to a flight system (2) comprising: a harness (4) configured to be worn by a user (1), said harness (4) at least partially covering the bust and surrounding the hips of the user (1); a plurality of primary propulsion modules (6) connected to the harness (4), the plurality of primary modules (6) being distributed symmetrically at the hips of the user (1), the primary modules (6) being configured to exert a primary thrust force so as to raise or maintain the user (1) in the air; at least one energy reservoir (10) configured to supply energy to the plurality of propulsion modules; the flight system (2) being characterized in that the plurality of primary propulsion modules (6) is pivotable at least between a vertical flight configuration and a horizontal flight configuration. Abstract figure: Figure 1

Description

Title of the invention: Flight system comprising pivotable propulsion modules Technical field

[0001] The present invention relates to the technical field of flight systems.

[0002] More particularly, the present invention relates to the technical field of individual flight systems, including a “JetPack” type individual flight system. STATE OF THE ART

[0003] Known from the state of the art is an individual flight system comprising at least one propulsion module configured to exert a thrust force making it possible to lift or maintain a user equipped with the flight system. Such a flight system generally comprises a harness configured to be worn by the user like a backpack, the propulsion module then being located on the user's back. The flight system is then commonly referred to as being of the "JetPack" type.

[0004] Known from the prior art is a “JetPack” type flight system comprising additional propulsion modules. For example, a flight system is described in which said additional propulsion modules are attached to the arms, legs and plexus of the user. The user can then fly in a flight configuration known as “vertical flight”, in which a frontal plane of the user’s body extends substantially perpendicular to the ground. Such a flight system has the advantage, for a quantity of onboard energy, of being able to distribute a plurality of thrust forces over the entire body of the user, thus facilitating the stabilization of the user in the air. Document GB2570773A describes a similar device, an additional propulsion module being attached to the lower back of the user.

[0005] As an example, another embodiment of “vertical flight” is described in document US2018208312A1, in which a platform equipped with a propulsion module is attached to the feet of a user by means of boots occupying the harness function previously described.

[0006] Alternatively, document US10364028B1 describes a flight system in which said propulsion modules are attached only to the arms, legs and sides of the trunk of the body of a user equipped with the flight system. The user can then fly in a flight configuration, called "horizontal flight", in which the frontal plane of the user's body extends substantially parallel to the ground. Such a flight system also has the advantage of being able to distribute a plurality of thrust forces over the user's entire body, facilitating the user's stabilization in the air.

[0007] However, existing flight systems have the disadvantage of forcing the user to maintain a substantially identical posture throughout the entire flight, in other words, the orientation of the frontal plane of the user's body is substantially invariant during the flight. In addition, a user flying in a vertical flight configuration, respectively horizontal flight, must take off and land in the same vertical flight configuration, respectively horizontal flight. Furthermore, any flight in an intermediate configuration is also prohibited. Furthermore, in these systems, the user's limbs, i.e. his arms and / or legs, are mobilized by the propulsion system, limiting the user's freedom of movement.Finally, in existing flight systems, the stability and balance of the user in flight are managed by the user alone, depending on his pro-prioception capacity and his mastery of the flight system, which can put him at risk of falling, particularly in the case of a novice user.

[0008] The invention therefore aims to resolve all or part of the problems of the state of the art, by proposing a flight system equipping a user and allowing him to vary his posture during the flight, simple to access and presenting increased maneuverability leaving the user's limbs free. PRESENTATION OF THE INVENTION

[0009] More specifically, the invention relates to a flight system comprising: • a harness configured to be worn by a user, said harness at least partially covering the bust and surrounding the user's hips; • a plurality of primary propulsion modules connected to the harness, the plurality of primary modules being distributed symmetrically at the level of the user's hips on either side of a sagittal plane of the user's body, the primary modules being configured to exert a primary thrust force so as to raise or maintain the user in the air; • at least one energy reservoir configured to supply energy to the plurality of primary propulsion modules.

[0010] The flight system is remarkable in that the plurality of primary propulsion modules is pivotable, by means of ball joints between the harness and the plurality of primary propulsion modules, at least between a vertical flight configuration in which a frontal plane of the user's body extends perpendicularly to the ground and a horizontal flight configuration in which the frontal plane of the user's body extends parallel to the ground.

