Electrical device having indirect lightning protection, attitude and orientation reference system, and aircraft

Abstract

The present invention relates to an electric device having indirect lightning protection. The electric device has a conductive housing in which an electric component is accommodated. The electric device further has an electric data interface connected to the electric component for transmitting an electric signal from the component to the outside of the housing or transmitting an external electric signal to the inside of the housing. Furthermore, a power supply interface is provided for supplying the electronic component with power from an external power source. The electric data interface and the power supply interface are configured such that the electric component is galvanically isolated from the housing and from input / output lines of the data interface and the power supply interface such that damage to the component due to a current pulse caused by lightning is prevented. Furthermore, an attitude and heading reference system and an aircraft are provided comprising the electric device.

Description

Detailed Description of the Invention

[0001] The present invention relates to an electrical device having indirect lightning protection, and more particularly to an electrical device having indirect lightning protection for use in an attitude and heading reference system for aviation or an aircraft.

[0002] The height of lightning protection requirements is of utmost importance, especially in the aircraft industry. All installed devices need to be provided with lightning protection of various sizes (threat levels). When the threat level is high and the number of wired interface connections between devices is large, space may be required for individual devices, which cannot be ignored. Depending on the requirements and mechanical design, this part can occupy up to one-third of the volume within the device.

[0003] According to the lightning protection standard DIN EN 62305-4 (VDE0185-3054), the risk to components due to lightning strikes is classified into five threat levels, or five lightning protection levels (LPLs). In FIG. 6, the corresponding characteristic data (the ratio Voc (unit: V) / Isc (unit: A) of the peak open-circuit voltage to the peak short-circuit current at the calibration point for various waveforms 3, 4, and 5a) are assigned to threat levels 1 to 5. Waveform 3 is a damped sine wave with a frequency of 1 MHz. Due to attenuation, about 50% of the amplitude remains after 5 cycles. Waveforms 4 and 5a are double-exponential pulses, differing only in duration. Waveform 4 has a rise time of 6.4 μs and a time to half-value of 69 μs. Waveform 5a has a rise time of 40 μs and a time to half-value of 120 μs. Therefore, the energy content of waveform 5a is the highest.

[0004] Regarding appropriately protecting the electrical and electronic systems of an aircraft against the effects of electromagnetic pulse, there are various combinations consisting of the following multiple protective measures: grounding and equipotential bonding, space shielding, cable routing, and cable shielding. The characteristic values of the protective measures need to correspond to the selected threat level or lightning protection level.

[0005] Electronic devices or electrical devices, especially those installed on an aircraft, require appropriate lightning protection to protect against lightning strikes. Due to an unfavourable configuration, if an externally mounted device (e.g., an electronic antenna) is directly struck by lightning, this is referred to as a "direct lightning strike". This case is not considered. When a lightning strike occurs at any position on the aircraft fuselage, the lightning pulse can capacitively couple from that position to the interface cables through which the electronic devices communicate with each other. The lightning pulse moves along the cable as a wave and enters the device via the device plug. This is referred to as an "indirect lightning strike". The protective measures required for this are referred to as "indirect lightning protection".

[0006] Indirect lightning protection is usually achieved by standardized protection elements. The components for this are gas arresters, varistors, suppressor diodes, and resistors. These are used according to the pulse energy. The basic principle is to convert the short-time pulse energy caused by an indirect lightning strike into heat by these components, especially by varistors / resistors or gas arresters. The calculations required for this are described in the technical literature (see Mel Clarke and Kent Walters (2018): ”Lightning protection for aircraft electrical power and data communication systems”, publication Micronote 127, Microsemi Corporation).

[0007] However, the current lightning protection measures in all types of aircraft have the following drawbacks. First, the space required for the protection elements increases linearly with the number of external wired interface connections connected to the device. Furthermore, as the threat level increases, the component surface increases exponentially. This exponential ratio has a significant impact on the volume of the device. For example, when energy is converted into heat using a resistor, if the resistance R remains constant, the energy E, and thus the volume of the component, increases according to E = R × I 2 × t. In this case, I is the surge current of the lightning pulse flowing into the device on the interface line, and t is the duration of the pulse. In the graph, Figure 7 shows the relationship between the component surface and the threat level, as well as the drawbacks of the current lightning protection measures. The coefficient between each threat level is approximately 2.5, and the current increases by this coefficient according to aviation standard DO-160 item 22. The calculations of the graph in Figure 7 were performed taking into account the existing protection elements based on the number of conventional digital interfaces in the aviation field.

