FR2998550A1 - Aircraft e.g. commercial aircraft, system for transport of passengers and/or freight, has equipment whose portion includes ground equipments being part of ground assistance device to partially provide functionalities required on ground - Google Patents

Abstract

The system has first equipment on-board of aircraft (2f) for application of specific functionalities to flight of the aircraft, and second equipment adapted to provide mixed functionalities e.g. flight and ground functionalities, to the aircraft. A portion of the second equipment provides the mixed functionalities to the aircraft, and includes equipments on-board of the aircraft to provide the mixed functionalities required in flight. The portion has ground equipments being part of a ground assistance device (3) to partially provide the mixed functionalities required on the ground.

Description

The present invention relates to aircraft, in particular commercial aircraft carrying passengers and / or freight. When the aircraft are on the ground, a number of functions must be able to be implemented. For example, it must be possible to: condition the temperature and, where appropriate, the air humidity inside the cabin in the presence of temperatures and humidity levels in the cabin. outside air that can vary widely from one geographical point to another; ventilate the trolley storage areas ("galleys"), ventilate and cool the avionics, cool IFE equipment, on-board power supplies, ventilate certain areas under pressure or not, provide air extraction, etc. ; transfer digital data between the aircraft and the ground; inert the fuel tanks; ventilate the areas adjacent to the tanks before starting the engines of the aircraft; fill the freshwater tanks and empty the wastewater tanks; provide security around the aircraft, for example with video means; air drying on board during ground operations to reduce the build-up of water and / or ice in insulating liners resulting in extra weight. The above list of functions that must be able to be implemented on the ground on board an aircraft is not limiting.

Moreover, a certain number of these functions, such as, for example, air conditioning, must also be able to be implemented when the aircraft is in flight. For this purpose, aircraft according to the state of the art comprise equipment sized to allow the implementation of certain mixed functions that must be completed both in flight and on the ground. These aircraft according to the state of the art may also include an auxiliary energy generator (APU) using a specific turbojet engine adapted to provide the aircraft with the energy required for the implementation of the functions required on the ground. It is known to assist the ground with the aircraft with assistance vehicles but they are intended to ensure the rolling of the aircraft (engines off) and especially during its recoil ('push back'). The invention aims to provide an aircraft system that optimizes an aircraft for the functions or operations required in flight. For this purpose, the subject of the invention is an aircraft system comprising an aircraft itself and at least one device distinct from said aircraft for ground assistance of said aircraft, said system comprising first equipment on board said aircraft for implementation of features specific to the flight of said aircraft, and second equipment adapted to provide said aircraft with mixed functionalities, namely functionality required in flight and on the ground, the system being remarkable in that at least a part of said second equipment adapted to provide said aircraft with mixed functionality includes second onboard equipment on board said aircraft to provide at least those of said mixed functionalities that are required in flight, and second ground equipment, forming part of said assistance device, for providing at least in part those of said mixed features that are required On the ground, and in that according to the invention, the aircraft and the assistance device are complementary and form a system by which the weight of the aircraft can be reduced and the latter optimized for flight. Indeed, at least some of the equipment onboard the aircraft can be dimensioned, with regard to the mixed functions, for their sole implementation in flight or, if necessary, for their implementation of a part in flight. and secondly on the ground together with complementary equipment of the assistance device. Therefore at least a portion of the second ground-based implementation equipment of mixed functionalities is deported from the aircraft in the assistance device. The equipment of the ground assistance device is not subject to the same constraints of regulation, maintenance, weight, safety, congestion, etc. than if they were on board an aircraft. They can be robust and less expensive. The cost of the aircraft system-assistance device is therefore reduced compared to that of an aircraft according to the state of the art.

According to a possible characteristic of the invention, said second ground equipment comprises a temperature-controlled air supply equipment to an air conditioning unit on board said aircraft. According to another possible feature of the invention, said second ground equipment comprises an air supply equipment temperature-controlled to an air conditioning circuit of said aircraft. According to another possible characteristic of the invention, said second ground equipment comprises an air supply equipment set in hygrometry to an air conditioning circuit of said aircraft. According to another possible characteristic of the invention, said second equipment on board said aircraft comprises at least one circuit for a heat transfer fluid for cooling consumers, said circuit comprising at least one exchanger, and said second ground equipment comprises at least one a thermal source for adjusting the temperature of said heat transfer fluid via said exchanger.

According to another possible feature of the invention, said second equipment on board said aircraft comprises at least one circuit of a coolant coolant consumer in said aircraft and said second ground equipment comprises a cooling unit of said coolant said circuit .