[0011] The term "sagittal plane" means an anatomical plane of the user's body, passing through the center of gravity of the user's body and which symmetrically divides the body into a right part and a left part.

[0012] The term "frontal plane" means an anatomical plane of the user's body, passing through the center of gravity of the user's body, perpendicular to the sagittal plane and which divides the body into a front part and a rear part.

[0013] The term "transverse plane" means an anatomical plane of the user's body, passing through the center of gravity of the user's body, perpendicular to the sagittal plane as well as to the frontal plane and which divides the body into an upper part and a lower part.

[0014] The term "bust" means the upper part of the user's body, which, unless otherwise specified, designates both the user's torso and the user's back.

[0015] Thanks to such a combination of characteristics, such a flight system allows an equipped user to fly in any flight configuration between the horizontal flight configuration and the vertical flight configuration, and to switch from one configuration to another during the flight. Thus, the user can simply choose the most appropriate configuration, for example depending on the flight phase, the stability conditions or the topology of the environment flown over. For example, the user can perform a takeoff operation in the vertical flight configuration and then, when reaching a satisfactory altitude, make a transition from the vertical flight configuration to the horizontal flight configuration. This applies to both the horizontal flight configuration on the stomach and the horizontal flight configuration on the back.In the same way, the user can make a transition from the horizontal flight configuration to the vertical flight configuration, for example to perform a landing operation. In addition, such a flight system leaves the user's hands and legs free, simplifying flight. The user can then interact with his or her immediate environment, for example to perform manual tasks using tools or to stand on structures without constantly worrying about his or her stability and balance in flight. Such a flight system is thus configured so as to guarantee the balance and stability of the user in flight, whatever the flight configuration and whatever his or her proprioception capacity and mastery of the flight system.

[0016] Advantageously, the primary thrust force is parallel to the frontal plane in the vertical flight configuration and the primary thrust force is perpendicular to the frontal plane in the horizontal flight configuration. In such a configuration, the flight system allows the user to take off or land perpendicular to the ground in the vertical flight configuration as in the horizontal flight configuration. Such a configuration also allows hovering.

[0017] Advantageously, the plurality of primary modules is pivotable into a takeoff configuration in which the thrust force of each of the primary modules 6 is perpendicular to the sagittal plane and oriented away from the user so that the primary thrust force is zero. In such a configuration, the user on the ground can adjust the primary thrust force without the latter being oriented towards the ground, and move from the takeoff configuration to one of the flight configurations when the thrust is sufficient for the user to be able to rise completely without risk.

[0018] Advantageously, the flight system comprises a plurality of secondary propulsion modules connected to the harness, the plurality of secondary propulsion modules being distributed symmetrically, above the shoulders of the user and configured to exert a secondary thrust force. In such a configuration, the thrust forces raising the user are partially distributed over the upper body of the user, making it possible to gain stability, particularly in a horizontal flight configuration.

[0019] Advantageously, the harness comprises knee pads configured to be worn by the user and a plurality of tertiary propulsion modules connected to the knee pads, the plurality of tertiary propulsion modules being distributed symmetrically at the user's knees and configured to exert a tertiary thrust force. In such a configuration, the thrust forces lifting the user are partially distributed over the user's lower body, providing increased stability, particularly in a vertical flight configuration.

[0020] Advantageously, the energy reservoir is secured to the harness at the user's chest. In such a configuration, the user carries his own energy reserves. The reservoir is, for example, located on the user's back.

[0021] Advantageously, the tank comprises a first compartment configured to supply the propulsion modules on a first side of the sagittal plane and a second compartment configured to supply the propulsion modules on a second side of the sagittal plane. In such a configuration, the position of the tanks can be adapted to be as close as possible to the supplied modules. In addition, a portion of the user's back can be left free, for example to accommodate additional equipment.

[0022] According to one embodiment, the flight system comprises a dorsal propulsion module connected to the harness at the user's torso and configured to exert a dorsal thrust force. The dorsal thrust force is parallel to the frontal plane of the user. In the vertical flight configuration, the dorsal thrust force contributes to the vertical movement of the user. In the horizontal flight configuration horizontal, the back thrust force allows the user to move horizontally. In any intermediate configuration, the back thrust force contributes to both the vertical and horizontal movement of the user. The back thrust force also contributes to maintaining airborne stability, particularly when hovering.