[0008] When the threat level is very high, it is assumed that a single protection element will be insufficient. Therefore, it is necessary to pre-connect a second, more powerful protection element in series by different technologies (step-by-step protection). This is particularly necessary for interfaces with low impedance such as power supply connections. By additionally strengthening the protection in this way, the space consumption by components becomes even greater.

[0009] US2019 / 0199137A1 describes a wireless near-field microwave power transmission system. The wireless power transmission system wirelessly transmits power to a wireless power receiving device using a wireless power transmission device. The wireless power transmission device includes a plurality of microwave antennas extending along an axis in a staggered arrangement. In the staggered arrangement, the plurality of microwave antennas are arranged on alternating sides with respect to the axis. Each microwave antenna extends along a direction perpendicular to the axis. Many antennas overlap with the wireless power receiving antenna in the wireless power receiving device. The control circuit uses an oscillator and an amplifier circuit to supply a drive signal to the plurality of antennas that overlap with the wireless power receiving antenna. The drive signal can be adjusted based on feedback from the wireless power receiving device so as to increase the power transmission efficiency. The system may include a wireless power transfer device having an inductive power transfer coil.

[0010] US2018 / 0041249A1 describes a power / data coupler. Such a data and power transmission network includes an actuator and two power / data couplers. The actuator is connected to the electrical coupler to first transmit power to the network via a power supply pin and a third pin, or to receive data from the network via a fourth pin. This system further includes a galvanic isolation transformer and windings, which are connected to a first power supply pin and a second power supply pin. Also, data transfer is performed via a first transformer and a second transformer, which inductively transfer the data from the network to the system and then inductively transfer the data to the network.

[0011] Therefore, the present invention is particularly based on the object of creating an electrical device with indirect lightning protection for use in an attitude and heading reference system for aviation and in an aircraft. This electrical device has high lightning protection requirements while having a reduced size.

[0012] This object is Claims achieved by the electrical device with indirect lightning protection described in 、 and by the attitude and heading reference system and , posture also by the aircraft. Advantageous and further embodiments of the present invention are described in the dependent claims. and navigation

[0013] ​According to the present invention, there is provided an electrical device having an indirect lightning protection. The electrical device has a conductive housing in which electrical components are housed inside. Further, the electrical device includes an electrical data interface connected to the electrical components so as to transmit an internal electrical signal from the components to the outside of the housing or to transmit an external electrical signal from the outside of the housing to the components. Further, a power supply interface for supplying power from an external power source to the electronic components is provided. The electrical data interface and the power supply interface are configured such that the electrical components are galvanically insulated from the housing and from the input / output lines of the data interface and the power supply interface so as to prevent damage to the components by lightning-induced current pulses. In order to properly use an electrical device for the navigation of an aircraft, according to the present invention, it is provided that the electrical component is adapted to provide attitude and heading reference data for navigation. In order to properly implement galvanic insulation of the electrical component from the conductive housing of the electrical device and the input / output lines of the data interface, the electrical data interface has an external data interface part connectable to a peripheral electrical conductor structure and an internal data interface part connected to the component, the external data interface part and the internal data interface part being galvanically insulated, and according to the present invention, data transmission between the external data interface part and the internal data interface part is performed optically, magnetically, capacitively, or mechanically.

[0014] Therefore, the present invention relates to an electrical device having an indirect lightning protection which still has a compact design with a small volume and reduced size even for high lightning protection requirements such as a threat level exceeding 3 (see FIG. 7). Since the components inside the housing of the electrical device are galvanically insulated, the lightning-induced current pulses are blocked by the present invention. In the prior art devices, the current due to the lightning pulse flows into the device in the aircraft cable, and then flows from the device through the above-described protection elements such as gas arresters, varistors, suppressor diodes, and resistors inside the device to the housing, and from there to the aircraft fuselage through the ground. However, with the present invention, the current due to the lightning pulse does not flow through the inside of the device to the housing. This means that protection elements that require a large space can be omitted, and in particular, when the number of wired interfaces is large and the threat level is high, both the volume and weight of the electrical device can be significantly reduced according to the present invention.

[0015] The electric component preferably includes a fiber optic gyrocompass or a MEMS gyro, and an electric circuit for controlling the compass and for evaluating and transmitting the attitude and orientation data.