According to another possible characteristic of the invention, said second equipment on board said aircraft comprises at least one pneumatic energy distribution circuit on board said aircraft and said second ground equipment comprises at least one air supply device regulated at the same time. less pressure / flow to said pneumatic power distribution circuit on board said aircraft. According to another possible characteristic of the invention, said second equipment on board said aircraft comprises at least a first electrical power supply source of at least one electrical network and in that said second ground equipment comprises at least one second supply source of said network with electrical energy. According to another possible characteristic of the invention, said second equipment on board said aircraft comprises at least a first hydraulic power generation and regulation equipment and at least one circuit for distributing said energy to on-board consumers and said second equipment on the ground comprise at least a second hydraulic power generation and regulation equipment for the hydraulic power supply of said distribution circuit. According to another possible characteristic of the invention, said second equipment on board said aircraft comprises at least one circuit for circulating an onboard consumer ventilation gas and said second ground equipment comprises at least one supply generator of said circuit with said gas. According to another possible characteristic of the invention, said second equipment on board said aircraft comprises at least one first servo-control device and said second ground-based equipment comprise at least one second servo-control device adapted to receive servo-control data of said servo-control device. first servo device. Different models of ground assistance devices can thus be provided according to: - the ground environment: assistance device models can be designed specifically for very cold, very hot and dry environments, very hot and wet, etc. ; the nature of the operations conducted on the ground: some models of assistance devices can for example be adapted to ensure maintenance phases of the aircraft; environmental rules in place at the location where the assistive device is used; different levels of automation of the movements according to the ground traffic, movements during the towing of the aircraft, the interface with the aircraft. According to another possible characteristic of the invention the system comprises third equipment intended to provide specific functionalities of ground operation of said aircraft, at least a part of said third equipment forming part of said ground assistance device. Therefore at least a portion of the third equipment specific to the implementation of ground operations can be deported from the aircraft in the assistance device, which allows a weight saving on the aircraft. According to another possible characteristic of the invention, said third equipment comprises at least one fuel tank on board said aircraft and, in said assistance device, at least one fuel pumping device in / out of said tank. According to another possible characteristic of the invention, said third equipment comprises at least one data management and storage server on board said aircraft and, in said assistance device, at least one secure interface for communicating data with said server. .

According to another possible characteristic of the invention, said third equipment comprises at least one clean water tank and at least one wastewater tank on board said aircraft and, in said assistance device, equipment for filling said tank. clean water and draining said wastewater tank.

According to another possible characteristic of the invention, said third equipment comprises at least one pressurized oxygen tank on board said aircraft and, in said assistance device, at least one equipment for filling said oxygen tank. According to another possible characteristic of the invention, said ground assistance device comprises at least one vehicle. With the aircraft system according to the invention, the aircraft can be devoid of auxiliary power source (APU), which is used on the ground. The energy required by the aircraft on the ground may be provided in part or in full by the assistance device. It can therefore be a low emission energy source and noise, which can be made in accordance with strict local environmental regulations without this having an impact on the design of the aircraft. Other features and advantages of the invention will emerge from the following description of the embodiments given solely by way of example and illustrated by the accompanying drawings in which: FIG. 1 is a block diagram which illustrates the functionalities of FIG. an aircraft and assistance vehicle system according to the invention in comparison with a standard aircraft of the state of the art; FIG. 2 is a block diagram illustrating a first embodiment of a mixed air conditioning and distribution management equipment using the system according to the invention; Figure 3 is a block diagram illustrating a second embodiment of a mixed equipment for managing the conditioning and distribution of air by means of the system according to the invention; FIG. 4 is a block diagram illustrating a hybrid equipment for managing humidity by means of the system according to the invention; FIG. 5 is a block diagram illustrating a first embodiment of a mixed cooling device for consumers by heat transfer fluid by means of the system according to the invention; FIG. 6 is a block diagram which illustrates a second embodiment of a mixed cooling equipment for consumers by heat transfer fluid by means of the system according to the invention; FIG. 7 is a block diagram illustrating a mixed equipment for managing the pneumatic energy by means of the system according to the invention; FIG. 8 is a block diagram illustrating a mixed electrical energy management equipment by means of the system according to the invention; FIG. 9 is a block diagram illustrating a mixed equipment for managing the hydraulic energy by means of the system according to the invention; FIG. 10 is a block diagram illustrating a mixed equipment for managing the ventilation of non-pressurized zones of the aircraft with or without inert gases by means of the system according to the invention; Figure 11 is a block diagram illustrating ground fuel management equipment by means of the system according to the invention; FIG. 12 is a block diagram illustrating ground equipment for data transport management by means of the system according to the invention; FIG. 13 is a block diagram illustrating ground equipment for water management using the system according to the invention; FIG. 14 is a block diagram illustrating ground equipment for managing the oxygen reserves by means of the system according to the invention; FIG. 15 is a block diagram illustrating ground equipment for managing taxiing by means of the system according to the invention; FIG. 16 is a block diagram illustrating ground equipment for monitoring the movements of persons and loads in the environment of the aircraft by means of the system according to the invention; FIG. 17 is a block diagram illustrating ground surveillance equipment for monitoring the physical environment of the aircraft by means of the system according to the invention; and Fig. 18 is a block diagram illustrating different types of ground support vehicles for the system according to the invention. Referring to FIG. 1, an aircraft system 1 comprises an aircraft 2 itself, for example an airplane, and a ground assistance device 3, for example a vehicle, which makes it possible to optimize the aircraft 2 For the flight. In the following, the term aircraft or aircraft will be used indifferently, but it should be understood that the invention applies to any type of aircraft that requires the implementation of in-flight functions and ground functions. In FIGS. 1 to 18 these functions or functionalities are identified by blocks, but it should be understood that these blocks designate both these functions or functionalities and the equipment that implements them. By comparison with a standard aircraft 4, the aircraft or optimized aircraft 2 has the same conventional features specific to flight (control of engines, movable wing elements, etc.), hereinafter called flight functions. On the other hand, the mixed functions 11, hereinafter called mixed functions, which are implemented both in flight and on the ground by a standard aircraft 4 are distributed in the system 1: a part 11 has mixed functions is put into operation. operates in the aircraft 2 and a part 11v of the mixed functions is implemented in the device or assistance vehicle 3.

This offset of part of the mixed functions of the aircraft 2 to the assistance device 3 results in a reduction in dimensions, and / or weight, and / or energy consumption, etc. embedded equipment that implements the mixed functions in the aircraft 2.

