SYSTEM FOR GROUND POWER SUPPLY

Abstract

A system for ground power supply of aircraft includes at least one mobile transformer unit having a first vehicle chassis and a voltage transformer mounted on the first vehicle chassis; at least two energy stores which can be alternately connected to an input of the voltage transformer in order to supply the voltage transformer with electric energy; and a supply cable for ground power supply of one of the aircraft. The supply cable is configured to be connected to an output of the voltage transformer. Each of the at least two energy stores is part of one of at least two mobile storage units each including a second vehicle chassis. The first vehicle chassis of the transformer unit and each of the second vehicle chassis of the at least two mobile storage units are moveable on the ground independently on each other.

Claims

1. A system for ground power supply of aircraft, the system comprising at least one mobile transformer unit having a first vehicle chassis and a voltage transformer mounted on the first vehicle chassis, the voltage transformer having an input and an output, at least two energy stores which are configured to be alternately connected to the input of the voltage transformer in order to supply the voltage transformer with electric energy, and a supply cable for ground power supply of one of the aircraft, the supply cable being configured to be connected to the output of the voltage transformer, wherein each of the at least two energy stores is part of one of at least two mobile storage units each including a second vehicle chassis, and wherein the first vehicle chassis of the transformer unit and each of the second vehicle chassis of the at least two mobile storage units are are configured to be moved on the ground independently on each other.

2. The system of claim 1, wherein each of the at least two energy stores of the at least two mobile storage units is configured to be connected to the input of the voltage transformer via a connection cable leading from the respective mobile storage unit to the transformer unit.

3. The system of claim 1, further comprising at least one charging unit, wherein the at least two energy stores of the at least two mobile storage units are configured to be alternately connected to the at least one charging unit.

4. The system of claim 3, wherein the at least one charging unit is stationary.

5. The system of claim 3, wherein each of the energy stores of the at least two mobile storage units comprises an electrical battery.

6. The system of claim 5, wherein each of the energy stores of the at least two mobile storage units is configured to be connected to the at least one charging unit via a connection cable, wherein the connection cable leads from the respective mobile storage unit to the at least one charging unit.

7. The system of claim 3, wherein the at least one charging unit is configured to be connected to a power grid at its input site.

8. The system of claim 3, wherein each of the energy stores of the at least two mobile storage units comprises a fuel cell and a fuel reservoir.

9. The system of claim 8, wherein the fuel reservoir includes a metal hydride store.

10. The system of claim 8, wherein the charging unit is configured to regenerate the fuel cell of the respective mobile storage unit.

11. The system of claim 1, wherein the at least two mobile storage units are devoid of voltage transformers.

12. The system of claim 1, wherein each of the at least two mobile storage units has a storage capacity in a range from 20 kWh to 300 kWh.

13. The system of claim 1, wherein each of the at least two mobile storage units has a storage capacity in a range 80 kWh to 100 kWh.

14. The system of claim 1, wherein the at least one transformer unit is devoid of any energy source for ground power supply of one of the aircraft.

15. The system of claim 1, wherein the at least one transformer unit includes an alternating switch which is configured to alternately connect two connectors for each of the at least two mobile storage units with the input of the voltage transformer of the at least one transformer unit.

16. The system of claim 1, wherein the voltage transformer of the at least one transformer unit comprises an inverter which is configured to output a supply AC voltage for the ground power supply of one of the aircraft.

17. The system of claim 1, wherein the at least one mobile transformer unit is one of a plurality of equal mobile transformer units of the system, wherein the at least two mobile storage units are two of many equal mobile storage units of the system, and wherein at least two of the mobile storage units of the many equal mobile storage units are provided per each transformer unit of the plurality of equal mobile transformer units.

18. The system of claim 17, further comprising several equal charging units, wherein the energy stores of the many equal mobile storage units are configured to be alternately connected to the several equal charging units.

19. The system of claim 1, wherein the first vehicle chassis and the second vehicle chassis correspond to a local standard of vehicle chassis for ground units that are configured to be moved on the ground in the surroundings of the aircraft.

20. The system of claim 1, wherein the first vehicle chassis and the second vehicle chassis are equal.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0011] The invention can be better understood with reference to the following drawings. The components in the drawings are not necessarily to scale, emphasis instead being placed upon clearly illustrating the principles of the present invention. In the drawings, like reference numerals designate corresponding parts throughout the several views.