[0016] For simple communication according to a data transmission standard applicable in aeronautics, the electric data interface is advantageously adapted to digitally read and output data, in particular in the ARINC429 protocol, the RS-422 protocol, the RS-485 protocol, the CAN protocol, the ETHERNET protocol, or the DISCRETE protocol.

[0017] For a fail-safe and redundant output of the attitude and orientation reference data, it is particularly advantageous if the electric data interface is adapted to output the attitude and orientation reference data analogously.

[0018] Since the component surface increases exponentially with the threat level (Figure 7), it is particularly useful if the electric component is provided with lightning protection according to DIN EN 62305 for threat levels 3 and above.

[0019] For particularly simple implementation of the galvanic insulation of the electric component of the electric device from the surrounding peripheral circuits and the external power supply, the power supply interface has an external power supply interface part connectable to an external power supply and an internal power supply interface part connected to the component, the external power supply interface part and the internal power supply interface part being galvanically insulated from each other, and power transmission between the external power supply interface part and the internal power supply interface part being effected by magnetic induction or by transmission of electromagnetic waves, which is particularly useful.

[0020] For particularly effective protection against lightning-induced voltage pulses of the electrical component, it is advantageous that the electrical component is protected against lightning-induced voltage pulses by an ESD protection diode.

[0021] To prevent or at least reduce the probability of voltage flashover between the lines of the electrical device, the electrical data interface advantageously includes an equipotentializing element intermediately connected between the two-core differential signal input / output lines such that, during a lightning-induced voltage pulse, the two-core differential signal input / output lines rise to the same potential and the voltage flashover between the lines is prevented.

[0022] The equipotentializing element desirably includes a suppressor diode, varistor, or series resistor element.

[0023] According to another particularly advantageous embodiment of the invention, the input / output lines of the electrical data interface and the power supply interface are advantageously arranged spaced apart from each other such that voltage flashover between the lines is prevented during a lightning-induced voltage pulse.

[0024] The minimum distance between the input / output lines of the electrical data interface and the power supply interface is desirably greater than 2 mm, or greater than 2.5 mm, or greater than 3 mm.

[0025] Furthermore, in the present invention, an attitude and heading reference system for aviation comprising an electrical device according to the present invention is claimed.

[0026] Furthermore, according to the present invention, an aircraft comprising an electrical device having indirect lightning protection according to the present invention is provided.

[0027] The present invention will be described in detail in the following text with reference to the figures by way of example. The subject matter of the present invention is defined by the claims.

[0028] FIG. 1 is a schematic block diagram of an electrical device with indirect lightning protection according to the present invention, connected to a peripheral electrical conductor structure and an external power supply; FIGS. 2A - 2D are schematic circuit diagrams of a data interface and a power supply interface of an electrical device according to the present invention; FIG. 3 is a detailed schematic block diagram of a data interface of an electrical device with indirect lightning protection according to the present invention; FIG. 4 shows an attitude and heading reference system for aviation according to the present invention; FIG. 5 shows an aircraft equipped with an electrical device according to the present invention; FIG. 6 is a table showing characteristic data of threat levels 1 - 5 according to the lightning protection standard DIN EN 62305; FIG. 7 is a schematic diagram showing the component surfaces required according to the threat levels of the lightning protection standard DIN EN 62305.

[0029] In the figures, the same reference numerals are assigned to the same components and components having the same functions.

[0030] FIG. 1 is a schematic block diagram of an electrical device 100 with indirect lightning protection. The electrical device 100 is connected to a peripheral electrical conductor structure 200 suitable for data transmission and an external power supply 300. The electrical device 100 with indirect lightning protection has a conductive housing 110, and an electrical component 120 is accommodated within the conductive housing 110. The conductive housing 110 may be a metal housing or a housing with a metal coating. The housing 110 can also be made of an insulating material, and in this case, the electrical shielding of the electrical component 120 is achieved by a wire mesh such as a Faraday cage. The electrical components are connected to each other via internal connection lines 160, and data can be transmitted or power supply can be ensured via the connection lines 160. The connection lines 160 are only schematically illustrated. The connection lines 160 can be designed as simple power supply lines up to the data transmission bus system.