A standard aircraft 4 also includes a number of equipment for implementing features not used in flight and specific ground, hereinafter called ground functions. As represented in FIG. 1, a part 12v of ground functions and equipment is deported in the assistance vehicle 3, another part 12a of these functions and ground equipment remaining implemented in the aircraft 2. Part of the functions and equipment ground equipment, braking for example, can not be deported out of the plane 2. This partial shift of the functions and ground equipment results in a deletion or a reduction of the sizing (size, weight, energy consumption, etc.) of the equipment embedded in the aircraft 2. The offset of part of the functions and mixed equipment and ground functions and equipment in the assistance device 3 results in a lightening of the aircraft 2. This lightening allows , at merchant loads 13, 13a equal, to reduce the operating load 14a (fuel) compared with that 14 of a standard aircraft 4. As illustrated by the block 15 of Figure 1, the weight gains as well Réalis s have the potential to improve the traffic load, and / or the radius of action, etc. of the plane 2.

In system 1, aircraft 2 is optimized for flight. It is a platform, carrying more or less functions and equipment with more or less advanced performance, coupled with a ground support vehicle 3 providing the appropriate complement of performance during ground operations. Referring to Figure 2, a first embodiment of a mixed ground management equipment for air conditioning and distribution of air in an aircraft using the system 1 according to the invention will be described. The aircraft 2 (hereinafter referred to as 2f in its flight configuration and 2g in its ground configuration) has an air conditioning unit 20a which is driven by electrical networks 20b and, where appropriate, pneumatic networks 20c. The regulation of the group 20a may, depending on the type of aircraft air conditioning system, be provided entirely electrically by the electrical networks 20b, essentially pneumatically by the pneumatic networks 20c except for the provision of temperature or other parameters by the electrical networks 20b, or hybrid, namely provided by both the electrical networks 20b and the pneumatic networks 20c. In the following description of the example illustrated in Figure 2, for the sake of clarity the air conditioning unit 20a will be described as being connected to both electrical networks 20b and pneumatic networks 20c. However, it should be understood that the invention is not limited to the case of essentially pneumatic or hybrid control, but also aims a fully electric control, that is to say without pneumatic networks 20c. The aircraft 2f comprises one or more energy sources 21 for supplying the electrical networks 20b and the pneumatic networks 20c with electrical energy and pneumatic energy. These energy sources 21 are sized to allow the group 20a to adjust the air temperature in flight, but not on the ground as in a standard aircraft. They are therefore less heavy and cumbersome than in a standard aircraft, for the benefit of their integration into the aircraft (volumes, cost, ...). The assistance vehicle 3 comprises an electrical power supply equipment 23b and a pneumatic power supply equipment 23c for supplying the ground respectively the existing electrical networks 20b and 20c of the airplane 2g, as well as a device servocontrol 24 which receives from the aircraft 2g servo feedback information to modify the demand flow / pressure mainly. Indeed, the flow rate and the pressure, or even the temperature, are preferably regulated at the level of the ground vehicle according to the tire demands and the external environment. The generation of electrical energy is preferably also regulated at ground vehicle 3. The power supply equipment 23b and the pneumatic power supply equipment 23c are sized according to local needs, it is that is, different types of vehicles may be provided depending on the local temperature conditions. When the aircraft 2f is in flight, the air in the cabin thereof is temperature controlled in a conventional manner by the air conditioning unit 20a 20b whose electrical networks and 20c are powered by the (the) on-board power source (s) 21. When the airplane 2g is on the ground and connected to the assistance vehicle 3, the air in the cabin of the latter is always regulated in temperature by the air conditioning unit 20a. , but the devices 22b and 22c of the assistance device respectively provide electrical energy and the pneumatic energy necessary for supplying the air conditioning unit 20a. The air conditioning performance of the aircraft during the ground / flight and flight / ground transition phases is ensured by the inertia of the exchanges between the aircraft and the external environment. The onboard source or sources 21 for supplying pneumatic and electrical energy are therefore dimensioned according to the only conditions likely to be encountered in flight. These energy supply sources are less stressed than those of standard aircraft during ground operations, or being in less extreme operating modes and a less polluted outdoor environment, their reliability is improved and / or their dimensioning can take into account the impact of this lesser solicitation. Part of these embedded power supply sources 21 can even be omitted, the APU for example.

FIG. 3 illustrates a second embodiment of a mixed equipment for ground management of the conditioning and distribution of air in an aircraft by means of the system 1 according to the invention. The aircraft 2f comprises the air conditioning unit 20a, a temperature controlled air distribution device 25a, a device 25b for mixing the temperature-controlled air with the air coming from the cabin of the aircraft, 25c air distribution equipment in the cabin and a device for recirculating air from the cabin to the device 25b of mixing. For its part, the assistance vehicle 3 comprises an air temperature regulation equipment 22, one or more power supply equipment 23 of the aircraft 2g and a servo-control device 24 which receives from the group 20a temperature information. On the ground, air regulated by the air conditioning unit 22 of the ground assistance vehicle 3 is supplied directly in the aircraft 2g to the air distribution device 25a of the air circulation circuit. 25a, 25b, 25c and 25d. In this example of FIG. 3, not only the on-board source (s) 21 for feeding pneumatic and electrical energy, but also the on-board air conditioning equipment in the aircraft 2g are sized according to the only conditions likely to to be encountered in flight. As a result, the group 20a which conditions the air temperature in the aircraft is not used on the ground, which increases its reliability and / or improve its dimensioning. FIG. 4 describes a mixed equipment for ground management of the hygrometry of the air distributed in an airplane by means of the system 1 according to the invention. This is similar to the management of the air temperature described with reference to FIG. 3. In flight, the hygrometry is regulated, like the air temperature, by the air conditioning unit 20. the plane 2f.

