Vehicle comprising a linear motor launch system powered by a supercapacitor energy storage device

Abstract

A land vehicle (12) for launching a drone (14) with a span greater than 2 metres equipped with one or more turbojets or turboprops (16) is provided with a system for catapulting (26) the drone (14), comprising a launch ramp (28) and a moving element (44) for supporting the drone (14). The moving element (44) is guided by the launch ramp (28) in a launch direction (100) over a length greater than 6 metres, and preferably greater than 8 metres. The catapulting system (26) comprises at least one linear motor (46) comprising an inductor (48) arranged along the linear path and an armature (50) arranged on the moving element (44) and at least one electrical energy storage device having one or more supercapacitors (58) for supplying power to the linear motor (46).

Description

DESCRIPTION TITLE: Vehicle comprising a linear motor launch system powered by a supercapacitor energy accumulator TECHNICAL FIELD OF THE INVENTION

[0001] The invention relates to the launching of a drone with jet engines or propellers with a wingspan greater than or equal to two meters, from a moving or stationary vehicle. STATE OF THE PRIOR ART

[0002] Solutions are known for launching drones from stationary or moving ground vehicles. The drones concerned are generally small in size and low in mass, as illustrated for example in document US7665691, which proposes the launching of a light drone from a moving vehicle with or without catapulting, or document CN106394924, which describes a ground vehicle equipped with a drone catapulting system, having a launch ramp, a carriage movable on this ramp, the carriage carrying the drone, and a linear motor having stator windings arranged on the carriage and permanent magnets arranged along the ramp, to launch the carriage in a very gradual manner.To power the windings, which move along the launch ramp with the carriage, by a power supply device arranged on the vehicle, it is necessary to provide electric rails along the launch ramp and brushes or current collectors at the carriage carrying the drone. Document CN112173153 discloses a land vehicle for the burst launch of small drones and provided with the same catapult system as document CN106394924, powered by an electrical energy accumulator with one or more supercapacitors for the power supply of the linear motor. This device is however not suitable for launching heavy drones. These devices are neither designed nor suitable for launching heavy drones.

[0003] To propose means of launching a large-wing and / or high-mass drone from the ground, with the aim of accomplishing a mission, in particular reconnaissance or dropping a load, the load being able in particular include rescue equipment, food, ammunition, transmission means, weapons or a device, quickly and at a distance from the launch zone, document W02020254512A1 has proposed an assembly comprising a motor launch vehicle and a drone, the motor launch vehicle being able to roll on a launch track to exceed a given speed threshold relative to a surrounding air mass, the motor launch vehicle being provided with a launch ramp cooperating with the drone to, in a launch position, guide the drone in translation from a starting position in a launch direction towards the front of the motor launch vehicle, the drone comprising one or more reactors and not comprising landing gear. The launch ramp may be equipped with an energy accumulator capable of impulsively releasing previously accumulated energy to catapult the drone.The energy accumulator can be sized to allow takeoff, in combination with the maximum thrust of the jet engines and the speed of the vehicle. It can also be sized to allow takeoff in combination with the maximum thrust of the jet engines with the vehicle stationary. This energy accumulator comprises one or more pneumatic energy accumulators, consisting of pressurized gas tanks, in particular compressed air, whose expansion in the open air or in a variable volume chamber of a pneumatic cylinder generates mechanical work to catapult the drone. This type of energy accumulator nevertheless has its limits in terms of power, in particular due to the resulting size.

[0004] Larger drones are usually catapulted from the ground. They are most often deployed using pneumatic catapult systems operating on launch rails fixed to the ground and of considerable length. Setting up these launch systems is extremely time-consuming, requires extensive logistics and a considerable number of operators. The launch system installed and fixed to the ground cannot be quickly moved to another launch zone. This requires complete dismantling of the installations, which goes against the mobility and speed of intervention criteria sought by defense or civil security units. Furthermore, these systems cannot be quickly repositioned against the wind when the weather changes on the ground. STATEMENT OF THE INVENTION

[0005] The invention aims to overcome the drawbacks of the state of the art and to propose means for launching a large-scale and / or mass drone raised from the ground, with the aim of carrying out in particular a reconnaissance mission or dropping a load, the load being able to include rescue equipment, food, munitions, transmission or optronic means, weapons and explosives, tactical neutralization systems, mini-drones or robots whatever their use, on land as well as at sea, quickly and at a distance from the launch zone.

