JPH0249960B2 - - Google Patents

Description

[Detailed Description of the Invention] [Field of Industrial Application] This invention provides a branched control system in which a vertical control function section that transmits a digital optical signal and generates a control command is connected to a servo unit that operates a control wing. The present invention relates to a control signal transmission device for an aircraft, which is equipped with a passive conductor system formed from a light guide and processes and transmits digital control signals.

[Conventional technology]

It is generally known that mechanical devices, such as wires, rods, rotating shafts, or combinations thereof, are used to transmit steering movements from the pilot to, for example, the rudder in an aircraft. Depending on the conditions of use, these devices are supported by hydraulic or electrical drives. It is also well known that large aircraft use servo control. If you are using this kind of control,
In order to connect predetermined rudders, for example, the following operating procedure is always prescribed. In other words, always operate the elevators symmetrically.

Operate the rudder asymmetrically.

Always operate the flaps symmetrically.

The disadvantage therefore arises that if one rudder fails, the remaining rudders are possibly unusable in order to maintain maneuverability. Considered from a military point of view, another drawback of the mechanical controls described above arises from their susceptibility to breakage. For this purpose, electric servo control is used, in which control signals are transmitted via a passive conductor, such as a coaxial cable. In this case, the individual operating circuits, including the cable leading to the drive, can be
For example, it is made fourfold. Therefore, even if three of the attached cables are damaged by bullets or the like, the operating circuit will still function. However, this idea also has the following weaknesses.

- This type of device is exposed to electromagnetic interference fields (lightning strikes, short circuits)
weak against

- Netted networks cannot be realized without equipping functional circuit elements at the connection points due to delay times and reflection effects.

- Because of the above effects, wiring can only be realized in the form of function-related ropes. In the case of a quadruple design, this means installing quadruple cables for each drive.

- This type of wiring results in heavy conductor weight when using cables with low attenuation.

Magazine "Electronique Praxis"
(“Elektronikpraxis”, Vol. 11, 1979, p. 34).
to control aircraft or industrial processes;
The introduction of this conductor is already known. A data bus, in a narrow sense, is a conductor that transmits information, and all related parts are connected to this conductor.
With the above information, this type of system can be configured as either a star bus or a T-shaped bus. In the case of a star bus, all relevant connection conductors are concentrated in the star coupler. In the case of a T-bus, each associated part is connected to the data bus via a T-coupler. Regarding the application of light guides to aircraft control, for example, advantages in terms of weight and tolerance can be expected, but both the star bus design concept and the T-shaped bus design concept require that each relevant part is connected via only one conductor. The disadvantage is that it is connected to the rest of the system. Therefore, a failure of this conductor results in a failure of the functions of the related parts involved. In aircraft operations, this means that if the corresponding conductor fails, −
The lack of use of the third component means that, for example, due to a local failure, the control function may fail, potentially fatally.

[Problem of invention]

It is therefore an object of the invention to provide a device for transmitting control signals for aircraft that operates without delay effects, reflections and disturbances due to electromagnetic disturbance fields and that, in the event of damage to a control element, a new pre-programmed The object of the present invention is to provide a passive conductor network for performing control.

[Means to solve problems]

The above problem can be solved by the present invention, the light guide 11,
The problem is solved by an aircraft control signal transmission device in which 12 circuits are multiplexed in a mesh to form one network.

Other advantageous developments of the invention are given in the remaining claims.

[Action and effect]

With the device according to the invention, mechanical, hydraulic,
Significantly improved reliability against failures is achieved compared to electrical or combined solutions. Furthermore, the invention allows the control vane to perform new tilt combinations under certain critical conditions. Therefore, even if the rudder fails, the maneuverability of the aircraft can be ensured.

The embodiment according to claim 11 is particularly advantageous. This configuration improves the energy supply of the device to the same level as the remaining components with respect to the degree of reliability of the device.

〔Example〕

The present invention will be explained in detail below based on schematic diagrams.