The assistance vehicle 3 comprises an equipment 26 for the supply of air controlled hygrometry to the air circulation circuit 25a, 25b, 25c and 25d of the aircraft, a power source 23 for supplying the aircraft 2g electrical energy, and a servo device 24 can be coupled to the servo means of the group 20 to receive information on the degree of hygrometry of the air inside the aircraft 2g. During the ground operation, the equipment 26 present on the ground assistance vehicle 3 makes it possible to extract a portion of the moisture accumulated in the pressurized areas of the aircraft to limit the impacts associated with the accumulation of fuel. condensation water, namely excess condensation causing dripping and saturation of the insulation material which causes an overweight of the aircraft and a loss of thermal performance, or even a degradation of performance or damage by the excess of weight, etc. The equipment of the assistance vehicle 3 with the humidity adjustment equipment 26 makes it possible to reduce the dimensioning of the equipment on board the aircraft to fulfill this function, or even to avoid their presence in the aircraft. This humidity control function 26 may be complementary to the air conditioning and / or air distribution functions described with reference to FIGS. 2 and 3, but also humidification functions and equipment (not shown) which are embedded to increase the comfort of the passengers but which increase the risks of accumulation of condensation. A first embodiment of a mixed ground cooling device for consumers by heat transfer fluid in an aircraft using the system according to the invention will now be described with reference to FIG. 5. The aircraft 2f is equipped with a group cooling 27 of one or more heat transfer fluids and a circulation pump 28 to cool one or more consumers 29a, 29b, 29c.

The assistance vehicle 3 has one (or more) cold heat source, but which can also be tempered or hot as needed. The heat source 30 makes it possible to regulate the temperature of a fluid, for example air, intended to circulate in an exchanger 31 of the airplane 2g when the latter is on the ground.

In operation, the airplane 2g being on the ground, the refrigerant coolant consumers 29a, 29b, 29c is cooled (or heated) in the exchanger 31 by the fluid temperature controlled by the thermal source 30 of the assistance vehicle 3. The regulation of the temperature of the heat transfer fluid is ensured in the ground plane 2g by its cooling unit 27.

The ground vehicle 3 is sized according to local needs, that is to say that the ground assistance vehicles 3 may differ according to the geographical areas. During the transition phases ground / flight, flight / ground, the required thermal performance is ensured by the inertia of exchanges. The on-board cooling unit 27 being dimensioned for flights, it is lighter and cumbersome and potentially less expensive than in a standard aircraft. Its integration into the aircraft in terms of volume, energy consumption, etc. is improved. On the other hand, this group being less stressed during ground operations or in less extreme operating conditions and in a less polluted environment, the reliability of this group is greatly improved and / or it can be dimensioned accordingly. A second embodiment of a mixed ground cooling device for consumers by heat transfer fluid in an aircraft using the system according to the invention will now be described with reference to FIG. 6. This second embodiment differs from that of FIG. Figure 5 in that the assistance vehicle 3 comprises a cooling unit 32 may be connected directly to the consumer cooling loop 33 29a, 29b, 29C when the aircraft 2g is on the ground.

The aircraft 2g, once connected to the assistance vehicle 3 on the ground, uses a source or several sources of pre-conditioned fluids to the needs of consumers which is equipped with the cooling unit 32. The advantages of the embodiment of the figure 6 are similar to those of the previously described embodiments. In addition, the ground assistance vehicle 3 may include equipment for analyzing, cleaning, upgrading the heat transfer fluid (s) to detect and / or prevent any anomalies. A mixed equipment for ground management of the pneumatic energy in an airplane by means of the system according to the invention will be described with reference to FIG. 7. The airplane 2f is equipped for the flight of a main or auxiliary group of power 34 for distributing, via a distribution device 35, air regulated at pressure / flow rate, and possibly at a temperature, to consumers 36 such as the air conditioning unit, zone ventilation fans, parking spaces, in pressure of hydraulic tarpaulins, engine starting and de-icing of the wing. Similarly, the assistance vehicle 3 is itself equipped with a pressure / flow regulated air distribution unit 37, and possibly with temperature, which can be coupled directly to the dispensing device 35 of the 2g plane when the one is on the ground. Under these conditions, the group 34 of the aircraft is not used on the ground. The advantages of the embodiment of FIG. 7 are similar to those of the previously described embodiments. Air distribution equipment regulated pressure / flow, and possibly temperature, embedded in the aircraft are dimensioned for the flight, even removed for example with regard to the pneumatic supply by the auxiliary power unit. A combined equipment for ground management of the electrical energy of an aircraft using the system according to the invention will be described with reference to FIG. 8. The aforementioned energy source 21 on board the aircraft 2f comprises one or a plurality of electrical current generators 38, one or more current regulators 39, one or more aircraft electrical networks 40, and electrical consumers 41. On its side, the assistance vehicle 3 comprises one or more electric current generators 42 and a or several current regulators 43. The ground assistance vehicle 3 is dimensioned to local needs (several types of vehicles are therefore possible). When the plane 2g on the ground is connected to the assistance vehicle 3, the current generator (s) 42 and current regulator (s) 43 are connected directly to the (x) airline network (s) 40 to supply the consumer (s) 41.

The advantages of the embodiment of FIG. 8 are similar to those of the previously described embodiments. In particular, the equipment 38 and 39 for generating and regulating the electric current are no longer solicited on the ground, their reliability is greatly improved and / or these equipment can be resized accordingly, which results in weight gains. , cost and bulk. The electrical equipment 42 and 43 of the ground assistance vehicle 3 can be adapted to power on starting high power systems (deicing / anti-icing wing, nacelle or other surface), the relay being provided in the next phase of maintenance by the onboard electrical equipment, once the aircraft disconnected from the ground support vehicle 3, thus limiting the sizing of these onboard equipment. A mixed equipment for ground management of the hydraulic power of an aircraft using the system according to the invention will be described with reference to FIG. 9.