[0012] FIG. 1 is a schematic side view of a first embodiment of a system for ground power supply of aircraft according to the present disclosure.

[0013] FIG. 2 is a top view of a second embodiment of the system for ground power supply of aircraft according to the present disclosure.

[0014] FIG. 3 illustrates a detail of a converter unit and a storage unit of a further embodiment of the system for ground power supply of aircraft according to the present disclosure.

[0015] FIG. 4 illustrates details of another storage unit of the system for ground power supply of aircraft according to the present disclosure; and

[0016] FIG. 5 illustrates details of an alternating switch of a converter unit according to the present disclosure of a further embodiment of the system for ground power supply of aircraft according to the present disclosure.

DETAILED DESCRIPTION

[0017] In a system for ground power supply of aircraft according to the present disclosure, the system comprising at least one mobile converter unit which includes a first vehicle chassis and a voltage converter mounted on the first vehicle chassis, and at least two energy stores which can alternately be connected to an input of the voltage transformer in order to supply the voltage transformer with electric energy, wherein a supply cable for ground power supply of one of the aircraft is connectable to an output of the voltage converter, each of the at least two energy stores is part of one of at least two mobile storage units which each include a second vehicle chassis.

[0018] That each storage unit includes a second vehicle chassis does not mean that the storage unit has two vehicle chassis but that each storage unit has a second vehicle chassis whereas the at least one converter unit has a first vehicle chassis.

[0019] Thus, in the system according to the present disclosure, the functions of voltage conversion and energy storage are distributed to different units, i.e. the converter unit and the storage units, which have separate vehicle chassis and which, correspondingly, are separately moveable. Thus, the voltage converter of the converter unit may be supplied with electric energy out of energy stores of different storage units. Particularly, one of the at least two mobile storage units may be removed from the converter unit and replaced by another of the at least two mobile storage units, if its energy store is exhausted. The exhausted energy store of the one storage unit may then be moved using the second vehicle chassis of this storage unit to a location remote from the converter unit and be recharged there, whereas the converter unit is supplied out of the not yet exhausted energy store of the other storage unit. If this energy store is exhausted, a further exchange of the storage units may take place, because, typically, this is only the case when the energy store of the one storage unit has already been recharged even if this takes a certain period of time. With very long periods of time for recharging the energy store, three or more storage units may be provided instead of the at least two storage units so that the energy stores of two or more of these storage units may simultaneously be recharged, whereas one further storage unit ensures the supply of the voltage converter of the converter unit with electric energy by means of its energy store.

[0020] The investment needed for realizing the system according to the present disclosure is thus restricted to what is technically practically necessary, i.e. to one converter unit per aircraft to be supplied at the same time and to so many storage units as alternately needed for a permanent supply of the voltage converters of the converter units with electric energy. Particularly, in the operation of the system according to the present disclosure, no voltage converters that are not needed in charging the energy stores are moved around with the storage units for charging the energy stores of the storage units. Each of the mobile units of the system according to the present disclosure is completely focused to its respective task of storing energy or converting voltage and thus of limited overall complexity. In practice, one converter unit and one energy supply unit of the system according to the present disclosure may often be provided at even lower cost than a known mobile unit comprising a voltage converter and an energy store. Particular high savings result from the system according to the present disclosure if only one converter unit and two energy storage units are used in the system according to the present disclosure instead of two known mobile units with voltage converter and energy store.

[0021] Typically, in the system according to the present disclosure, the energy stores are each connectable to the input of the voltage converter via a connection cable leading from the respective storage unit to the converter unit. Such a connection cable provides for a certain flexibility with respect to relative positioning of the storage unit with respect to the converter unit.

[0022] It will be understood that, as a rule, at least one charging unit is present in the system according to the present disclosure, to which the energy stores are alternately connectable. As a general rule, this charging unit is stationary, in contrast to the at least one converter unit and the at least two storage units.

[0023] The energy stores of the at least two storage units may either include an electric battery, or a fuel cell and a fuel reservoir. In other words, the respective energy store may either be an electric battery or a so called fuel cell battery. In both cases, the energy store, as a whole, is an electrochemical energy store.

[0024] Independently on the design of the energy stores of the storage units as electric batteries or fuel cell batteries, the converter unit may be the same, i.e. suitable both for usage with storage units comprising electric batteries and for usage with storage units comprising hydrogen batteries.