In FIG. 1, a control signal transmission device for an aircraft F is shown. This aircraft F has conventional control wings: two elevators 1, 1', one rudder 2, two slow ailerons 3, 3', and two rapid ailerons 4, 4'. , takeoff and landing flaps 5, 5', leading edge flaps 6, 6', and a tail fin 7. Among them, the aircraft F is provided with drive devices 8, 8' and a control function section 9. In this case, the control stick 9a and pedals are shown in this schematic diagram. The transmission system for transmitting the control signals mainly includes a multiplex network of light guides formed from a plurality of signal processors 10, dielectrics 11 and horizontal conductors 12. This circuit network is
It is connected to an addressable servo unit 14. In this case, the connection point 13 is formed from a known branch, for example in the form of a star-shaped or T-shaped coupler. The steering function section 9 is configured to output a digital optical signal corresponding to a steering command.
Servo unit 14 arranged around this circuit network
activates a device that converts the input optical signal into a controlled movement. Furthermore, this unit has a device for detecting, for example, the instantaneous position of the control vane and outputting a corresponding optical signal to the longitudinal conductor 11. Data communication between the signal processor 10 and peripheral devices connected via the vertical conductor 11 takes place periodically. That is, the signal processor 10 outputs an addressed information signal to, for example, the servo unit 14 at a constant interrogation period. This servo unit responds with an information signal that again addresses the above signal. The data communication performed here is specified by a message with a certain word length. These telegrams are digitally frequency modulated and placed on a carrier frequency. In that case, the optical signal is finally subjected to amplitude modulation according to the carrier frequency. Therefore, very high reliability against external intrusion light can be obtained. Since the transmission path is mesh-like, the signal follows many paths from the signal processor 10 to the servo unit 14, further improving the reliability of the system. The illustrated system is constructed in triplicate. That is, three vertical conductors 11 having corresponding horizontal conductors 12 are arranged on the fuselage, main wing, and page wing, and the rudder,
There are three servo units 14 per control wing, etc. Signal processor 10 contains the main control circuitry for the entire device. This unit is also configured in three layers to improve reliability.

FIG. 2 shows a mixer 15 and three information systems 16,
The circuitry of signal processor 10, consisting of 17 and 18, is shown. Via a triple light guide 19, the mixer 15 is connected to a primary light guide network 20. The three outputs of the mixer 15 are each connected to one of the information units 16-18. Furthermore, each unit 16-18 has three connecting light conductors 16a-18a, which are connected to a network 24 consisting of longitudinal conductors 11 and transverse conductors 12. The mixer 15 has the task of processing a digital optical signal input from, for example, a control stick, logically evaluating other information, and further transmitting the optical signal to the information systems 16-18. For example, when a signal corresponding to a predetermined target altitude and a signal corresponding to the measured altitude output from the altimeter 22 are introduced into the mixer 15, the mixer 1
5 forms a difference signal used to set the target altitude and inputs this difference signal to the circuitry 24 via information systems 16-18. Elevator servo unit
Receives the message addressed to 14.01 from this unit, translates the rudder tilt accordingly, and returns the aircraft to the desired flight altitude without pilot intervention. Similarly, the route/actual measurement value output from the aircraft device 23 is compared with a predetermined route/target value by the mixer 15. The difference signal generated at this time is converted into a control command addressing the servo units 14.03 and 14.04 of the aileron 2 in the servo unit 14.02 of the aileron 2, and is transmitted via the information systems 16 to 18 and further via the circuit network 24. is introduced into the servo unit. These servo units respond with an aileron tilt that provides the necessary course correction. A display/operation device (not shown) connected to the mixer 15 via the primary network 20 is used to graphically display the frequent values and actual values using regular symbols. When this device is switched to manual operation, the mixer no longer compares the nominal value and the actual value.
Control commands input via the primary circuit 20 are converted into corresponding telegrams and introduced into the servo unit. A control function section 9 that outputs control commands, such as a control stick, pedals, control wheels, etc., is connected to the primary circuit 20 via a triple light guide. In the above sequence, the mission of the information systems 16-18 is to control the conventional data communication within the mixer 15 at regular intervals and to prepare addressed commands or interrogation telegrams accordingly.