[0031] The electrical component 120 is connected to the electrical data interface 130 via an internal connection line 160 so as to transmit an internal electrical signal from the component 120 to the outside of the housing 110 or to transmit an external electrical signal from the peripheral electrical conductor structure 200 to the inside of the housing 110 to the component 120. The electrical device 100 further includes a power supply interface 140 that supplies power from an external power supply 300 to the electrical component 120. As a means for ensuring the supply of power to the electrical device 100, the external power supply 300 may be of any type. However, a power supply by direct current with a power supply voltage of 28V, which is common in the aviation field, is preferred.

[0032] As schematically shown by broken lines in FIG. 1 for the electrical data interface 130 and the power supply interface 140, the electrical data interface 130 and the power supply interface 140 are configured such that the electrical component 120 is galvanically insulated from the housing 110 and from the input / output lines 150 of the data interface 130 and the power supply interface 140 so as to prevent damage to the component 120 by lightning-induced current pulses. Therefore, in the electrical device according to the present invention, all the components 120 are configured to be galvanically insulated from the housing 110, and the supply to these components 120 is also galvanically insulated from the housing 110.

[0033] Although the electrical device with indirect lightning protection according to the present invention is not intended to be limited to applications in the aircraft industry, it is preferred that the electrical component 120 be adapted to provide attitude and azimuth reference data for aviation navigation. In this case, the electrical component 120 can perform various functions. For example, one of the electrical components 120 can be a data transmission unit 120a. The data transmission unit 120a is electrically connected to the internal data interface portion 130b in a galvanically insulated state to send internal electrical signals from the component 120 to the peripheral electrical conductor structure 200 via the electrical data interface 130. Further, when the electrical device 100 is used as an attitude and azimuth reference component for aviation navigation, one of the electrical components 120 may be the fiber optic gyrocompass 120b through which attitude and azimuth reference data is provided. Further, an electrical circuit 120c may be provided to control the compass 120b and to evaluate and transmit the attitude and azimuth data. Finally, the electrical device 100 may have a central processing unit 120d. The operation of the electrical device 100, in particular the control of the compass and the evaluation and transmission of the attitude and azimuth data, is monitored and controlled by the central processing unit 120d. Also, the electrical device 100 can be designed as a data distribution mechanism, as a data compression mechanism, or as a flight control device. Generally, the electrical device 100 needs to meet high lightning protection requirements and at the same time can be a device particularly at risk, for example due to a large number of interfaces.

[0034] In one embodiment of an electrical device 100 having indirect lightning protection as part of an attitude and heading reference system (AHRS) with a fiber optic gyro (FOG), data can be output in the ARINC 429 format, which is standard in the aircraft industry. Therefore, the electrical data interface 130 is adapted to digitally read and output the data. However, optionally, the attitude and heading reference data can also be output via an analog interface (e.g., a synchro interface). For this reason, the electrical data interface 130 is also adapted to output the attitude and heading reference data analogously. Due to the high precision of the sensors provided in the electrical component 120 of the electrical device 100, autonomous azimuth adjustment (gyrocompassing) becomes possible. Therefore, magnetic sensors that are prone to causing interference for azimuth adjustment can be completely omitted.

[0035] Referring to FIGS. 2A - 2D, the galvanic insulation of the housing 110 and the input / output lines 150 of the data interface 130 and the power supply interface 140 for the electrical component 120 will be described in the following text. For galvanic insulation, the electrical data interface 130 has an external data interface portion 130a that can be connected to a peripheral electrical conductor structure 200 via the input / output line 150, and an internal data interface portion 130b that is connected to the electrical component 120 via an internal connection line 160. The external data interface portion 130a and the internal data interface portion 130b are galvanically insulated, that is, electrically insulated from each other, and data transmission between the external data interface portion 130a and the internal data interface portion 130b can be performed, for example, in the manner shown in FIGS. 2A - 2D.

[0036] According to FIG. 2A, an input signal (referred to as signal A) from the peripheral electrical conductor structure 200 on the input line 150 can be converted into an optical signal (E Photon ) by an amplifier and a light-emitting diode in the external data interface portion 130a, and can be reconverted into the electrical input signal A (corresponding to the signal A on the input side of the external data interface portion 130a) by a photodiode and an amplifier in the internal data interface portion 130b. Next, the electrical signal A of the internal data interface portion 130b is sent to the component 120 via the internal connection line 160.