[0006] To do this, according to a first aspect of the invention, a land vehicle for launching a drone according to claim 1 is proposed.

[0007] The use of one or more supercapacitors makes it possible to store electrical energy with a high power density and an energy density adapted to the application, and thus to meet the constraints of catapulting from a vehicle. The accumulated electrical energy is returned with a very low time constant, which allows a high acceleration of the drone over the entire catapulting phase, which, in practice, is of the order of half a second.

[0008] By favoring a permanent magnet synchronous motor, with a stator inductor made up of windings or electromagnets supplied with alternating current and an armature made up of permanent magnets, we have an unpowered armature, which avoids having to provide a current collector between the launch ramp and the moving assembly.

[0009] According to one embodiment, the electrical energy accumulator with one or more supercapacitors has an electrical capacity greater than 10 F, preferably greater than 15 F, and a nominal voltage greater than 500V, and preferably greater than 600 V, and preferably greater than 700V, and preferably greater than 750V.

[0010] Such a dimensioning makes it possible to store electrical energy greater than 1 MJ. In practice, only a fraction of this stored energy, about 1 / 3, is restored during the catapulting phase, and high values ​​of electrical capacity, greater than 15 F, and nominal voltage, greater than 700 V, are preferred. Nominal voltage here means the maximum voltage that the energy accumulator with one or more supercapacitors can permanently withstand.

[0011] Power electronics are required to supply the linear motor with alternating current and to control the inductor. According to various embodiments: the linear motor is connected to the electrical energy accumulator with one or more supercapacitors by an inverter; and / or the inductor is controlled by a power switch circuit.

[0012] It is naturally necessary to charge the energy accumulator, and charging equipment is preferably provided on board the vehicle. For this purpose, the catapulting system preferably comprises a circuit for charging the electrical energy accumulator with one or more supercapacitors, comprising one or more primary sources of electrical energy.According to various methods, which may be combined where appropriate: the primary source(s) of electrical energy comprise(s) at least one primary source of direct current electrical energy, for example a direct current generator set, a battery or a fuel cell; and / or the primary source(s) of electrical energy comprise(s) at least one primary source of alternating current electrical energy, for example an alternating current generator set, connected to the supercapacitor electrical energy accumulator by a rectifier; and / or the primary source(s) of electrical energy are capable of delivering a power greater than 5KW; and / or. the electrical power supply circuit of the supercapacitor electrical energy accumulator is connected to photovoltaic panels carried by the vehicle; and / or The catapulting system comprises a regenerative braking system for the moving assembly electrically connected to the supercapacitor electrical energy accumulator, capable of transforming the kinetic energy of the moving assembly into electrical energy transmitted to the supercapacitor electrical energy accumulator.

[0013] In practice, it is expected that at the end of an acceleration phase of the mobile assembly carrying the drone on a first portion of the launch ramp, the drone separates from the mobile assembly which must still be braked to stop at the latest at the end of the launch ramp. However, the mass of the mobile assembly is high due to the presence of the armature. According to one embodiment, it is therefore expected that the catapult system comprises at least one, and preferably at least two, devices for braking the mobile assembly from among the following devices: an electromagnetic braking device, preferably eddy current braking, arranged in a front end portion of the launch ramp; a spring-based kinetic energy accumulator device; a shock energy absorption device using elastomer pads; a fluidic reversible energy absorption device; a friction braking device.

[0014] According to one embodiment, the launch ramp in the launch position has a front end portion which projects beyond a front end of the vehicle body, and the vehicle is equipped with a removable balancing front running gear, movable between a storage position and an operational position, the removable balancing front running gear in the operational position having wheels located less than 50 cm from the ground, at a distance in front of the front end of the body, for example more than 1 meter in front of the front end of the body, preferably under the front end portion of the launch ramp. This front running gear The balancing system is primarily intended to prevent the vehicle from tipping forward when the mobile unit brakes after the drone has taken off, or when the mobile unit reaches the front end of the launch pad. The balancing nose gear can be equipped with active suspension.