[0023] Advantageously, the primary propulsion modules on the same given side of the sagittal plane are secured to at least one adjacent primary module, a single primary propulsion module being in a ball joint connection with the harness. In such a configuration, all of the propulsion modules on the same given side of the sagittal plane can pivot simultaneously using a single pivot connection, simplifying the manufacture of the flight system.

[0024] Advantageously, each primary propulsion module on the same given side of the sagittal plane is in ball joint connection with the harness, the pivoting of a given primary propulsion module being independent of the pivoting of the other primary propulsion modules on the same side. In such a configuration, each primary propulsion module on a given side can exert a thrust force in a different direction, making it possible to further diversify the flight configurations.

[0025] Advantageously, the plurality of primary propulsion modules is pivotable in a forward configuration in which the primary thrust force forms a first forward angle relative to the ground. In such a configuration, a vertical component of the primary thrust force allows the user to be kept in the air or raised, i.e. the user to move vertically, and a horizontal component of the primary thrust force then allows horizontal movement.

[0026] Advantageously, the primary modules on a first side of the sagittal plane pivot synchronously and the primary modules on a second side of the sagittal plane pivot synchronously, the pivoting of the modules on the first side and the modules on the second side being independent. Thus, the user's movement possibilities are improved, for example to rotate on himself or move horizontally in the frontal plane.

[0027] Advantageously, the primary propulsion modules on the same given side of the sagittal plane are distributed symmetrically with respect to the frontal plane of the user's body. In such a configuration, the horizontal displacement for a user is identical when the user moves forward of the frontal plane or when the user moves backward of the frontal plane. PRESENTATION OF FIGURES

[0028] The invention will be better understood on reading the following description, given solely by way of example, and referring to the appended drawings given as of non-limiting examples, in which identical references are given to similar objects and on which:

[0029] [Fig.l] is a schematic representation in front isometric perspective of a user equipped with a flight system according to a first embodiment of the invention, in a vertical flight configuration;

[0030] [Fig.2] is a schematic representation in rear isometric perspective of a user equipped with a flight system according to a second embodiment of the invention, in the vertical flight configuration;

[0031] [Fig. 3] is a schematic representation in front isometric perspective of a user equipped with a flight system according to a third embodiment in the vertical flight configuration;

[0032] [Fig.4] is a schematic representation in front isometric perspective of a user equipped with the flight system of [Fig.l] in a vertical flight configuration;

[0033] [Fig.5] is a schematic representation in rear isometric perspective of a user equipped with the flight system of [Fig.l] in the horizontal flight configuration;

[0034] [Fig.6] is a schematic representation in front isometric perspective of a user equipped with the flight system of [Fig.l] in a takeoff configuration;

[0035] [Fig.7] is a schematic representation in front isometric perspective of a user equipped with the flight system of [Fig.l] in a first forward configuration

[0036] [Fig.8] is a schematic representation in rear isometric perspective of a user equipped with the flight system of [Fig.l] in another variation of the forward configuration.

[0037] [Fig.9] is a schematic representation in front isometric perspective of a user equipped with the flight system of [Fig.l], in a rotational configuration;

[0038] [Fig. 10] is a schematic representation in front isometric perspective of a user equipped with the flight system of [Fig.l], in a turning configuration.

[0039] It should be noted that the figures set out the invention in detail to enable the invention to be implemented; although not limiting, said figures serve in particular to better define the invention where appropriate.

[0040] In the description and the claims, the terminology longitudinal, transverse and vertical will be adopted without limitation with reference to the trihedron X, Y, Z indicated in the figures. DETAILED DESCRIPTION OF THE INVENTION

[0041] The invention relates to a flight system 2, in particular an individual flight system 2 of the “JetPack” type equipping a user 1, as illustrated in [Fig.l].

[0042] The body of the user 1 has three anatomical planes intersecting at the level of the user's center of gravity when it is not equipped with the flight system 2. A first anatomical plane, called the "sagittal plane", divides the user's body in a substantially symmetrical manner into a right part and a left part.