[0037] Similar to FIG. 2A, data transmission with simultaneous galvanic isolation can be achieved by magnetic coupling of two coils through the magnetic field H as shown in FIG. 2B.

[0038] FIG. 2C shows another possibility of data transmission. In this case, the signal C in the external data interface portion 130a is converted by an amplifier through capacitive coupling into the charge on the capacitor plate (connected to the electric field E), and the opposite charge is reconverted by the amplifier into the signal C on the opposite capacitor plate in the internal data interface portion 130b.

[0039] Regarding the non-time-limited signal, as shown in FIG. 2D, the switching signal D in the external data interface portion 130a is supplied by an amplifier to the mechanical switching relay, whereby the mechanical switch in the internal data interface portion 130b is actuated by the transmission of force by the force F, whereby the switching signal D can be transmitted to the component 120 while being galvanically isolated from the peripheral electrical conductor structure 200, which is also theoretically conceivable.

[0040] Data transmission between the external data interface part 130a and the internal data interface part 130b can be carried out optically (FIG. 2A), magnetically (FIG. 2B), capacitively (FIG. 2C), mechanically (FIG. 2D), or generally by the transmission of electromagnetic waves (for example, in a non-optical radio range where appropriately designed transmitting and receiving antennas are used). Therefore, as shown in FIGS. 2A to 2D, separating the signal from the remaining electronic components is mainly achieved by optical transmission technology, magnetic transmission technology, electrical transmission technology, or mechanical transmission technology. FIGS. 2A to 2D are initially described only with respect to the input of the signal, but it is obvious that the same technology as shown in FIGS. 2A to 2D is used in the reverse direction for the transmission of the signal from the internal data interface 130b to the external data interface 130a.

[0041] Also, for consistent galvanic insulation, the power supply of the interface components needs to be configured with galvanic insulation. Since the power consumption of the driver component and the receiver component 120 is small, the space required for this is small. In the aircraft industry, a DC power supply with a power supply voltage of 28V is used, and the 28V input voltage operates via a DC converter. In this case, since the DC transformer functions in the same way as an AC transformer via inductive coupling, galvanic insulation has already been obtained.

[0042] According to the present invention, an electrical device 100 with indirect lightning protection is created, in which all wired interfaces, as well as the power supply connection from and to the device, are galvanically insulated. For this purpose, the power supply interface 140 also has an external power supply interface part 140a connectable to an external power supply 300 and an internal power supply interface part 140b connected to the components, and these are also galvanically insulated. The power transmission between the external power supply interface part 140a and the internal power supply interface part 140b is done by magnetic induction (Fig. 2B) or by electromagnetic wave transmission.

[0043] Therefore, by galvanically insulating the electrical device from its environment, damage to the components 120 caused by lightning-induced current pulses can be prevented. In addition to protection against damage by lightning-induced current pulses, lightning protection against lightning-induced voltage pulses is also necessary.

[0044] The lightning protection measures against damage caused by lightning-induced voltage pulses are schematically shown in the block diagram of Fig. 3. The lightning protection measures are described using the example of the data interface 130, but are also applicable to the power supply interface 140 of the electrical device 100. As shown in Fig. 3, for example, at least one so-called ESD (electrostatic discharge) protection 131 is provided in the region of the electrical data interface 130a between two-core differential signals on the input line, thereby realizing protection against lightning-induced voltage pulses. Particularly active components such as drivers, receivers, and controllers generally need to be protected from high voltage pulses. Since the current is small, ESD protection is sufficient in this case. In some drivers and receivers, this is already incorporated into the components by existing ESD protection diodes, so no additional processing is required. The ESD protection diode can be implemented, for example, by a tunnel diode connected in the reverse direction.

[0045] In the case of a two-core differential signal on the output line 150 having lines 151 and 152, an equipotentializing element 153 can be additionally provided so that all electrical inputs / outputs rise to the same potential during a lightning pulse and no voltage flashover occurs. Due to reasons related to the manufacturer for space savings, since the distance between the pins of the component 120 is small, this is particularly necessary in the case of high voltage pulses. Therefore, the electrical data interface 130 may include an equipotentializing element 153 intermediately connected between the two-core differential signal input / output lines 151 and 152 so that the input / output line 150 rises to the same potential during a lightning-induced voltage pulse and a voltage flashover between the lines is prevented. Since the internal connection lines 160 are arranged within the shield on the back side of the insulation of the electrical data interface 130, there is no need to provide an equipotentializing element between the two-core connection lines 161 and 162. A suppressor diode having a size individually adapted to the type of interface and the threat level is sufficient as the equipotentializing element 153. A series resistor in the signal line 150 also serves this purpose.