[0015] Similarly, it may be provided that the launch ramp in the launch position has a rear end portion which protrudes from a rear end of the vehicle body, and that the vehicle is equipped with a removable rear balancing running gear, movable between a storage position and an operational position, the removable rear balancing running gear in the operational position having wheels located less than 50 cm from the ground, behind a rear end of the vehicle body, preferably under the rear end portion of the launch ramp. This rear running gear allows balancing of the vehicle during the acceleration phase of the drone and the mobile crew, before takeoff. The rear balancing gear may be equipped with an active suspension.

[0016] The vehicle is preferably capable of moving by rolling with the drone's catapulting system in the launch position. According to one embodiment, this makes it possible in particular to envisage a launch mode in which the vehicle is moving in a straight line facing the wind, at a speed exceeding a given speed threshold relative to the wind at the time of catapulting the drone. When the terrain is suitable, launching from the moving vehicle contributes to limiting the energy that must be consumed by the drone in the takeoff phase. The relative speed obtained by the moving vehicle is added to the propulsion speed of the launcher and makes it easier to obtain the lift speed of the drone at the exit of the ramp. This is all the more necessary when the length of the ramp is reduced and the mass of the drone is high.

[0017] But the ability to move into launch position is also useful in the event that the launch is always carried out while stationary: it then allows the launch ramp to be positioned or repositioned in an ideal launch position, facing the wind, just a few moments before launch.

[0018] The vehicle is preferably motorized. It may, if necessary, include a motorized vehicle towing a trailer or semi-trailer. It is preferably a wheeled vehicle, preferably with a double rear axle, for good absorption of the forces generated during the launch of the drone. The vehicle is preferably an all-terrain motor vehicle, the ramp being positioned, for example, on the roof of the vehicle or on a platform provided for this purpose. An all-terrain vehicle allows, if necessary, a launch from rough terrain or an unprepared runway, for example from a beach in the case of a sea rescue. Preferably, an active suspension incorporating a trim correction is arranged between a chassis and wheel sets of the vehicle, or between the launch ramp and the chassis of the motor vehicle or between the mobile assembly and the launch ramp, to help stabilize the drone.

[0019] According to one embodiment, the vehicle comprises at least two, and preferably at least three, removable stabilizers between a retracted position and an operational position resting on the ground. Such stabilizers make it possible, if necessary, to correct the attitude of the vehicle when stationary before launching. They can also define a polygon of support for the vehicle on the ground larger than that defined by the wheels of the vehicle. They can be actuated hydraulically, pneumatically or electrically.

[0020] In practice, it is desirable for the vehicle to have dimensions that do not impair its maneuverability. It is therefore preferably provided that the launch ramp can be retracted or folded into a transport position. The transition to the transport position can be achieved by a telescopic movement. However, and preferably, it is provided that the launch ramp comprises several articulated sections, at least some of which are movable between the launch position, in which the sections are aligned, and a transport position, in which the sections are side by side. The sections that are adjacent in the launch position are linked two by two by articulations, which preferably have a single pivot axis and only one. In the event that the launch ramp comprises more than two sections, the pivot axes between adjacent sections are preferably parallel to each other. In the transport position, the pivot axes are preferably located in a vertical plane. According to a preferred embodiment, the articulation axis(es) are vertical in the transport position. This minimizes the force required to deploy the launch ramp from the transport position to the launch position.

[0021] The articulated sections of the launch ramp preferably allow for a linear trajectory to be formed for the mobile crew with a length of at least six meters, and preferably at least eight meters, and at most fourteen meters. However, to allow the launch of heavier drones, or in unfavorable conditions where the length of the articulated ramp is not sufficient, it may be possible, where appropriate, to envisage additional sections of launch ramp, possibly transported on a trailer of the vehicle or independently, being added to the articulated sections to lengthen the launch ramp, which may then exceed 14 meters in length. Of course, such a ramp can only be used when the vehicle is stationary, and with ground supports.