[0043] A second anatomical plane, called the "frontal plane", divides the body into a front part and a rear part. The frontal plane is perpendicular to the sagittal plane.

[0044] A third anatomical plane, called the "transverse plane", divides the body into an upper part and a lower part. The transverse plane is perpendicular to the sagittal plane and the frontal plane.

[0045] The flight system 2 comprises a harness 4 configured to at least partially cover the bust and surround the hips of the user 1. The hip is understood here as the joint which forms the junction between the legs and the bust of the user 1. Here, the harness 4 is a full suit, covering the body of the user 1. Alternatively, the harness 4 may comprise several pieces equipped independently of each other.

[0046] The harness 4 supports a plurality of primary propulsion modules 6. The primary propulsion modules 6 are configured to exert a primary thrust force making it possible to raise or maintain the user 1 in the air. The primary modules 6 are distributed symmetrically at the level of the hips of the user 1, on either side of the sagittal plane of the body of the user 1. In other words, a first part of the primary modules 6 is located on the side of the left part of the body of the user 1 and a second part of the primary modules is located on the side of the right part of the body of the user 1. The primary modules 6 can optionally be housed in the same casing, as shown in [Fig.l], in which each casing here accommodates three primary modules 6. The flight system 2 can naturally comprise in total an even number of primary modules other than six, for example two, four, or eight modules.

[0047] Preferably, the primary modules 6 on the same side of the sagittal plane are distributed symmetrically with respect to the frontal plane of the body of the user 1. In such a configuration, the horizontal displacement for the user 1 is identical when the user 1 moves forward of the frontal plane or when the user 1 moves backward of the frontal plane. In the remainder of the description, we will speak of advancement to describe both the forward displacement of the frontal plane and the backward displacement of the frontal plane.

[0048] More preferably, the primary propulsion modules 6 on the same given side of the sagittal plane are integral with at least one adjacent primary module 6, a single primary propulsion module being in ball joint connection 12 with the harness 4. On the [Fig.l], the primary module 6 included in the frontal plane is the module in ball joint connection 12 with the harness 4. This primary module 6 is in connection with two other primary modules 6, one in front of the frontal plane and the other behind the frontal plane. In such a configuration, all of the primary propulsion modules 6 on the same given side of the sagittal plane can pivot simultaneously using a single ball joint connection 12, simplifying the manufacture of the flight system 2.

[0049] To generate a thrust force, the primary modules 6 are supplied with energy by at least one tank 10. Here, the tank 10 is located on the torso of the user 1 and is integral with the harness 4. The primary propulsion modules 6 can operate using a liquid, solid or gaseous fuel stored in the tank 10 in the case of thermal propulsion, for example kerosene, hydrogen or liquefied natural gas, but can also be supplied by electrical energy, the tank 10 then comprising at least one electric battery or an electric current generator system.

[0050] The plurality of primary modules 6 is pivotable, by means of ball joints 12, between the harness 4 and the plurality of primary modules 6. Thus, the primary modules 6 allow the user to fly in a flight configuration called "vertical flight" and a flight configuration called "horizontal flight". In the vertical flight configuration, the frontal plane of the user's body extends perpendicular to the ground, in other words perpendicular to a reference plane X, Y. In the horizontal flight configuration, the frontal plane of the user's body extends parallel to the ground, in other words parallel to the reference plane X, Y. The flight system 2 allows the equipped user 1 to fly in a horizontal flight configuration and / or a vertical flight configuration, and to switch from one configuration to another during the flight.Thus, the user can choose the most appropriate configuration, for example depending on the flight phase, stability conditions or the topology of the environment flown over. For example, user 1 can perform a takeoff operation in a vertical flight configuration and then, when reaching a satisfactory altitude, perform a transition from the vertical flight configuration to the horizontal flight configuration. In the same way, user 1 can perform a transition from the horizontal flight configuration to the vertical flight configuration, for example to perform a landing operation. The flight system 2 can also allow user 1 to fly in any flight configuration between the horizontal flight configuration and the vertical flight configuration.Such a flight system is thus configured to guarantee the balance and stability of the user in flight, whatever the flight configuration and whatever his proprioception capacity and his mastery of the flight system.