FIG. 3 shows a principle diagram of a photoelectric device 25 for sensing the position of the control stick 9a, which functions as a signal generator. This device mainly uses a light receiving diode 2.
It consists of an arc-shaped fixed part 25a with diodes 6 disposed inside thereof, and these diodes are connected to the input ends of the encoding matrix 27, respectively. Fixed part 2
5a, a segment portion 29 that rotates around a fixed point 28 is disposed on the inner side thereof, facing each other, and this fixed point 28 coincides with the center of the inner contour of the fixed portion 25a, and a portion of the rotating portion 29 The area is fixed part 25
Together with a, it forms an arc-shaped gap having a center 28. Light emitting diodes 30 are arranged on the arc-shaped edge surface of the rotating part 29, and the light emitted from these diodes is directly received by the diode 26. The light emitting diode 30 is connected to a switching matrix 31 which is supplied with current from the onboard circuitry. However, three buffer batteries 32, 33, and 34 are provided. The switching matrix 31 outputs electrical pulses in a predetermined pattern, which causes the light emitting diodes 30 to emit constant digital light pulses. Movable part 29
is connected to the control stick so as to maintain a constant relationship and follow the movement of the control stick 9a. in this case,
The light receiving diode 26 receives a received signal corresponding to each position of the control stick. This optical signal is converted into a digital optical signal by the encoding matrix 27,
Interrogated continuously by mixer 15. If the diode power supply dependent on the onboard circuitry fails, the corresponding energy is transferred to the buffer battery 3.
Supplied from 2 to 34. If more diodes are installed per unit of curvature, the signal generator will operate with higher accuracy. If the movable part 29 is driven by a conversion gear of the common type, the accuracy will be further improved. Due to the logic circuit, even if three light emitting diodes 30 fail during operation, the reading by the encoding matrix will still be accurate. According to the present invention, other control functions such as pedals, control theory, etc. can also be equipped with the photoelectric device 25 of the above type. Interchanging the light emitting and light receiving diodes provides other variations of the optoelectronic device 25.

A block diagram of the force simulator 35 is shown in FIG. Devices of this type for simulating rudder forces are known per se and are often
It is based on a truly complex mechanical transmission system. The device shown here operates electromagnetically and is controlled via a light guide. force simulator 35
It mainly consists of a control unit 36, an electronic simulator unit 37, and an electric motor 38. Said mixer 15 outputs a signal corresponding to the addressed flight speed to the force simulator 35 via the light guide. These signals are selectively received by the control unit 36 and sent to the electronic simulator unit 3 as electrical digital signals.
7 will be further introduced. The simulator unit outputs a predetermined electrical power to the motor 38 as a function of flight speed and rudder tilt based on fixedly programmed functional equations for the aircraft. This motor generates a corresponding torque at rest via shaft 38a.
M _d , and this torque acts, for example, directly on the control stick 9a and corresponds well to the rudder force, giving a perceivable force to the pilot. Based on the program stored in the simulator unit 37, when the control stick 9a passes the neutral position, the direction of the torque is reversed. The signal input to the mixer 15 depending on the flight speed is guided via an analog-to-digital converter, for example by the measurement result of a pitot tube (not shown), and converted into a digital optical signal via an addressable control device as a primary signal. Supplied to circuit 20.

In FIG. 5, three central processing units 41, 4
The internal circuit of the mixer 15 is shown with two connection units 39, 40, together with 2, 43, each associated with one control stick 9a. These arithmetic units each have one memory 44, 4
5, 46 are arranged. Furthermore, the mixer 15 has connection units (not shown) for each function for outputting control commands. The mixer 15 also includes vertical reference circuits 47, 48, 49 per memory.
and horizontal reference circuits 50, 51, and 52. A light guide is used to connect the control stick 9a and the force simulator 35. The individual functional units of the mixer 15 are connected to one another by electrical conductors in accordance with FIG. Connections to the information systems 16 to 18 are likewise made via electrical conductors. For example, the encoded signal output from the control stick 9a reaches the connection unit 39, which mainly consists of an amplifier and a code converter. Here, the signal is amplified or encoded, and the central processing unit 41, 42, 43
The data bus inside the mixer is connected to the mixer. The priority circuit in the connection unit connects the control stick 9a signal to the control stick and controls the control stick as long as the priority is maintained until manual activation. In the memories 44, 45, 46, the reference circuit 47
The data corresponding to the actual measured position of the aircraft outputted from ~49 and 50~52 is stored, and the calculation unit 4
1 to 43 to compare with each other. In this case, data that is consistent among a large number of arithmetic processing units 41 to 43 is recognized as correct. Arithmetic units with out-of-order information are considered to be in error and are blocked via the data bus inside the mixer. The above operations are performed by means of a special error code signal. The calculation units 41 to 43 are also units that perform operations necessary for the above-mentioned automatic flight control. Corresponding processors are known, for example, under the designation PDP11/70.
Corresponding to FIG. 1, the entire device uses three signal processors 10 and three mixers 15, which improves reliability.

