FR3162333A1 - Data and/or electrical power transmission system for flight test equipment - Google Patents

Abstract

The invention relates to a system for transmitting a set of data comprising information and/or electrical energy, comprising a first part (2), referred to as the transmitting part, and a second part (3), referred to as the receiving part. The transmitting part (2) comprises a circuit (4) for transmitting said data and a device (5) for transmitting said data to the receiving part (3). The receiving part (3) comprises a device (6) for receiving said data transmitted by the transmitting part (2) and a circuit (7) for transmitting said data. The transmitting device (5) and the receiving device (6) are configured to communicate wirelessly with each other. Abstract figure: Figure 3

Description

Data and/or electrical power transmission system for flight test equipment

The present invention relates to a data transmission system for flight test equipment.

To ensure aircraft safety, particularly during flight testing, dedicated equipment known as a Flight Test Installation (FTI) is generally used. This equipment collects data, performs measurements, and verifies aircraft performance. The FTI comprises a set of components, such as temperature sensors, engine speed sensors, and structural vibration sensors. Some of these components are mounted on panels forming the aircraft's external structure, such as the wings, horizontal stabilizer, or vertical stabilizer.

It may be necessary to open the panels on which some FTI components are mounted, which requires disassembling the sensors and cutting the connecting cables that would prevent the panels from being opened, an operation which is costly and time-consuming.

The aim of the invention is to remedy at least partially these drawbacks.

Summary

To this end, a system is proposed for transmitting a set of data comprising information and/or electrical energy comprising a first part, called the transmitting part, and a second part, called the receiving part, the transmitting part comprising a circuit for transmitting said data and a device for transmitting said data to the receiving part, the receiving part comprising a device for receiving said data emitted by the transmitting part and a circuit for transmitting said data, the transmitting device and the receiving device being configured to communicate wirelessly with each other.

Thus, thanks to the system according to the present invention, it is possible to mount each of the transmitting and receiving parts on a respective panel of the aircraft, and to move and replace the panels without having to disassemble the parts or cut any connecting cables.

According to another aspect, the transmitting part includes a flexible support on which the transmission circuit and the transmitting device are printed.

In another aspect, the receiving part includes a flexible support on which the transmission circuit and the receiving device are printed.

According to another aspect, the transmitting part is connected to a sensor via the transmission circuit.

In another aspect, the receiving part is connected to a control unit via the transmission circuit.

The invention also relates to an aircraft comprising a first panel and a second panel mounted opposite each other, the aircraft also comprising a transmission system as previously described, the transmitting part being attached to the first panel and the receiving part being attached to the second panel.

According to another aspect, the emitting device of the emitting part and the receiving device of the receiving part are superimposed.

According to another aspect, the aircraft includes removable means of securing the transmitting part to the receiving part.

According to another aspect, the emitting part is glued to the first panel and/or the receiving part is glued to the second panel.

The invention also relates to a flight test installation, comprising at least one transmission system as described above, a control unit and at least one sensor, the control unit and the sensor being configured to communicate with each other via said at least one transmission system.

Other features, details, and advantages will become apparent upon reading the detailed description below and analyzing the attached drawings, on which:

Fig. 1

FIG. 1 is a schematic perspective view of an information transmission system according to the present invention, in a first position of a transmitting part and a receiving part of the system.

Fig. 2

FIG. 2 is a schematic perspective view of the system of the FIG. 1 , in a different position of the transmitting part and the receiving part.

Fig. 3

FIG. 3 illustrates a schematic perspective view of the system of the FIG. 1 , in yet another position of the transmitting part and the receiving part.

Fig. 4

FIG. 4 illustrates a schematic perspective view of a detail of an aircraft equipped with the transmission system shown in Figures 1 to 3.

Fig. 5

FIG. 5 illustrates a schematic perspective view of the system of the FIG. 1 , according to an alternative embodiment of the invention.

The examples and associated conditions detailed herein are primarily intended to aid the reader in understanding the principles of the present invention and not to limit its scope to these specific examples and conditions. It will be understood that a person skilled in the art can conceive of various arrangements which, although not explicitly described or illustrated herein, nevertheless embody the principles of the present invention and are included in its spirit and scope.