The aircraft 2f comprises one or more hydraulic power generators 44, one or more controllers 45 of flow / pressure and temperature of hydraulic fluid, one (or more) loop (s) 46 of circulation of hydraulic fluid, and consumers 47a , 47b, 47c of hydraulic energy .. For its part, the assistance vehicle 3 comprises one or more 30 hydraulic energy generators 48a and one or more pressure regulators / flow 48b. The ground assistance vehicle 3 is sized to local needs (several types of vehicles are possible). When the ground plane 2g is connected to the assistance vehicle 3, the hydraulic energy generator (s) 48a and the pressure / flow regulator (s) 48b are connected directly to the ) loop (s) 46 to supply the consumer (s) 4Ta, 47b, 47c of the airplane 2g. The advantages of the embodiment of FIG. 9 are similar to those of the previously described embodiments. In particular, the equipment 44 and 45 for generating and regulating the hydraulic energy are no longer solicited on the ground, their reliability is greatly improved and / or these equipment can be resized accordingly, which results in gains weight, cost and bulk. The vehicle on the ground 3 may include additional functions of the type analysis, cleaning, complement level to detect and / or prevent any hydraulic anomalies. A mixed equipment for ground management of the ventilation of non-pressurized areas of the aircraft, with or without inert gases, by means of the system according to the invention will be described with reference to FIG.

The airplane 2f comprises one or more generators in pressure / air flow 49 of air or an inert gas, one or more regulators 50 of flow / pressure and possibly concentration of the gas, a loop 51 of circulation of the gas, and consumers 52a, 52b, 52c ventilated by the gas. For its part, the assistance vehicle 3 comprises one or more generators in pressure / air flow 53 or an inert gas and one or more regulators 54 of pressure / flow and possibly concentration of the gas. The ground assistance vehicle 3 is sized to local needs (several types of vehicles are possible). When the aircraft 2g on the ground is connected to the assistance vehicle 3, the generator (s) in pressure / flow rate 53 of air or of an inert gas and the regulator (s) 54 of pressure / flow and possibly concentration of the gas are connected directly to the loop 51 to supply the consumers 52a, 52b, 52c of the aircraft 2g. This embodiment of FIG. 10 makes it possible to take advantage of the vehicle 3 as soon as it is connected to ventilate the appropriate areas of the aircraft with or without inert gases, so as to no longer have to do so by onboard systems, at least during these phases of soil. It can be the fuel tanks of the aircraft (fuel vapor) but also the so-called areas adjacent to these tanks which must be ventilated and that one can thus supply inert gases before the power is turned on. plane, or even during the maintenance phases. It is indeed only at this power up of the aircraft that ventilation is provided by the aircraft itself. The same arrangement can be applied for other types of fuel (hydrogen, etc.).

The operation of embedded systems is saved and they can be resized accordingly. The reliability but also the longevity of the consumables can be increased: in fact, the inert gases are generally obtained from chemical reactions (catalyst type) via membranes located in cylinders which, at the passage of a fluid (air in general, more or less hot with a flow and a volume more or less high), generate the inert gas with the flow and the desired concentration. These cylinders must be regularly replaced to be regenerated. The proportions of inert gases in the tanks can be increased to better cover the risk of flammability of the vapors. An advantage of the embodiment of FIG. 10 is also to avoid loading forced ventilation equipment covering the ground operation phases, or even to reduce the level of protection of certain components that would no longer be subject to the same risk. . The duration of ventilation of the aircraft tanks in order to access them and to allow dedicated maintenance tasks can also be reduced.

Ground handling equipment of the fuel (s) of the aircraft by means of the system according to the invention will be described with reference to FIG. 11. The airplane 2f comprises one or more fuel tanks 55, a or more devices 56 for regulating the flow and / or the pressure of the fuel in the fuel network (es) 57 of the aircraft, and consumers 58 to which the fuel is conveyed. The assistance vehicle 3 comprises pumping equipment 59 that can be connected to ground fuel tanks (not shown) on the one hand, and to the aircraft tanks 55 on the other hand and to the (x) control device (s) 56.

Once the aircraft 2g connected to the assistance vehicle 3, it can be used for filling functions of the fuel tank (s) (fuel oil, bio fuel, hydrogen, other, ..) in order to win time on these operations from the taxi phases, but also to offset the volumes consumed during certain phases on the ground (starting, engine cooling, acceleration, deceleration, etc. ....). The vehicle 3 also makes it possible to empty the tanks 55 if necessary by using the same interface during the maintenance phases. This makes it possible to limit the number of vehicles in direct contact with the aircraft 2g and therefore to limit the risk of damage to the aircraft, and to facilitate certain geometrical definitions of the aircraft (location of passenger and cargo doors, hatches, air evacuation outlets, wing position and landing gear, etc.). The assistance vehicle 3, according to its configuration, may or may not include equipment (not shown) for purification / treatment of fuel or fuels and associated distribution networks (antifungal treatment and purging water in fuel oil for example) , for reheating or cooling according to the geographical situation (for a better use of the thermal inertia of the aircraft tanks in flight as a heat sink), which has the effect of reducing the maintenance and refueling tasks related to this (s) fuel (s).