[0025] The fuel reservoir of the fuel cell batteries is preferably a metal hydride store to be able to store hydrogen as fuel for the low-emission operation of the fuel cell at as little pressure as possible. In the system for ground power supply of aircraft according to the present disclosure, the long filling times of a metal hydride store are no problem due to the higher number of storage units as compared to the number of converter units.

[0026] If the energy stores of the at least two storage units each comprise an electric battery, the energy stores may each be connectable to the charging unit via the first connection cable via which the energy stores are also connectable to the voltage converter, or via a second connection cable, wherein the respective connection cable leads from the storage unit to the charging unit. Further, the at least one charging unit may be configured for an input side connection to a local or public power grid.

[0027] If, on the other hand, the energy stores of the at least two storage units each comprise a fuel cell and a fuel reservoir, it is preferred if the charging unit is not only provided for refilling the fuel reservoir but also for regenerating the fuel cell. Often, fuel cells can be regenerated with respect to their efficiency by subjecting them to a certain sequence of voltages. Correspondingly, the charging unit is preferably configured for applying such a sequence of voltages to the respective fuel cell. It will be understood that the storage units of the system for ground power supply of aircraft according to the present disclosure, as a rule, do not only comprise a single but several fuel cells, typically a so-called fuel cell stack such that they can provide sufficient electric power.

[0028] Independently on whether the storage units include electric batteries or full cell batteries, the at least two mobile storage units of the system according to the present disclosure may each be devoid of voltage converters, particularly devoid of voltage converters for electric power output by the energy stores and, in case of an electric battery as an energy store, also for electric power to be fed into the battery for charging it.

[0029] Storage units of the system for ground power supply of aircraft according to the present disclosure, which are suitable for application in a commercial airport, have storage capacities in the range from 20 kWh to 300 kWh. More particular, storage units with storage capacities between 80 kWh and 100 kWh are usable without permanent exchange but nevertheless quickly rechargeable and available at acceptable cost.

[0030] The at least one converter unit of the system according to the present disclosure may be completely devoid of energy sources for the ground power supply of one of the aircraft. This does, however, not exclude that the converter unit has a buffer store at the input of the voltage converter, like for example a dc voltage link having a high electric capacity to bridge an exchange of a storage unit with exhausted energy store for a storage unit with a fresh energy store. However, as a rule, the converter unit does not comprise an electrochemical energy store for the ground power supply of one of the aircraft. On the other hand, also as a rule, the converter unit will comprise an electrochemical energy store for supplying a controller of the converter unit and the like.

[0031] In order to allow for a trouble-free change between different storage units during ground power supply of an aircraft by means of the converter unit, the at least one converter unit of the system according to the present disclosure may comprise a alternating switch which alternately connects two connectors, which are each provided for one of the at least two storage units, to the input of the voltage converter of the at least one converter unit. Herein, the connection of the respective aircraft via the supply cable to the converter unit persists which is at any time connected to one of the storage units via a respective first connection cable and temporarily even to both of the least two storage units.

[0032] Because commercial aircraft typically have an onboard grid of an alternating voltage of 400 Hz, the voltage converter of the at least one converter unit typically has an inverter which outputs a supply alternating voltage of typically 400 Hz for the ground power supply of one of the aircraft.

[0033] The absolute number of the converter units and the storage units of a system according to the present disclosure will typically be higher than 1 and 2, respectively. This means that the at least one mobile converter unit, as a rule, is one of several equal or even identical mobile converter units of the system, and the at least two mobile storage units, as a rule, are two of many equal or even identical mobile storage units of the system, wherein per each converter unit of the several equal or even identical mobile converter units, as a rule, two of the storage units of the many equal or even identical mobile converter units are provided. In a same way, the at least one charging unit may be one of several equal or even identical charging units of the system, wherein per each converter unit of the several equal or even identical mobile converter units one of the charging units of the several equal or even identical charging units may be provided.

[0034] With respect to their first and second vehicle chassis, the converter units and the storage units may comply with a local standard of vehicle chassis of units which are movable in the surroundings of the aircraft on the ground. In any case, the first and second vehicle chassis of the converter units and the storage units may generally be equal or even identical.