Furthermore, to facilitate understanding, the following description may describe relatively simplified implementations of the present invention. As a person skilled in the art will understand, other implementations of the present invention may be of greater complexity.

In some cases, examples of modifications to the present invention may also be shown. This is done simply to aid understanding and, again, not to define the scope or establish the limits of the present invention. These modifications are not an exhaustive list, and a person skilled in the art may make further modifications while remaining within the scope of the present invention.

Furthermore, all the following statements relating to the principles, aspects and implementations of the present invention, as well as specific examples thereof, are intended to encompass both the structural and functional equivalents thereof, whether currently known or developed in the future.

The invention relates to a system for transmitting information and/or electrical energy, referred to as 1 in the figures. Advantageously, but not limitingly, system 1 is part of a flight test equipment, FTI, for "Flight Transmission Installation", as will be detailed later.

For ease of reading, the generic term "data" refers to the information and/or electrical energy transmitted by system 1.

As can be seen in the figures, system 1 comprises a first part 2 and a second part 3. In the following description, the first part is called the transmitting part 2 and the second part the receiving part 3.

As also visible in the figures, the transmitting part 2 includes a data transmission circuit, 4, and a device 5 for transmitting data to the receiving part 3. The receiving part 3 includes a device 6 for receiving data transmitted by device 5, and a data transmission circuit 7.

For example, transmission circuit 4 is connected, directly or indirectly, to a sensor on the aircraft, while transmission circuit 7 is connected, directly or indirectly, to a control unit on the aircraft or a ground station. Thus, system 1 ensures that the information from the sensor can be received and analyzed by the control unit.

The transmitting device 5 and the receiving device 6 are configured to communicate with each other, via contactless, wireless communication.

As can be seen from the figures, the transmitting part 2 comprises a flexible substrate 8 on or in which the transmission circuit 4 and the transmitting device 5 are arranged. In other words, the transmitting part 2 forms a flexible printed circuit.

The substrate 8 has an elongated straight portion 9 extended by a circular portion 10. The straight portion 8 includes at least one cable C forming the transmission circuit 5. The circular portion 10 includes the transmitting device 5.

Similarly, the receiving part 3 includes a flexible substrate 11 on or in which the transmission circuit 7 and the receiving device 6 are arranged. In other words, the receiving part 3 forms a flexible printed circuit.

The substrate 11 has an elongated straight portion 12 extended by a circular portion 13. The straight portion 12 includes at least one cable C forming the transmission circuit 7. The circular portion 13 includes the receiving device 6.

The flexible substrate 8, 11 is advantageously made of polyimide, for example marketed under the brand name "Kapton", and/or polyethylene terephthalate (PET), and/or polyethylene naphthalate (PEN). Other materials, for example woven fibers such as fiberglass, are also possible.

The flexible substrate 8, 11 ensures that system 1 has an aerodynamic shape, flush with the surface on which system 1 is intended to be mounted.

As already mentioned, the data transmitted by system 1 includes information and/or electrical energy. Depending on the communication protocol (LVDS for "Low Voltage Differential Signaling", Ethernet, or POE for "Power over Ethernet") of the FTE equipment's digital bus, the electrical energy may differ (25 volts DC for LVDS, 48 volts DC for POE).

The transmitter 5 and receiver 6 devices each include capacitors and coils to form antennas printed in the flexible substrate 8, 11.

To make system 1 operational, it is sufficient to position each of the parts 2, 3 on a respective panel of the aircraft, as will be detailed later, arranging them so that the circular portions 10 and 13 overlap, as illustrated in the sequence of figures 1 to 3, which ensures the transmission of energy and/or information between the transmitting and receiving parts 2, 3.

The invention is now described in detail with reference to figures 4 and 5.

As particularly visible on the FIG. 4 The invention also relates to an aircraft A comprising an external envelope 15 having panels, two of which are illustrated in the figure and referenced 16, 17. These may be wing panels, or horizontal stabilizer panels, or vertical stabilizer panels, for example. The panels may be doors, for example.

The first panel 16 and the second panel 17 are positioned opposite each other. They are mounted edge to edge, with one edge 16b of panel 16 being placed against (or spaced a few millimeters apart from) one edge 17b of panel 17.

The receiving part 3 is mounted on the second panel 17, the elongated portion 12 being secured, for example glued, to the panel 16. The circular portion 13 is left free and protrudes out of the edge 17b so as to be placed on the first and second panels 16, 17.