Ground handling equipment for data transfers between the aircraft and the ground using the system according to the invention will be described with reference to FIG. 12. The aircraft 2f, 2g comprises management and storage servers 60 data carrier, data channel 62, and clients 63a, 63b and 63c receiving and / or transmitting data on the channels 62. The ground assistance vehicle 3 comprises secure communication interfaces 64 between the aircraft 2g and various installations and users on the ground 65 via external communication networks 66. When the aircraft is on the ground, its servers 60 may be connected to the interfaces 64 of the vehicle 3 by any means. suitable physical or radio link (not shown) at high speed. Preferably, in order to simplify the manner in which the communications are managed by the aircraft 2g when it is on the ground, the ground vehicle 3 is adapted to handle all the protocol, security, etc. problems, and to provide an interface and a 30 unique and simplified channel to the aircraft. During the ground phases where the aircraft 2g is physically connected to the assistance vehicle 3, massive data exchanges can take place between the aircraft 2g and the interface 64 (if it has its own data storage capacities ) or the installations and users on the ground 65 via the interface 64. These data exchanges concern for example: the state of the aircraft: breakdowns, levels of wear, aging, configuration, etc., the setting up-to-date software and embedded documentation, - the parameters of the following flight: weather, navigation, cartography, etc., - passengers: number, names, allocated seats, preferences, services, meals etc., - data ' hobbies: movies, games, videos, digital press etc.

The secure interfaces 64 being carried by the assistance vehicle 3, the computing power, the data transfer capacity, the security and the storage capacity of the management and data transfer servers 60 of the aircraft 2g, can therefore be limited. In addition, because of the high-speed data transfer capacity on the ground between the aircraft 2g and the assistance vehicle 3, the communications during the flight can be limited to the essential. The volume of data exchanged in flight is limited and the management of their integrity and security facilitated. The cost of flight communications is lowered and the sizing of functions associated with these in-flight communications can be reduced.

A ground water management equipment in an aircraft using the system according to the invention will be described with reference to FIG. 13. The airplane 2f, 2g comprises clean water tanks 67, flow regulators pressure 68, clean water networks 69, consumers 70, sewage networks 71, and gray or sewage tanks 72. The assistance vehicle 3 comprises equipment 73 for filling the storage reservoirs. clean water 67 and equipment 72 for emptying gray water tanks 72. The operations of filling tanks 67 and emptying tanks 72 are preferably implemented when the aircraft 2g is connected to the assistance vehicle. 3 ("taxi in / taxi out") to limit the impact of these tasks on the time of immobilization on the ground of the aircraft ("turn around time"). The clean water fill can be adjusted according to the next flight data to optimize the amount of water to be loaded. Optionally, the assistance vehicle 3 comprises equipment (not shown) of: - purification / treatment of the water supplied to the tanks 67 and distribution networks 69; - Reheating or cooling water according to geographical situations, for example, to use the thermal inertia of the water tanks of the aircraft as a heat sink, or to limit the risk of icing in the network.

This management of the aircraft 2g by means of the assistance vehicle 3 makes it possible to reduce maintenance and refueling tasks related to water, but also to limit the number of vehicles in direct contact with the aircraft on the ground for avoid the risk of damage and facilitate certain geometrical aspects of the aircraft (passenger and cargo doors, hatches, air evacuation outlets, wing position and landing gear etc ...). The filling and purging of the tanks 67 being performed at each aircraft cycle, the maximum volume of these tanks can be adapted according to the typical missions of the aircraft. The assistance vehicle 3 can also intervene during the maintenance operations to purge all the clean water systems and possibly flush the wastewater systems of the aircraft. Equipment for ground management of the oxygen reserves in an aircraft using the system according to the invention will be described with reference to FIG. 14. The airplane 2f, 2g comprises one or more oxygen tanks 75, regulators flow rate / pressure 76, oxygen distribution networks 77, and oxygen consumers 78. The assistance vehicle 3 comprises an equipment 79 for filling the oxygen tanks 75 of the aircraft 2g via connection lines (not shown)