FIG. 6 shows the triple-configured information units 16, 17, 1 shown in FIG. 2 inside the processor 10.
A block circuit diagram of a photoelectric information system in which 8 is arranged is shown. The illustrated system includes three memories 56, 57, 58, three code modulators 59,
60, 61, three demodulation decoders 62, 63, 6
4. There are three processors 53, 54, 55 having three transmitters 65, 66, 67 and three receivers 68, 69, 70 connected to each other. The main parts of transmitters 65-67 are each a laser diode that outputs an optical signal to network 24. The receivers are each formed essentially from one silicon phototransistor, which transistor serves as a light-receiving element for the optical signal input via the network 24 and converts the optical signal back into an electrical signal. The illustrated information system consists of three branches operating in parallel circuits to improve reliability. To explain the operation, first, only the left branch, that is, the memory 56, code modulator 59, demodulator decoder 62,
Processor 53 with transmitter 65 and receiver 68
Consider a branch consisting of . This circuit consists of network 24
The oscillator in processor 53 functions as a clock generator. The electrical signal reaching processor 53 from mixer 15 is introduced into code modulator 59 . Inside the encoding section, the data telegram is transformed from a processor-related structure to a peripheral-related language and address structure. Next, this message passes through a modulation section, where the message is frequency-modulated and placed on a high-frequency carrier wave. The corresponding pure data content is then demodulated back to its original state in an intermediate stage and not placed on a constant other carrier by amplitude modulation. The signal thus generated is amplified in a transmitter 65 and supplied to a laser diode. The laser diode outputs an optical signal similar to a diode current to the network 24. In the reverse direction, the incoming optical signal via network 24 is received by receiver 68 and converted to an amplitude modulated electrical signal by an integrated phototransistor. This signal then reaches demodulator decoder 62. At the output end of this demodulation signal generator there is a data telegram having a structure related to the processor, and this telegram is again subjected to arithmetic processing by the processor 53.
The other two branches of the system perform the same operation with the same period, and synchronization pulses are output from the clock oscillator of processor 53. If this clock oscillator fails, the left branch shown will automatically shut down and the adjacent clock oscillator will take control of the synchronization. Information systems 17 and 18 in FIG. 2 are normally synchronized by processor 53. Information systems 17 and 18 in FIG. The corresponding synchronization pulse is
It is output via 4.

FIG. 7 shows a block circuit diagram of a servo unit 14 for operating the elevator 1, which has mechanical and electrical parts, for example. The mechanical part mainly consists of a drive cylinder 71, a connecting rod 72 and two servo valves 73. The electronic part includes two servo amplifiers 79 and 80, a processor unit 81, a modulator 82, a demodulator 83, a transmitter 84, a receiver 85,
There is a position transducer 88, a memory 78 and a power source 88. These are connected to each other. These functional units are preferably formed primarily of integrated circuits and are arranged in an electronics compartment in the case of the drive cylinder 71. In this way, the drive cylinder 71 equipped with electronic parts forms a new type of integrated servo unit 14 which, in addition to hydraulic pressurization conduits 74, 75 and return conduits 76, 77, There is a connection terminal 89 for supplying current and two light conductor connection terminals 90, 91.
Input via light guide 11 and information system 16,1
The optical signals addressed to the drive cylinder 71 from 7, 18 are converted into electrical signals by the receiver 85 and introduced into the demodulator 83. The demodulator is
A processor unit 81 extracts the original data telegram from this signal and controls the built-in decoder.
Enter this message into . The decoder converts the telegram into a unique interrogation cycle and connects it to the internal data bus. The memory 87 stores various possible operating programs for the drive cylinder 71. Servo valve 7
Based on this telegram, a certain program is recalled from the memory 87 in order to control the servo amplifiers 79 and 80 which electrically control the servo amplifiers 79 and 80. This valve controls the inflow and outflow of hydraulic fluid so that the connecting rod 72 provides initiation of movement consistent with the program called into the elevator 1 (not shown). Memory 87 can be formed as a semiconductor or magnetic valve memory. The addressable program is stored as a function that provides rapid, slow, linear, and non-linear rudder tilt. The stored functions can satisfy various control conditions. For example, the rudder tilt can be matched to the individual flight speed. Furthermore, it is equipped with a predetermined emergency program to compensate for important rudder failures. For example, a failure in aileron 3 can be counterbalanced by giving the elevator an asymmetric tilt, or a failure in rudder 2 can be balanced by tilting the aileron 3 and 4 or 3' and 4' on the inside of the intended bend. It is also conceivable to achieve equilibrium by tilting. Another novel possibility based on the invention is that, for example, a unilateral crosswind acting on the main wing is compensated for by sharply tilting the unilateral aileron. In response, the aileron closest to the point where the load is applied is activated. An effect of this kind is introduced, for example, by the signals of accelerometers of the conventional type mounted on the wings. The above examples only show the advantageous effects of this device in the case of corresponding programs. The drive generator 78 outputs a signal corresponding to each position of the connecting rod 72 to a position converter 86, which is an analog-to-digital converter. The signal output from this converter is
It is input to processor unit 81, where it is used to control the program executed by this unit. Furthermore, the data telegrams corresponding to each interrogation are sequentially sent to the modulator 82, the transmitter 84 and the light guide 11,
via 12 to information systems 16, 17, and 18,
Controls the operation of the servo unit 14.