[0022] Preferably, the vehicle offers in a modular manner several of the launch modes previously envisaged: a launch mode with the vehicle in motion, and / or a launch mode with the vehicle stationary, but capable of moving into the launch position, and / or a launch mode with the vehicle stationary, balanced by stabilizers, and / or a launch mode with a ramp extended by additional sections requiring independent support on the ground.

[0023] Such modularity is particularly interesting for the user, and allows him to adapt the vehicle to the launch conditions encountered on the ground.

[0024] In the event that the drone is jet-powered, it is advantageous to provide, in order to protect the inductor placed along the launch pad, that the crew mobile is provided with a thermal deflector to protect a portion of the launch ramp located behind the mobile crew with reference to the launch direction. The deflector is shaped to deflect a jet of air expelled by the drone's reactor(s), in order to avoid damaging the rail integrating the electromagnetic systems and the braking systems and more broadly the vehicle and its occupants. In the event that the vehicle is intended to launch jet drones and turboprop drones, the deflector may be removable.

[0025] According to one embodiment, the mobile assembly comprises a trolley rolling on the launch pad. It is also possible to provide for the mobile assembly and the launch pad to be equipped with an electromagnetic lift circuit for the mobile assembly relative to the launch pad.

[0026] According to another aspect of the invention, it relates to an assembly comprising a vehicle as described above and a drone with a wingspan greater than two meters equipped with one or more turbojets or turboprops, supported by the mobile crew.

[0027] According to one embodiment, the assembly further comprises at least one locking mechanism, movable between a locking position for fixing the drone relative to the mobile assembly in an armed position, and an unlocking position allowing movement of the drone relative to the mobile assembly. In particular, it can be provided that the attachment device is provided with a trigger, preferably mechanical, electromechanical or pyrotechnic, preferably controlled to trigger when the drone reaches a given position on the launch pad, corresponding to the end of the linear motor.

[0028] The drone's piloting during the take-off phase can be carried out from the vehicle, in a pre-programmed manner with dedicated avionics equipment or independently by a remote operator.

[0029] Preferably, the release of the load involves turning the drone onto its back, then, by gravity, releasing the load from a cavity of the drone flying on the back, then, preferably, deployment of a parachute to slow down the load in free fall.

[0030] According to another aspect of the invention, possibly combinable with the previous aspect of the invention, the latter relates to a ground launch vehicle capable of launching a drone with a wingspan greater than two meters equipped with one or more reactors, the ground launch vehicle being provided with a catapult system comprising a launch ramp and a mobile assembly guided by the launch ramp along a linear trajectory of the launch ramp, the mobile assembly being capable of supporting the drone oriented in a launch direction, characterized in that the mobile assembly is provided with a thermal deflector for protecting a portion of the launch ramp located behind the carriage with reference to the launch direction of the drone.Such a deflector is particularly useful when the catapulting system incorporates a linear motor, which the thermal deflector then protects from the flow of hot air coming from the reactor(s).

[0031] According to another aspect of the invention, which can be taken in combination with the preceding aspects of the invention, the invention relates to a ground launch vehicle for launching a drone with a wingspan greater than 2 meters equipped with one or more reactors, the ground launch vehicle comprising a body and being provided with a catapult system comprising a launch ramp which, in a launch position, has a front end portion which protrudes from a front end of the vehicle body, characterized in that the vehicle is equipped with a removable balancing running gear, movable between a storage position and a launch position, the balancing running gear in the launch position being on the ground, at a distance in front of the front end of the body, preferably under the front end portion of the launch ramp. BRIEF DESCRIPTION OF THE FIGURES

[0032] Other characteristics and advantages of the invention will emerge from reading the description which follows, with reference to the appended figures, which illustrate: [fig. 1] figure 1, an isometric view taken from the right rear three-quarters of an assembly according to a first embodiment of the invention, comprising a motor vehicle equipped with an electromagnetic catapult system and a drone, in a transport position; [fig. 2] figure 2, a side view of the assembly according to figure 1, in transport position; [fig. 3] figure 3, a top view of the assembly of figure 1, illustrating the deployment of a catapult system in the drone launch position; [fig. 4] figure 4, a profile view of the assembly according to figure 1, in a launching position, before launching the drone; [fig. 5] figure 5, a profile view of the assembly according to figure 1, in a launch, during launch of the drone; [fig. 6] figure 6, a side view of a variant of the assembly according to figure 1, in a launching position; [fig. 7] Figure 7, an electrical diagram of the catapulting system of the assembly according to Figure 1. DETAILED DESCRIPTION OF EMBODIMENTS

[0033] In Figures 1 and 2, an assembly 10 is illustrated, in a transport position, comprising a land vehicle 12 and a drone 14 equipped here with two turbojets 16, supported by the vehicle 12.