The assistance vehicle 3 makes it possible to provide the ground with the effective filling of the oxygen tanks 75 on board the aircraft 2g so as to limit the volume of the on-board tanks 75 if necessary and to simplify the operations while avoiding intervention. human verification of the oxygen volume available on board. Equipment for managing the taxiing of an aircraft using the system according to the invention will be described with reference to FIG. 15. The airplane 2f is equipped with a set of landing gear and steering systems. and braking device 80. The ground device 3 is a vehicle comprising devices 81 for coupling with landing gear and steering and braking systems (or undercarriages) 80 of the aircraft 2g, devices 82 for cooling the brakes of the aircraft 2g, and devices 83 digital and / or voice link with the cockpit 84 of the aircraft 2g. In order to support the aircraft and to relieve its landing gear, the ground vehicle comprises, in addition to the devices 81 for coupling with landing gear and steering and braking systems, contact interfaces between the assistance vehicle. 3 and the structure of the aircraft 2g shown in Figure 2 by the block "Structural contacts". The block "ground link" of Figure 2 corresponds to arrangements forming connection between the ground and the assistance vehicle 3, and between the aircraft 2g and the assistance vehicle 3, to relieve the stresses on the train of landing, or even replace the landing gear. In operation, the ground vehicle 3 is interfaced or coupled with the aircraft 2g to relieve all the rolling functions during ground operations. This makes it possible to reduce as much as possible the ground stresses of the aircraft 2g related to running and to consequently size the systems associated with the undercarriages (landing gear, braking, steering). Once the ground vehicle 3 coupled to one or more landing gear 80 of the airplane 2g, the cooling devices 82 cool the brakes (by blowing or contact) to reduce the potential impact of their heating on the time of call of the plane ("Turn Around Time") of the aircraft, but also to keep a larger operating margin for the next takeoff vis-à-vis the margins required in case of emergency braking, but especially to limit the brake wear due to ground operations, and therefore if necessary reconsider their dimensioning. Preferably, the cooling devices 82 comprise means for measuring the brake temperature of the aircraft 2g. For guidance, the functions of the ground vehicle 3 may be limited to the exit of the aircraft from the runway, the more complex operations (rotation, tight turn, ...) that can be covered by the ground vehicle 3 in interaction with the landing gear 80 to limit the physical constraints. A benefit provided by the ground vehicle 3 in the ground taxi assistance of the aircraft is to minimize the impact that the taxiing functions have on the sizing of the aircraft and thus to reduce weight , to facilitate the integration of bodies related to taxiing, and to reduce the costs both direct and maintenance of the aircraft. For example, in some cases the installation of dedicated ventilation systems on landing gear can be avoided. The taxiing assistance of the aircraft by the ground vehicle 3 can also have an impact on functions that are more or less necessary on the ground: see the ground from the cockpit, deicing functions, windscreen wipers, size of the bumpers catches and windows, with if necessary is a replacement of the direct vision from the cockpit by cameras on the ground vehicle to retransmit to screens in the cockpit. In addition, according to a particular embodiment, the ground assistance vehicle 3 is adapted to provide assistance with the acceleration and deceleration of the aircraft. FIG. 16 illustrates a ground assistance vehicle 3 comprising an equipment 85 for ground surveillance of movements of persons and loads in the environment 86 of the airplane 2g, in particular the inputs and outputs thereof. The monitoring equipment 85 may be of video, optical, infrared, radar, etc. type. The equipment may also include known face recognition means for people, means for remote reading of badges, boarding passes or RFID tags. The equipment 85 may comprise at strategic positions satellite devices of the ground assistance vehicle 3. Preferably, the ground assistance vehicle 3 is connected to external resources 87 such as safety platforms, logistics, maintenance, etc. In operation, the ground vehicle 3 makes it possible to continuously scan the area around the aircraft 2g to detect who enters and leaves the aircraft, and what enters and leaves the aircraft. The input-outputs and activities around the plane are typically those of: - people: passengers, crew, maintenance teams, cleaning, etc. ; - commercial charges: trolleys, containers and other cargo loads, but also spare parts, etc. The aircraft's input-output monitoring can be of interest from a safety point of view to control and memorize access to the aircraft, or to facilitate boarding and counting of passengers. From a logistical point of view, the surveillance equipment 85 makes it possible to monitor the loading and unloading of luggage, containers, trolleys. This avoids installing on board the aircraft these monitoring and / or control functions and all the associated functions, such as the management and the transfer of data related to these loads and unloads.

The surveillance equipment 85 makes it possible to prevent, by means of an alarm and alarm system, the intrusion of unauthorized persons during maintenance operations, but also when the aircraft is at the unattended parking lot, or closed, typically for VIP planes. FIG. 17 illustrates a ground assistance vehicle 3 comprising equipment 88 for monitoring the physical environment of the airplane at standstill and during taxiing in particular. Preferably, the ground assistance vehicle 3 is connected to external resources 89 such as information processing and alarm management platforms. The equipment 88 is adapted to fulfill one or more of the following functions: - to detect the presence of debris, - if necessary, to analyze the size of the debris (s) and the risk of impact with regard to the rolling paths of the wheels of the landing gear. the aircraft 2g, - initiate an alarm, - provide data or commands to avoid an impact, - generate alerts to trigger the cleaning of debris by another vehicle or by means on board the ground support vehicle.

The equipment 88 can also be adapted to scan the environment so as to establish / confirm mapping of the operation site, in particular when completing works that modify airport facilities (distance with buildings, width of the taxiways, etc. .) and transmit this data to a training center. The equipment 88 may also include sensors installed on the ground vehicle 3 to analyze the air quality, make sound measurements, etc. and transmit this data to a training center.

The different types of ground support vehicle 3 that can be used in the system 1 will now be described with reference to FIG. 18. The ground assistance vehicle 3 is considered as a platform that can be modular in the mixed functions that it implements, in its autonomy, in the energies that it uses, etc.

First of all, the assistance vehicle 3 can be modular in the mixed functions that it fulfills by replacing more or less completely the equipment on board the aircraft. Thus, for example, depending on the needs, the assistance vehicle 3 may comprise one or more of the equipment and mixed functionalities and ground that have been described above: there may be assistance vehicles ground optimized for hot weather or for hot and humid weather 3a, for cold weather 3b, for very short turn-around times 3c, for exclusive coverage of 3d maintenance phases, etc. All the ground and mixed functions are 'a la carte', mainly according to each stopover, and according to the needs. The synchronization of the aircraft / vehicle coupling will have to be carried out. The ground assistance vehicle 3 can also be modular in its autonomy: the vehicle can be completely autonomous 3rd, or partially autonomous 3f (in the "parking" phases for example) by being connected or interfaced with fixed infrastructures or mobile airport connections via the ground or surface to other vehicles. The ground assistance vehicle 3 may have different degrees of autonomy: it can be completely autonomous from the connection phase to the aircraft after landing to the parking zone, during the parking phase, and then to the disconnection area prior to flight; - it can be designed to move to its next 'coupling' with an aircraft or return to a car park to recharge, exchange and / or transfer data and / or, energy and / or liquids or gases with ground interfaces. This mode frees the crew of the aircraft from certain tasks during the ground phases and leaves this management to a centralized control body managing the various traffic, needs in time and availability and priorities: ground vehicles (by type), ground vehicles coupled with airplanes, ground traffic of ground vehicles, incoming aircraft traffic requiring a ground vehicle and initially releasing a ground vehicle; - It can also be less autonomous, with a pilot on board and more or less robotic connections and steering; it may, for example, be under the authority of the pilot of the aircraft in the phases of "taxi-in taxi out", call for manual connection of functions to the aircraft, etc. ; the connections of the assistance vehicle 3 with the aircraft 2 may be more or less direct with, for example, contactless exchanges of the induction type for electrical energy, without contact (`contact less') for the data, etc. The ground support vehicle can still be modular in the energies it uses (green energies) 3g and its impact on the environment (limitation of discharges, noise, etc.). The ground vehicle may consist of several 'satellites' or mini specialized vehicles that can connect to the aircraft in an optimized manner so as to limit the grouping of the mixed functions to a single point of contact with the aircraft.