According to the above, the memory 87 contains various operating programs to be carried out by the drive cylinder 71 (or, for example, an electric servo motor) and at the same time corresponds to the signal output from the position detector, ie the drive generator 78. It is used to monitor cylinders based on This type of memory is also called an "intelligent memory." The processor unit 81 is a well-known device, Intel's 8080.
can be used.

A block circuit diagram of the display and operating device 92 is shown in FIG. This device includes an arithmetic unit 9
3. Electronic image unit 94, image screen 9
5. Keyboard 95a, encoder 96, transmitter 9
7. There is a decoder 98 and a receiver 99. transmitter 97
and receiver 99 are connected to primary network 20 via a light guide.
It is connected to the. For example, through an alphanumeric keyboard 95a that operates based on ASCI code (American standard code for information interchange),
Operational data is input to primary circuitry 20.

For certain modes of operation, selection keys with corresponding symbols are used. Here, the basic operating mode can be selected, for example manual control (MANOP), semi-automatic control (SEMOP) or automatic control (AUTOP). In this case, the arithmetic unit has key 9.
The task is to process the signal in such a way that the output signal of 5a reaches the mixer 15 via an encoder 96 and a transmitter 97 via a light pipe in the form of an interrogated data telegram. Screen 95 is connected to arithmetic unit 93 via electronic image unit 94. Image unit 94 includes a signal generator and transcoding matrix such as those used for conventional image display. This kind of circuit is known from Klein,
“Mikrocomputersysteme”, Francis Verlag,
Munchen, 1979, 2 Auf.S.32. The screen 95 is formed as a semiconductor image screen and is for displaying the actual position of the aircraft F.
and used to display the control corrections made. The signal generator of the image unit 94 is used here to create alphanumeric symbols in ASCI code for the process of symbolically representing position and route information. The transcoding matrix controls the point matrix field of the image screen 95, thus converting the digital signal within the code of the signal generator into a corresponding representation. The overall arrangement can use three of the display and operation devices 92. In this case, the displayed figures and the operating procedures performed are usually completely different due to the different missions of the respective operators. Even in this case, the illustrated circuit can be programmed and modified accordingly.

FIG. 9 shows a block circuit diagram of an interaction device 100 in which the useful construction of this device occurs.
This dialogue device 100 is composed of a conversation analysis unit 101 connected to a microphone, and a conversation/synthesis device 102 connected to a speaker. The dialogue device 100 is the display operation device 9 in FIG.
It communicates with the arithmetic unit 93 of No. 2 and allows the operator to interact with the device. In this case, a code word inputted in language via a microphone is recognized by a language analysis unit on the basis of the syllable evaluation stored in this unit, and is input into the calculation unit 93 in the form of a corresponding digital telegram. This is the so-called
This can be done using a PROM language decoder (PROM = Program Read Only Memory). Conversely, important information can be output to the operator via the speaker. In this case, language synthesis is performed within unit 102.
This is done by a PROM language decoder. The language decoder decodes the telegram output from the arithmetic unit 93, synthesizes it into a corresponding output language based on the stored syllable evaluation, and outputs this audio frequency signal to the speaker via an output amplifier (not shown). . Language encoders or decoders of this kind are known per se, for example in the magazine "Electronique"
(Elektronik) 1980, vol. 14, p. 54 onwards, as an application example.

In the device body described above, a significant improvement in reliability can be achieved by applying the photoconductor technology according to the present invention, digital technology based on a microprocessor, and automatic recognition and removal of defects using a logic circuit. If this device is powered by a conventional energy supply, the reliability achieved is significantly reduced. Therefore, according to the idea of the invention, the energy supply of the device is carried out by an equivalent energy supply device.