[0034] The illustrated drone 14 is only one example of a class of drones intended to be transported and launched using the vehicle 12, and which is constituted by drones with one or more turbojets or turboprops having a fuselage 18 and a wing 20 which, in flight, has a large wingspan, in particular greater than 2 meters or 2.5 meters, or even greater than 3 meters, where appropriate with variable geometry, for example with foldable wings, so that the width of the wing for transport is narrower than for launch and flight. The drone 14 has a relatively high takeoff weight, for example greater than 350 kg. The drone 14 is preferably without landing gear, which allows a reduction in the empty weight and volume of the drone and a significant reduction in drag, and also contributes to an increase in payload and range. In addition, this absence of landing gear allows for mechanical simplification which limits the risk of failure.

[0035] The vehicle 12 illustrated here is an all-terrain motor vehicle on wheels, with a front wheel set 22 and, preferably, a double rear axle 24 to increase the payload and, as will be seen later, to take up the forces when launching the drone 14 from the vehicle 12.

[0036] The vehicle 12 is equipped with a catapulting system 26 for the drone 14, comprising a launch ramp 28 placed on a platform, illustrated in the transport position in FIGS. 1 and 2, being deployed in FIG. 3, and in a launch position in FIGS. 4 and 5. The launch ramp 28 comprises several sections, articulated two by two, in this case a central section 28A, a rear section 28B articulated at a rear end of the central section 28A and a front section 28C articulated at a front end of the central section 28C. In the transport position, the sections 28A, 28B, 28C are positioned side by side on a support plate 30. By unfolding the rear 28B and front 28C sections, as illustrated in FIG. 3, the launch ramp is brought into the launch position illustrated in FIG. 4.The pivot axes 32AB, 32AC of the articulations between the central section 28A and the rear section 28B on the one hand and between the central section 28A and the front section 28C on the other hand, are parallel to each other and, preferably, vertical in the transport position and during deployment, to limit the deployment forces. The deployment may, if necessary, include a final phase of pivoting the platform 30 and the unfolded ramp around a transverse horizontal pivot axis 34, using a crane 35, so that the ramp 28 in the launching position is more inclined than its sections 28A, 28B, 28C in the transport position, which are preferably horizontal.

[0037] In the launching position illustrated in Figure 4, the launching ramp 28 has a front end portion that projects beyond a front end of the vehicle body, and the vehicle is preferably equipped with a running gear removable balancing front axle 36, movable between a storage position at the rear of the vehicle (figure 1) and an operational position (figure 4), the balancing front axle 36 in the operational position having wheels located less than 50 cm from the ground, at a distance in front of the front end of the vehicle body, for example more than 1 meter in front of the front end of the body, preferably under the front end portion of the launch ramp 28. A front support arm 38 connects a front portion of the launch ramp 28 to a front end of the vehicle body 12, at a point located longitudinally between the front wheel set 22 of the vehicle 12 and the removable balancing front axle 36.

[0038] Similarly, the launch ramp 28 in the launch position has a rear end portion that projects beyond a rear end of the vehicle body 12, and the vehicle 12 is preferably equipped with a removable rear balancing undercarriage 40, movable with the rear section 28B of the launch ramp 28 between a storage position (in FIG. 1) and an operational position (in FIG. 4), the removable rear balancing undercarriage 40 in the operational position having wheels located less than 50 cm from the ground, behind a rear end of the vehicle body 12, preferably under the rear end portion of the launch ramp 28.

[0039] The deployment of the sections 28B, 28C of the launch ramp illustrated in Figure 3 is done while stationary, but, remarkably, the vehicle 12 is able to move while rolling with the catapulting system 26 of the drone 14 in the launch position of Figure 4.