[0051] To improve the comfort of the user 1, in particular in the flight configuration horizontal, the harness 4 may include retractable rods (not shown) which can serve as supports for the user's torso or legs.

[0052] In the embodiment illustrated in [Fig. 1], the primary thrust force is parallel to the frontal plane in the vertical flight configuration and the primary thrust force is perpendicular to the frontal plane in the horizontal flight configuration. In such a configuration, the flight system 2 allows the user 1 to take off or land perpendicular to the ground in both the vertical flight configuration and the horizontal flight configuration. Such a configuration also allows hovering.

[0053] It should be noted that by "primary thrust force" is meant a force resulting from a thrust force of each primary propulsion module 6 taken individually. Thus, as long as this resultant is parallel to the frontal plane in vertical flight and perpendicular to the frontal plane in the horizontal flight configuration, the thrust force of a primary propulsion module 6 taken alone can have a different orientation, compensated by the orientation of the other primary propulsion modules 6.

[0054] [Fig. 2] illustrates the flight system 2 in another embodiment of the invention. Here, the flight system 2 comprises a first tank 10 configured to supply the propulsion modules on a first side of the sagittal plane and a second tank 10 configured to supply the propulsion modules on another side of the sagittal plane. In such a configuration, the position of the tanks 10 can be adapted to be as close as possible to the supplied modules. In addition, a portion of the back of the user 1 can be left free, for example to simplify the reception of additional equipment. In [Fig. 2], the flight system 2 then comprises a dorsal propulsion module 20, connected to the harness 4, at the level of the user's back. The dorsal propulsion module 20 is configured to exert a dorsal thrust force. The dorsal thrust force is parallel to the frontal plane of the user 1.In the vertical flight configuration, the dorsal thrust force contributes to the vertical movement of the user 1. In the horizontal flight configuration, the dorsal thrust force allows the horizontal movement of the user 1. It should be noted that the flight system 2 may comprise a dorsal propulsion module 20 even if it comprises a single tank 10.

[0055] [Fig. 3] illustrates the flight system 2 in another embodiment of the invention. Here, the flight system 2 comprises in particular a plurality of secondary propulsion modules 14 connected to the harness 4, the plurality of secondary propulsion modules 14 being distributed symmetrically, above the shoulders of the user 1 and configured to exert a secondary thrust force. Here, the plurality of secondary modules 14 is pivotable via ball joints 12 between the harness 4 and the plurality of secondary modules 14, at least between the flight configuration vertical in which the secondary thrust force is perpendicular to the frontal plane and the horizontal flight configuration in which the secondary thrust force is parallel to the frontal plane. In such a configuration, the thrust forces lifting user 1 are partially distributed over the user's upper body, providing increased stability, particularly in the horizontal flight configuration.

[0056] In the flight system 2 of [Fig. 3], the harness 4 comprises, independently of the secondary propulsion modules 14, knee pads 16 configured to be worn by the user 1. A plurality of tertiary modules 18 is connected to the knee pads, the plurality of tertiary propulsion modules 18 being distributed symmetrically at the knees of the user 1 and configured to exert a tertiary thrust force. Here, the plurality of tertiary modules 18 is pivotable via ball joints 12 between the knee pads and the plurality of tertiary modules 18, at least between the vertical flight configuration in which the tertiary thrust force is perpendicular to the frontal plane and the horizontal flight configuration in which the tertiary thrust force is parallel to the frontal plane.

[0057] Similarly to the primary thrust force, it should be noted that by "secondary thrust force" is meant a force resulting from a thrust force of each secondary propulsion module 14 taken individually. Thus, as long as this resultant is parallel to the frontal plane in vertical flight and perpendicular to the frontal plane in the horizontal flight configuration, the thrust force of a secondary propulsion module 14 taken alone may have a different orientation, compensated by the orientation of the other secondary modules 14. An identical principle can be applied to the tertiary thrust force and to the tertiary modules 18.