[0046] To prevent voltage flashover between different interface lines, all conductor tracks of the input / output line 150 can have a sufficient distance a therebetween. Further, a device plug (both male and female parts) connected to the external data interface part 130a having a sufficient pin spacing a can also be used.

[0047] The input / output lines 150 of the electrical data interface 130 and the power supply interface 140 are preferably arranged at a distance from each other so that a voltage flashover between the lines 150 is prevented during a lightning-induced voltage pulse. The minimum distance a between the input / output lines 150 of the electrical data interface 130 and the power supply interface 140 may be greater than 2 mm, or may be greater than 2.5 mm, or may be greater than 3 mm, or may be greater than 3.5 mm, or may be greater than 4 mm, or may be greater than 4.5 mm, or may be greater than 5 mm. When it is not desired to increase the pin pitch a in the front unit of the external data interface portion 130a, a local coating of the printed circuit board can also be used.

[0048] Figure 4 is a schematic block diagram of an attitude and heading reference system 400 for aviation navigation. The attitude and heading reference system 400 includes an electrical device 100, a peripheral electrical conductor structure 200 for further data transmission, and an external power supply 300. The attitude and heading reference system (AHRS) 400 is to be understood as a system preferably mounted on an aircraft 500 schematically shown in FIG. 5. The system 400 is intended to include all relevant electronic devices involved in the aviation navigation of the aircraft 500. The term aircraft 500 is generally intended to be understood to mean a flying device including helicopters and airships. Therefore, the aircraft 500 in which the electrical device and / or the attitude and heading reference system 400 according to the present invention is particularly usefully used can be a turboprop aircraft, a business jet, an IFR helicopter, a regional aircraft, or a military COTS application.

[0049] According to the present invention, there is provided an electrical device 100 with indirect lightning protection having a compact design with reduced volume even at high threat levels. This is because conventional protection elements such as gas arresters, varistors, suppressor diodes, or resistors do not need to be used to galvanically insulate the component 120 from the external current source 300 and the surrounding electrical conductor structure 200. In FIG. 7, the increase in the required space due to the increase in insulation requirements, as well as the increase in the required space due to the simple protection elements 131 and 153 shown in FIG. 3 for differential data lines, can be seen as a slight increase in the dashed line.

[0050] The solid exponential function line shows the component surface for components of the prior art, and the dashed line shows the component surface of the electrical device 100 with indirect lightning protection according to the present invention. This does not include the very small additional space required for galvanic insulation of the power supply. Looking at FIG. 7, the significant savings in space on the printed circuit board are most prominent from threat level 3. Therefore, it is preferable that the electrical component 120 is provided with lightning protection at threat levels of 3 or higher according to DIN EN 62305. The absence of the aforementioned protection elements and the associated reduction in the volume of the housing 110 result in a reduction in weight. This is a top priority, especially in the aircraft industry. The cost is calculated by comparing the eliminated protection elements with the galvanic insulation elements for the associated drivers. These are at similar levels. That is, the solution according to the present invention can be achieved cost-neutrally.

[0051] The present invention provides the possibility of eliminating protective elements that are classified as generally important. The protective elements do not function under normal operating conditions, and as a result, a failure of a protective element may not be noticed until the next service interval of the aircraft. If a protective element fails, a lightning pulse can penetrate the electronic components of a prior art device via this line, resulting in an overall failure of the device. Then, the safety of the flight can be threatened. Without these protective elements, this risk no longer exists. When the solution according to the present invention is implemented, a component failure means that data transmission on this interface line becomes impossible. This failure will be reported to the pilot via another signal line, giving the pilot the opportunity to make safety-related decisions.

[0052] The present invention provides an electrical device 100 with indirect lightning protection and an electrical device having a galvanically isolated potential. The galvanic insulation for the data interface according to the present invention can be achieved by various transmission types (for example, optical transmission, magnetic transmission, capacitive transmission, electrical transmission, mechanical transmission, or electromagnetic transmission by radio waves). In this case, the galvanic insulation can be achieved individually or in combination for analog inputs, digital inputs, and power supply line inputs. Also, it is possible to implement galvanic insulation for individual conductors (serial bus systems), differential conductors, or parallel bus lines. The transmission of signals in the galvanic insulation regions of the external data interface part 130a and the internal data interface part 130b, as well as the transmission of signals in the galvanic insulation regions of the external power supply interface part 140a and the internal power supply interface part 140b, can be carried out via media such as air, gas, electrolytic solution, glass fiber, or plastic fiber.