[0040] If necessary, it is possible to further lengthen the launch ramp 28 with additional sections which are interposed between the central section 28A and one and / or the other of the front 28C and rear 28B end sections. The additional sections can be transported in a trailer or an accompanying vehicle. The assembly operations for deploying the ramp are then greater, and the vehicle is no longer able to move with the extended launch ramp deployed.

[0041] Alternatively, it is possible, according to the embodiment illustrated in Figure 6, to retain the three-section structure 28A, 28B, 28C, by enlarging each of the sections. In this case, instead of the removable balancing trains 36, 40, removable feet 136, 140 are provided, resting on the ground. Removable stabilizers 142 are also provided, which rest on the ground to fix the vehicle 12 in the position of Figure 6.

[0042] The launch ramp 28 defines a launch direction located in a median vertical longitudinal plane of the vehicle and a linear trajectory with a length greater than 6 meters, and preferably greater than 8 meters in the launch position of FIG. 5, and possibly exceeding 14 meters in the launch position of FIG. 6, for a mobile crew 44 supporting the drone 12.

[0043] This mobile assembly 44 is here constituted by a carriage rolling in slides of the launch ramp 28, but it is envisaged as an alternative to equip the mobile assembly 44 and the launch ramp with an electromagnetic lift circuit of the mobile assembly 44 relative to the launch ramp 28. The mobile assembly 44 is provided with a thermal deflector 45 for protecting a portion of the launch ramp located behind the mobile assembly 44 with reference to the launch direction.

[0044] The catapulting system 26 enabling the drone 12 to be launched comprises a linear motor 46 comprising an inductor 48 arranged along the linear trajectory and an armature 50 arranged on the moving assembly 26, as shown diagrammatically in FIG. 7. The linear motor 46 is preferably a synchronous motor whose armature 50 is composed of permanent magnets or electromagnets and the inductor 48 comprises electromagnets or windings. More precisely, the inductor 48 of the linear motor 46 extends from the rear end of the launch ramp 28 forward over only a portion of the launch ramp, called the acceleration portion. A portion of the launch ramp 28, called the braking portion, located at the front end of the launch ramp is reserved for braking the moving assembly after launching the drone.

[0045] The linear motor 46 is powered by a power supply circuit illustrated in FIG. 7 and preferably housed in a compartment 47 of the vehicle 12. The inductor 48 of the linear motor 46 is connected to a direct current bus 52 via an inverter 54 and a control power switch circuit 56. Remarkably, this direct current bus 52 is electrically powered by an electrical energy accumulator with one or more supercapacitors 58. The electrical energy accumulator with one or more supercapacitors 58 has an electrical capacity greater than 10 F, preferably greater than 15 F, and a nominal voltage greater than 500 V, and preferably greater than 600 V, and preferably greater than 700 V, and preferably greater than 750 V.The direct current bus 52 can advantageously be connected to a low-pass filter 60 to limit transient overvoltages and to a discharge circuit 62 to allow, if necessary, discharge of the supercapacitors.

[0046] The linear motor power supply circuit further comprises a circuit for charging the electrical energy accumulator 58 to one or more supercapacitors, comprising one or more primary sources of electrical energy 64, 66 capable of delivering a power preferably greater than 5 kW, which may include in particular: a primary source of direct current electrical energy, for example a direct current generator set, a battery or a fuel cell; and / or a primary source of alternating current electrical energy, for example an alternating current generator set;

[0047] These primary sources of electrical energy are preferably carried by the vehicle and may, if necessary, be supplemented by: a photovoltaic generator 67 carried by the vehicle and / or a regenerative braking system of the mobile assembly 72, 74 electrically connected to the charging circuit, capable of transforming the energy kinetics of the moving assembly 44 in electrical energy transmitted to the charging circuit.

[0048] The primary electrical energy source(s) 64, 66 are preferably connected to the direct current bus 52 and to the supercapacitor electrical energy accumulator 58 by an adapter circuit 68, which may include, for example, a rectifier or a direct voltage booster.