[0035] Referring now in greater detail to the drawings, FIG. 1 depicts an aircraft 1 at a ground 2 which is supplied with power via a supply cable 3. The supply cable 3 leads from a mobile converter unit 4 to the aircraft 1. A mobile storage unit 5 is connected to the mobile converter unit 4 via a connection cable 6. The mobile storage unit 5 supplies the converter unit 4 with electric energy and has an energy store for this purpose. A further equal or even identical mobile storage unit 5 is connected to a stationary charging unit 7 via its connection cable 6 to charge its energy store. When the energy store of the storage unit 5 connected to the converter unit 4 is exhausted, and the energy store of the storage unit 5 connected to the charging unit 7 is charged, the storage units 5 can be exchanged, wherein, temporarily, both storage units 5 may be connected to the converter unit 4. Thus, the converter unit 4 is suitable for continuous ground power supply of aircraft 1.

[0036] FIG. 2 shows a system for ground power supply of aircraft 4 with a total of two converter units 4 and five storage units 5 and two charging units 7. Here, one storage unit 5 is provided as a backup, in case that the energy store of one of the storage units 5 connected to the converter units 4 is exhausted, before the energy store of the alternately used storage unit 5 connected to the charging unit 7 is recharged. If there are more than two aircrafts 1 to be simultaneously supplied with power on the ground 2 as depicted in FIG. 2, correspondingly more converter units 4, storage units 5 and charging units 7 are to be provided.

[0037] FIG. 3 schematically illustrates the interior construction of one converter unit 4 and of one storage unit 5 connected there to. The converter unit 4 has a voltage converter 8. The voltage converter 8 includes an input side step up converter 10 which is generally optionally, a dc voltage link 9 connected to the output of the step up converter 10, and an inverter 11 connected with its input to the dc voltage link 9. For example, the inverter 11 is configured to output alternating current at a frequency of 400 Hz via the supply cable 3. The battery store 12 of the storage unit 5 is an electric battery 13 with a plurality of interconnected battery cells 14. Both units 4 and 5 comprise equal or even identical vehicle chassis 15 and 16 and can each be coupled via a tongue 17 to a towing vehicle not depicted here and moved with the towing vehicle on the ground 2.

[0038] FIG. 4 schematically illustrates an alternative embodiment of the energy store 12 of a storage unit 5 as fuel cell battery 18 having a fuel cell 19 indicated as a fuel cell stack and a fuel reservoir 20, which particularly is a metal hydride storage for hydrogen. Not only the fuel reservoir 20 via a fuel line 21 but also the fuel cell 19 via the connection cable 6 is connected to the charging unit 7 depicted in FIG. 4. This serves for regenerating the fuel cell 19 by subjecting it to certain voltages during refilling the fuel reservoir 20. Further, the fuel cell 19 is indicated as breathing air 22 out of the surroundings.

[0039] FIG. 5 illustrates an input side alternating switch 23 which is connected upstream of the input side of the dc voltage link 9 of the converter unit 4. The alternating switch may be provided as alternative or an addition to the step up converter according to FIG. 3, and, particularly, be provided at the input side of the step up converter. The alternating switch 23 has two connectors DC1 and DC2 for two storage units 5 providing direct voltages. By a control unit 24, the connectors DC1 and DC2 are alternately connected to the dc voltage link 9 via power switches QA1 and QA2, wherein the connectors DC1 and DC2 are additionally decoupled by diodes D1 and D2. Further, for each of the connectors DC1 and DC2, a pre-charging circuit A1 and A2 is provided, respectively, which includes a voltage measuring to, if necessary, pre-charge the dc voltage link 9 prior to closing the respective switch QA1 or QA2, respectively, in order to avoid over currents. The switches QA1 and QA2 may be power switches, connectors or relays. By means of the control unit 24, it is possible to switch over between two storage units 5 connected to the connectors DC1 and DC2 for charging the dc voltage link 9, without interrupting the energy supply of the voltage converter 9 connected to the dc voltage link and thus the ground power supply of the aircraft 1 connected thereto. The point in time of switching over between these storage units 5 may be set manually or according to a control program that exactly switches over when the energy storage 12 of the hitherto used storage unit 5 is exhausted, i.e. de-charged down to a defined level.

[0040] Many variations and modifications may be made to the preferred embodiments of the invention without departing substantially from the spirit and principles of the invention. All such modifications and variations are intended to be included herein within the scope of the present invention, as defined by the following claims.