The transmitting part 2 is mounted on the first panel 16, the elongated portion 9 being secured, for example glued, to the panel 16. The circular portion 10 is left free and protrudes out of the edge 16b so as to be placed on the circular portion 13 of the receiving part 3.

Thus, as already explained, the data is transmitted in system 1 between the transmitting part 2 and the receiving part 3 by the superposition of the circular portions 10, 13.

It is noted that the elongated parts 9, 12 are advantageously arranged parallel to the airflow F, which helps to strengthen the adhesion of parts 2 and 3 against their respective panels 16, 17.

As seen on the FIG. 5 The system 1 advantageously includes removable means 18 for attaching the circular portions 10 and 13. These means are, for example, magnets or aluminum strips. The removable attachment means 18 ensure that the transmitting and receiving devices 5 and 6 remain close to each other throughout the aircraft's flight, thus preventing any interruption in data transmission to the control unit. The fact that the attachment is removable allows for easy disconnection of the circular portions 10 and 13 when necessary.

When panels 16 and 17 need to be moved, for example during maintenance, simply detach the circular sections 10 and 13 so that the two transmitting and receiving parts of system 1 are separated; panels 16 and 17 can then be moved without difficulty. Once the panels are back in place, simply replace the circular sections 10 and 13, overlapping them, and, if necessary, secure them using the means 18. System 1 is then functional again, without any wires needing to be cut or the system itself damaged. In other words, the integrity of system 1 is ensured in the event of movement of panels 16 and 17. Moreover, the short-range wireless transmission between parts 2 and 3 allows for some play in the alignment of panels 16 and 17.

As already indicated, the invention also relates to a flight test facility, FTI, comprising at least one system 1. The FTI facility also includes a set of monitoring equipment, including multiple sensors (temperature, engine speed, structural vibrations) and equipment for recording data from the sensors and transmitted in particular to the control unit by the transmission systems 1.

As can be seen from the preceding description, the transmission system 1 according to the present invention ensures reliable, wireless transmission of data and electrical power while having an aerodynamic shape and allowing simplified and less costly aircraft maintenance.

Modifications and improvements to the above-described implementations of the present invention may be apparent to a person skilled in the art. The above description is illustrative through examples rather than exhaustive. The scope of the present invention is therefore limited only by the scope of the claims below.

Claims (10)

A system for transmitting a set of data comprising information and/or electrical energy, comprising a first part (2), called the transmitting part, and a second part (3), called the receiving part, the transmitting part (2) comprising a circuit (4) for transmitting said data and a device (5) for transmitting said data to the receiving part (3), the receiving part (3) comprising a device (6) for receiving said data transmitted by the transmitting part (2) and a circuit (7) for transmitting said data, the transmitting device (5) and the receiving device (6) being configured to communicate wirelessly with each other. System according to claim 1, wherein the transmitting part (2) comprises a flexible support (8) on which are printed the transmission circuit (4) and the transmitting device (5). System according to one of claims 1 or 2, wherein the receiving part (3) comprises a flexible support (11) on which are printed the transmission circuit (7) and the receiving device (6). System according to any one of the preceding claims, wherein the emitting part (2) is connected to a sensor by the transmission circuit (4). System according to any one of the preceding claims, wherein the receiving part (3) is connected to a control unit by the transmission circuit (7). Aircraft comprising a first panel (16) and a second panel (17) mounted opposite each other, the aircraft (A) also comprising a transmission system (1) according to one of the preceding claims, the transmitting part (2) being integral with the first panel (16) and the receiving part (3) being integral with the second panel (17). Aircraft according to the preceding claim, wherein the transmitting device (5) of the transmitting part (2) and the receiving device (6) of the receiving part (3) are superimposed. Aircraft according to the preceding claim, comprising removable fastening means (18) of the transmitting part (3) to the receiving part (2). Aircraft according to any one of claims 6 to 8, wherein the transmitting part (2) is glued to the first panel (16) and/or the receiving part (3) is glued to the second panel (17). Flight test facility, comprising at least one transmission system according to one of the claims, a control unit and at least one sensor, the control unit and the sensor being configured to communicate with each other via said at least one transmission system (1).