[0049] The braking portion of the launch ramp, located at the front end of the launch ramp, is equipped with at least one, and preferably at least two, braking devices 70 for the moving assembly from among the following devices: an electromagnetic braking device 72, preferably eddy current braking; a shock energy absorption device using elastomer pads 74; a reversible fluid energy absorption device; a friction braking device.

[0050] If necessary, the electromagnetic braking device 72 can be connected to the direct current bus by an energy converter 74 including a rectifier, to constitute a regenerative braking circuit. Naturally, the examples shown in the figures and discussed above are given only for illustrative and non-limiting purposes. It is explicitly provided that the different embodiments illustrated can be combined with each other to propose others.

[0051] To take off the drone 14 from the launch position of Figure 4, the turbojets or turboprops are powered and brought to a maximum thrust regime, while keeping the drone 14 fixed to the moving assembly 44 by a first locking system and the moving assembly 44 fixed relative to the launch pad 28 by a second locking system. The supercapacitor energy accumulator 58 being charged, a sudden discharge is commanded in the inductor 48, via the inverter 54 and the power switch circuit 56. The linear motor is preferably controlled so as to produce on the armature 50 and the moving assembly 44 a constant force throughout the launch and takeoff phase, over a length which may be of the order of 6 meters for an 8 meter launch ramp, or 8 meters for a 10 meter launch ramp. The lock between the mobile assembly 44 and the launch ramp 28 is released, and the mobile assembly undergoes an acceleration proportional to the resulting electromagnetic force on the armature 50 and to the thrust of the turbojets 16 or turboprops. The lock between the mobile assembly 44 and the drone 14 is released as soon as a speed of the drone 16 relative to the surrounding air mass is reached which is sufficient to ensure the lift of the drone 16, which separates from the mobile assembly 14 at the latest when the mobile assembly enters the front end portion of the ramp 28 which comprises the braking device(s) of the mobile assembly 44.Finally, and as illustrated in Figure 5, the moving assembly 44, whose mass is nevertheless significant since it includes the mass of the armature 50, is slowed down and stopped by the various braking devices, and in particular by the electromagnetic brake 72 and the shock absorber 74. This entire take-off procedure of the drone 14 can take place when the land vehicle 12 is stopped, or, preferably, while the land vehicle 12 is traveling in a straight line at regulated speed, which makes it possible to reach the desired relative speed of the drone 14 more quickly with respect to the air mass.

[0052] From the launch position of Figure 6, the take-off procedure is similar, but naturally with the vehicle 12 stationary.

[0053] Various modifications are envisaged. The linear motor 46 may be an asynchronous machine. The launch ramp deployment mechanism may be telescopic. The vehicle 12 may be a trailer or semi-trailer, or an articulated vehicle consisting of a tractor and a trailer or semi-trailer. It may also be a tracked vehicle.

Claims

CLAIMS 1 . Land vehicle (12) for launching a drone (14) equipped with one or more turbojets or turboprops (16), the land vehicle (12) being provided with a system (26) for catapulting the drone (14), comprising a launch ramp (28) and a mobile assembly (44) for supporting the drone (14), the mobile assembly (44) being, in a launch position of the catapult system (26), guided by the launch ramp (28) in a launch direction (100) along a linear trajectory of the launch ramp (28), the catapult system (26) comprising at least one permanent magnet synchronous linear motor (46) comprising an inductor (48) consisting of windings or electromagnets supplied with alternating current, and an armature (50) consisting of permanent magnets, and at least one electrical energy accumulator with one or more supercapacitors (58) for the power supply of the linear motor (46).characterized in that the launch ramp (28) has a length greater than 8 meters, the inductor being stator, the windings or electromagnets of the inductor being arranged along the linear trajectory and the permanent magnets of the armature being arranged on the mobile assembly (44), the land vehicle (12) being capable of launching a drone (14) having a take-off mass greater than 350 kg and a wingspan greater than two meters.

2. Vehicle (12) according to claim 1, characterized in that the electrical energy accumulator with one or more supercapacitors (58) has an electrical capacity greater than 10 F, preferably greater than 15 F, and a nominal voltage greater than 500V, and preferably greater than 600 V, and preferably greater than 700V, and preferably greater than 750V.