Claims (17)

REVENDICATIONS1. Aircraft system comprising an aircraft proper (2) and at least one device (3) separate from said aircraft for ground assistance of said aircraft, said system comprising: first equipment (10) onboard said aircraft (2) for the implementation of features specific to the flight of said aircraft, and second devices (11) adapted to provide said aircraft (2) with mixed functionalities, namely functionalities required in flight and on the ground, characterized in that - at least a part of said second equipment adapted to provide said aircraft with mixed functionalities comprise: o second equipment (11a) onboard said aircraft (2) to provide at least those of said mixed functionalities which are required in flight, and o second equipment at ground (11b), forming part of said assistance device (3), for providing at least in part those of said mixed functionalities which are required are on the ground. 2. Aircraft system according to claim 1, characterized in that said second ground equipment (11b) comprises an equipment (22) for supplying electrical and / or pneumatic energy to an air conditioning unit (20). on board said aircraft (2). 3. Aircraft system according to claim 1, characterized in that said second ground equipment (11b) comprises an equipment (22) for supplying temperature-controlled air to a circuit (25a-25d) of air conditioning said aircraft (2). 4. Aircraft system according to any one of claims 1 to 3, characterized in that said second ground equipment (11b) comprises an equipment (26) for supplying air controlled hygrometry to a circuit (25a). 25d) for air conditioning said aircraft (2). 5. Aircraft system according to any one of claims 1 to 4, characterized in that said second equipment on board said aircraft (11a) comprises at least one circuit (28) of a heat transfer fluid for the cooling of consumers (29a). 29c), said circuit comprising at least one exchanger (31), and in that said second ground equipment (11b) comprises at least one thermal source (30) for adjusting the temperature of said heat transfer fluid via said exchanger (31). 6. Aircraft system according to any one of claims 1 to 4, characterized in that said second equipment on board said aircraft (11b) comprises at least one circuit (33) of a coolant coolant consumers (29a -29c) in said aircraft and in that said second ground equipment (11a) comprises a group (32) for cooling said heat transfer fluid of said circuit (33). 7. Aircraft system according to any one of claims 1 to 6, characterized in that said second equipment on board said aircraft (11a) comprises at least one circuit (35, 36) of pneumatic energy distribution on board said aircraft and in that said second ground equipment (11b) comprises at least one air supply device (37) regulated at least in pressure / flow to said circuit (35, 36) of pneumatic energy distribution on board said aircraft (2). 8. Aircraft system according to any one of claims 1 to 8, characterized in that said second equipment on board said aircraft (11a) comprises at least a first source (38, 39) of electrical power supply of at least one electrical network (40) and in that said second ground equipment (11b) comprises at least a second source (42, 43) supplying said network (44) with electrical energy. 9. Aircraft system according to any one of claims 1 to 8, characterized in that said second equipment on board said aircraft (11a) comprises at least a first hydraulic power generation and regulation equipment (44) and at least one circuit (46) for distributing said energy to onboard consumers (47a-47c) and in that said second ground equipment (11b) comprises at least one second hydraulic power generation and regulation equipment for supplying hydraulic power to said distribution circuit (46). 10. Aircraft system according to any one of claims 1 to 9, characterized in that said second equipment on board said aircraft (11a) comprises at least one circuit (51) for circulating an onboard consumer ventilation gas ( 52a-52c) and in that said second ground equipment (11b) comprises at least one generator (53, 54) supplying said circuit (51) with said gas. 11. Aircraft system according to any one of claims 1 to 10, characterized in that said second equipment on board said aircraft (11a) comprises at least a first servo device (20, 25a, 25b) and said second ground equipment (11b) comprises at least a second servo device (24) adapted to receive servo data from said first servo device (20, 25a, 25b). 12. Aircraft system according to any one of claims 1 to 11, characterized in that it comprises third equipment (12) intended to provide specific ground operation functions of said aircraft, at least a portion (12v ) said third equipment forming part of said ground assist device (3). 13. Aircraft system according to claim 12, characterized in that said third equipment (12v) comprises at least one fuel tank (55) on board said aircraft (2) and, in said assistance device (3), at least one fuel pumping device (59) in / out of said tank (55). 14. Aircraft system according to any one of claims 12 and 13, characterized in that said third equipment (12v) comprises at least one server (60) for managing and storing data on board said aircraft (2) and in said assistance device (3), at least one secure interface (64) for communicating data with said server (60). 15. Aircraft system according to any one of claims 12 to 14, characterized in that said third equipment (12v) comprises at least one clean water tank (67) and at least one wastewater tank (72). ) on board said aircraft (2) and, in said assistance device (3), equipment (73,74) for filling said clean water tank (67) and for emptying said wastewater tank (72) . 16. Aircraft system according to any one of claims 12 to 15, characterized in that said third equipment (12v) comprises at least one pressure oxygen tank (75) on board said aircraft (2) and, in said assistance device (3), at least one equipment (79) for filling said oxygen tank (75). 17. Aircraft system according to any one of claims 1 to 16, characterized in that said ground assist device (3) comprises at least one vehicle.