[0058] The remainder of the description focuses on describing flight configurations of a user equipped with the flight system 2 according to the embodiments described previously, in particular the embodiment of [Fig.l]. [Fig.4] corresponds to a vertical flight configuration of the flight system described according to the first embodiment and [Fig.5] corresponds to the vertical flight configuration of the flight system described according to the first embodiment. For the sake of readability, only the user 1, the harness 4, the ball joints 12 and the primary modules 6 are shown. It is understood that the flight system 2 according to the embodiments of [Fig.2] and [Fig.3] allow in particular the movements described below.

[0059] [Fig. 6] illustrates the flight system 2 in a takeoff configuration, in which the plurality of primary modules 6 is pivotable so that the thrust force of each of the primary modules 6 is perpendicular to the sagittal plane, oriented away from the body of the user 1. In such a configuration, the user 1 on the ground can adjust the primary thrust force without the latter being oriented towards the ground, and switch from the takeoff configuration to one of the confi flight figures when the thrust is sufficient for user 1 to rise completely without risk. Here, the user is shown standing on his feet at takeoff, but can alternatively be on his torso at takeoff, the primary modules 6 pivoting identically in both cases.

[0060] [Fig.7] and [Fig.8] illustrate a user equipped with the flight system in a forward configuration according to two variants. The variant of [Fig.8] differs from [Fig.7] only in that in [Fig.8], the frontal plane of the body of the user 1 is parallel to the ground. The plurality of primary propulsion modules is pivotable in a forward configuration in which the primary thrust force forms a first forward angle relative to the ground. Such an angle induces that the primary thrust force comprises a vertical component and a horizontal component. The vertical component of the thrust force allows the vertical movement of the user, in other words this component opposes the weight of the user 1 and allows the user to be kept in the air or to rise. The horizontal component allows the forward movement of the user 1.

[0061] To enhance the movement possibilities, the primary modules 6 on a first side of the sagittal plane can pivot synchronously and the primary modules 6 can pivot synchronously, the pivoting of the modules on the first side and the modules on the second side being independent. In other words, the primary modules 6 on the first side of the sagittal plane and the second side of the sagittal plane can form different angles relative to the body of the user 1. The value of the thrust force exerted by the primary modules 6 on the first side of the sagittal plane can also be different from the value of the thrust force of the primary modules 6 on the second side of the sagittal plane, making it possible to further enhance the movement possibilities.

[0062] The user 1 can for example turn on itself by performing a rotation along the transverse axis Y, as illustrated in [Fig. 9], by pivoting the primary modules along this same transverse axis Y. A rotation along the vertical axis Z is also possible, by pivoting the primary modules 6 along the vertical axis Z. The user 1 can also for example move horizontally in the frontal plane, here by pivoting only the primary modules on a given side of the sagittal plane around the longitudinal axis X, as illustrated in [Fig. 10]. In the horizontal flight configuration, the primary modules 6 on both sides of the sagittal plane can pivot around the longitudinal axis X to improve horizontal movement.

[0063] As a reminder, the movements described and illustrated in [Fig.4], [Fig.5], [Fig.6], [Fig.7], [Fig.8], [Fig.9] and [Fig. 10] are compatible with a flight system 2 according to the embodiment of [Fig.2] and [Fig.3]. The pivoting of the modules secondary 14 and tertiary modules 18 is then adapted for carrying out said movements described.

[0064] The flight system advantageously comprises a control device (not shown). The control device is configured to allow the user to control his movements made from the flight system, as well as the transitions from one configuration to another configuration. To determine in particular the angle of advancement of the thrust force relative to the ground, the control device may comprise a plurality of sensors configured to detect an instruction formed by the hands of the user, each instruction corresponding to a given hand sign. For example, a closed fist with the palm facing down may correspond to an instruction to advance. The user may thus command a horizontal movement, a vertical movement or a combination of these two movements as described above.Alternatively or in addition, instructions may be given by a movement of the user's head, allowing for more instructions. To determine in particular the configuration of the user's body relative to the ground, the control unit may comprise a plurality of sensors configured to detect an instruction formed by a movement of the user's torso. For example, a backward movement of the shoulders may correspond to a pivoting instruction so that the user's body moves from the horizontal flight configuration to the vertical flight configuration. Finally, to determine in particular the value of the thrust force of the propulsion modules, the control unit may comprise a remote control allowing the user to select from a set of predetermined force values. Each predetermined value may for example correspond to an intuitive "level" for the user.The remote control may, for example, take the form of a denture worn by the user in his or her mouth, with the user operating a level by squeezing the denture with his or her jaw. Alternatively, the remote control may, for example, take the form of a handle equipped with a joystick and / or buttons and / or triggers, or a touchscreen mounted on one of the user's arms.