3. Vehicle (12) according to any one of the preceding claims, characterized in that: the linear motor (46) is connected to the electrical energy accumulator with one or more supercapacitors (58) by an inverter (54); and / or the inductor (48) is controlled by a power switch circuit (56).

4. Vehicle (12) according to any one of the preceding claims, characterized in that the catapulting system (26) comprises a circuit for charging the electrical energy accumulator with one or more supercapacitors (48), comprising one or more primary sources of electrical energy (64, 66, 67).

5. Vehicle (12) according to claim 4, characterized in that: the primary source(s) of electrical energy (64, 66, 67) comprise at least one primary source of direct current electrical energy, for example a direct current generator set, a battery or a fuel cell; and / or the primary source(s) of electrical energy (64, 66, 67) comprise at least one primary source of alternating current electrical energy, for example an alternating current generator set, connected to the supercapacitor electrical energy accumulator (58) by a rectifier; and / or the primary source(s) of electrical energy (64, 66, 67) are capable of delivering a power greater than 5KW; and / or the electrical power supply circuit of the supercapacitor electrical energy accumulator (58) is connected to photovoltaic panels (67) carried by the vehicle; and / or The catapulting system (26) comprises a regenerative braking system (72) for the moving assembly electrically connected to the supercapacitor electrical energy accumulator (58), capable of transforming the kinetic energy of the moving assembly (44) into electrical energy transmitted to the supercapacitor electrical energy accumulator (58). Vehicle (12) according to any one of the preceding claims, characterized in that the catapulting system (26) comprises at least one, and preferably at least two, devices for braking the moving assembly from among the following devices: an electromagnetic braking device (72), preferably eddy current braking, arranged in a front end portion of the launch ramp (28); a spring-based kinetic energy accumulator device; a shock energy absorption device using elastomer pads (74); a fluidic reversible energy absorption device; a friction braking device.Vehicle (12) according to any one of the preceding claims, characterized in that the launch ramp (28) in the launch position has a front end portion which projects beyond a front end of the body of the vehicle (12), and the vehicle is equipped with a removable balancing front running gear (36), movable between a storage position and an operational position, the removable balancing front running gear (36) in the operational position having wheels located less than 50 cm from the ground, at a distance in front of the front end of the body, for example more than 1 meter in front of the front end of the body, preferably under the front end portion of the launch ramp (28).Vehicle (12) according to any one of the preceding claims, characterized in that the launch ramp (28) in the launch position has a rear end portion which projects beyond a rear end of the vehicle body, and the vehicle is equipped with a removable rear balancing running gear (40), movable between a storage position and an operational position, the removable rear balancing running gear (40) in the operational position having wheels located less than 50 cm from the ground, behind a rear end of the vehicle body, preferably under the rear end portion of the launch ramp (28). Vehicle (12) according to any one of the preceding claims, characterized in that the vehicle (12) is capable of moving by rolling with the catapulting system (26) of the drone (12) in the launching position. Vehicle (12) according to any one of the preceding claims, characterized in that the vehicle comprises at least two, and preferably at least three removable stabilizers (142) between a retracted position and an operational position resting on the ground. Vehicle (12) according to any one of the preceding claims, characterized in that the launch ramp (28) comprises several articulated sections (28A, 28B, 28C), at least some of which are movable between the launching position, in which the sections (28A, 28B, 28C) are aligned, and a transport position, in which the sections (28A, 28B, 28C) are side by side.Vehicle (12) according to any one of the preceding claims, characterized in that the mobile assembly (44) is provided with a thermal deflector (45) for protecting a portion of the launch ramp (28) located behind the mobile assembly (44) with reference to the launch direction (100). Vehicle (12) according to any one of the preceding claims, characterized in that: the mobile assembly (44) comprises a trolley rolling on the launch ramp, and / or the mobile assembly (44) and the launch ramp are equipped with a circuit for electromagnetic support of the mobile assembly relative to the launch ramp. Assembly (10) comprising a vehicle (12) according to any one of the preceding claims, and a drone (14) with a wingspan greater than 2 meters, having a takeoff mass greater than 350 kg, and equipped with one or more turbojets (16) or turboprops, supported by the mobile assembly (44).

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