Brief Description of the Drawings

[0053]

Figure 1

Figure 2A

Figure 2B

Figure 2C

Figure 2D

Figure 3

Figure 4

Figure 5

Figure 6

Figure 7

Claims

1. An electrical device (100) having indirect lightning protection, comprising: A conductive housing (110) having an electrical component (120) housed therein, the electrical component (120) being adapted to provide attitude and azimuth reference data for aviation; An electrical data interface (130) connected to the electrical component (120) for transmitting an internal electrical signal from the electrical component (120) to the outside of the conductive housing (110) or for transmitting an external electrical signal from the outside of the conductive housing (110) to the electrical component (120); A power supply interface (140) for supplying power from an external power supply (300) to the electrical component (120); The electrical device (100) being configured such that: The electrical data interface (130) and the power supply interface (140) are configured to galvanically insulate the electrical component (120) from the conductive housing (110), and from input / output lines (150) of the electrical data interface (130) and the power supply interface (140), so as to prevent damage to the electrical component (120) by lightning-induced current pulses; The electrical data interface (130) comprises: An external data interface portion (130a) connectable to a peripheral electrical conductor structure (200); An internal data interface portion (130b) connected to the electrical component (120); The external data interface portion (130a) and the internal data interface portion (130b) being galvanically insulated from each other; Data transmission between the external data interface portion (130a) and the internal data interface portion (130b) being optically conducted; The electrical data interface (130) including an equalization element (153) intermediately connected between two-core differential signal input / output lines (151, 152) such that, during a lightning-induced voltage pulse, the two-core differential signal input / output lines (151, 152) rise to the same potential, preventing a voltage flashover between the two-core differential signal input / output lines (151, 152).

2. The electrical component (120) is ​ A fiber optic gyrocompass or MEMS gyro (120b), an electric circuit (120c) for controlling the fiber optic gyrocompass or MEMS gyro (120b) and for evaluating and transmitting the attitude and orientation reference data, The electric device (100) according to claim 1, characterized by comprising the same.

3. The electric data interface (130) is adapted to digitally read and output data in an ARINC429 protocol, an RS-422 protocol, an RS-485 protocol, a CAN protocol, an ETHERNET protocol, or a DISCRETE protocol. The electric device (100) according to claim 1 or 2.

4. The electric data interface (130) is adapted to analogously output attitude and orientation reference data. The electric device (100) according to claim 1 or 2.

5. The electric component (120) is provided with lightning protection at a threat level of 3 or higher according to DIN EN 62305. The electric device (100) according to claim 1 or 2.

6. The power supply interface (140) has an external power supply interface portion (140a) connectable to an external power supply (300), and an internal power supply interface portion (140b) connected to the electric component (120), and the external power supply interface portion (140a) and the internal power supply interface portion (140b) are galvanically insulated, and the power transmission between the external power supply interface portion (140a) and the internal power supply interface portion (140b) is performed by magnetic induction or by electromagnetic wave transmission. The electric device (100) according to claim 1 or 2.

7. The electric component (120) is protected from lightning-induced voltage pulses by an ESD protection diode (131). The electric device (100) according to claim 1 or 2.

8. The equipotentialization element (153) includes a suppressor diode, a varistor, or a series resistor element. The electric device (100) according to claim 1 or 2.

9. The input / output lines (150) of the electrical data interface (130) and the power supply interface (140) are arranged separately from each other so as to prevent a voltage flashover between the two-core differential signal input / output lines (151, 152) during a lightning-induced voltage pulse. The electrical device (100) according to claim 1 or 2.

10. The minimum distance (a) between the input / output lines (150) of the electrical data interface (130) and the power supply interface (140) is greater than 2 mm, or greater than 2.5 mm, or greater than 3 mm. The electrical device (100) according to claim 1 or 2.

11. An attitude and azimuth reference system (400) for aviation navigation, comprising the electrical device according to claim 1 or 2.

12. An aircraft (500), comprising the electrical device according to claim 1 or 2.

Images