[0065] It will also be noted that the invention is not limited to the embodiments described above. It will indeed appear to those skilled in the art that various modifications can be made to the embodiment described above, in light of the teaching which has just been disclosed to them.

[0066] In the detailed presentation of the invention which is made above, the terms used must not be interpreted as limiting the invention to the embodiment set forth in the present description, but must be interpreted to include all equivalents whose prediction is within the reach of a person skilled in the art by applying his general knowledge to the implementation of the teaching which comes to be disclosed to him.

Claims

Claims

1. Flight system (2) comprising: • a harness (4) configured to be worn by a user (1), said harness (4) at least partially covering the bust and surrounding the hips of the user (1); • a plurality of primary propulsion modules (6) connected to the harness (4), the plurality of primary modules (6) being distributed symmetrically at the hips of the user (1) on either side of a sagittal plane of the body of the user (1), the primary modules (6) being configured to exert a primary thrust force so as to raise or maintain the user (1) in the air; • at least one energy reservoir (10) configured to supply energy to the plurality of primary propulsion modules (6);the flight system (2) being characterized in that the plurality of primary propulsion modules (6) is pivotable, by means of ball joints (12) between the harness (4) and the plurality of primary propulsion modules (6), at least between a vertical flight configuration in which a frontal plane of the user's body (1) extends perpendicular to the ground and a horizontal flight configuration in which the frontal plane of the user's body (1) extends parallel to the ground.;

2. The flight system (2) of claim 1, wherein the primary thrust force is parallel to the frontal plane in the vertical flight configuration and the primary thrust force is perpendicular to the frontal plane in the horizontal flight configuration.

3. A flight system (2) according to any preceding claim, wherein the plurality of primary modules (6) is pivotable into a takeoff configuration in which the thrust force of each of the primary modules (6) is perpendicular to the sagittal plane and oriented away from the user (1) such that the primary thrust force is zero.

4. Flight system (2) according to any one of the preceding claims, comprising a plurality of secondary propulsion modules (14) connected to the harness (4), the plurality of propulsion modules secondary (14) being distributed symmetrically, above the shoulders of the user (1) and configured to exert a secondary pushing force.

5. A flight system (2) according to any preceding claim, wherein the harness (4) comprises knee pads (16) configured to be worn by the user (1) and a plurality of tertiary propulsion modules (18) connected to the knee pads (16), the plurality of tertiary propulsion modules (18) being distributed symmetrically at the knees of the user (1) and configured to exert a tertiary thrust force.

6. Flight system (2) according to any one of the preceding claims, in which the energy reservoir (10) is integral with the harness (4) at the level of the bust of the user (1).

7. Flight system (2) according to claim 6, wherein the tank (10) comprises a first compartment configured to supply the propulsion modules on a first side of the sagittal plane and a second compartment configured to supply the propulsion modules on a second side of the sagittal plane.

8. Flight system (2) according to any one of the preceding claims, comprising a dorsal propulsion module (20) connected to the harness (4) at the level of the bust of the user (1) and configured to exert a dorsal thrust force.

9. Flight system (2) according to any one of the preceding claims, in which the primary propulsion modules (6) on the same given side of the sagittal plane are integral with at least one adjacent primary module, a single primary propulsion module being in ball joint connection (12) with the harness (4).

10. A flight system (2) according to any preceding claim, wherein the plurality of primary propulsion modules (6) are pivotable into a forward configuration in which the primary thrust force forms a first forward angle relative to the ground.

11. Flight system (2) according to any one of the preceding claims, wherein the primary modules (6) on a first side of the sagittal plane pivot synchronously and the primary modules (6) on a second side of the sagittal plane pivot synchronously, the pivoting of the modules on the first side and the modules on the second side being independent.

12. Flight system (2) according to any one of the preceding claims, in which the primary propulsion modules (6) of the same given side of the sagittal plane are distributed symmetrically with respect to the frontal plane of the user's body (1).

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