FIG. 10 accordingly shows the basic circuit of the energy supply device. The aircraft-side equipment that transmits the control signals is powered by four different energy sources. That is, the energy source is the aircraft drive unit 8, the auxiliary turbine 112, the battery 128, or the antegrade turbine 120.

Inside the engine nacelle 103 is a generator 10.
4 and a hydraulic pump 105 are connected to the shaft of the drive device. The hydraulic supply of the servo unit 14.09 or 14.10 takes place via a pressure line 107 and a return line 108. The electrical output of the generator 104 is connected to the pressure conduit 107 in such a way that the metal tube of the pressure conduit 107 is simultaneously used as an electrical energy conductor.
The opposite electrode of the generator is connected to the ground line. The measuring and switching unit 106 connects the generator 104 and the pump 105 on the one hand to the network 24 via three transmission units 110 connected in parallel on the other hand.
It is connected to. The auxiliary turbine 112 is connected to a separate generator 113 and a separate hydraulic pump 114 . The input end of the generator 113 is connected via a line 117 to a pressurizing line 118, so that here too the pressurizing line 118 is simultaneously used as an electrical energy line. The return takes place via the conductor 116. Electrical return is via the ground line. The measuring and switching unit 115 on the one hand controls the auxiliary turbine 112, the generator 113 and the pump 114.
On the other hand, it is connected to the network 24 via a transmission unit 110. An (onboard) battery 128 can be used as a separate energy source. This battery 128 supplies power to an electric motor 129 connected to a hydraulic pump 130. The battery conductor 133 is again connected to the pressurized conduit 132,
This is also used as a power supply wire. Electrical return is via the ground line.
Hydraulic pressure return is via conduit 134. Measuring and switching unit 131 is connected on the one hand to electric motor 129, pump 130 and switch 136, and on the other hand to network 24 via transmission unit 110. As another energy source, antegrade turbine 120
is provided, and this is a gathering device 119 in relative wind.
It can also be driven by the forward motor 123. The collecting device 119 consists of a generator 121 and a hydraulic pump 122, and the output conductor 126 of the generator is connected to the pressurized conduit 12.
5, and this conduit also serves as a power supply conductor. Hydraulic pressure return is via conduit 127. Electricity return is via the Graland line.

The inspection unit 135 arranged at an arbitrary position is
Since it is connected to a fiber optic network 24, this network communicates digitally with the measuring and switching unit. During normal, undisturbed operation, the electrical and hydraulic power source is a generator 104 located within the nacelle 103.
and is supplied by the pump 105. In this case, the test unit 135 interrogates current representative operating data of the generator and pump, such as electricity, temperature, pressure, etc., via a digital telegram addressed to the measuring and switching unit 106 . It is compared with the specified value stored in . If a drive fails, this failure is immediately recognized by the inspection unit and, according to the memorized priority list,
The nearest next energy source, for example an auxiliary turbine, is connected. The digital optical signal addressed to the measuring and switching unit 115 reaches the transmission unit 110 via the network 24, is converted into an electrical signal, is identified and, as a result of the correct address, is introduced further into the measuring and switching unit 115. be done. This unit connects to the auxiliary turbine via the received telegram and returns the corresponding operating data to the inspection unit 135 via interrogation. If the auxiliary turbine fails, this is immediately identified by the inspection unit 135 and, for example, the antegrade turbine 120 is connected as the closest energy source. Inspection unit 1
The corresponding signal output from 35 reaches the measuring and switching unit 124 via the network 24 and the transmission unit 110, which starts the corresponding switching process. If antegrade turbine 120 fails, battery 128 is similarly utilized as an energy source. For example, taking into account the relatively high power consumption of the control unit, the supply of power to the main systems of the aircraft can only be guaranteed for a short time with this battery. However, it should be noted that these few minutes are critical. In this type of device, the 24V battery voltage is naturally converted to the normal power supply voltage of 115V/400Hz by a converter (not shown). In multi-engine aircraft, every engine is equipped with a generator and pump. Here, if a drive 8 fails, the other drive 48 is first used for powering the control device before the auxiliary turbine 112 is connected.

FIG. 11 shows the inspection unit 135 of FIG.
The internal principle circuit of is shown. This unit is
Three central processing units 137, 138 and 139 with storage 140, 141, 142 respectively
Consists of. Central processing unit 137, 138 and 1
39 are photoelectric information systems 147, 148 and 1, respectively.
49 to the network 24. two pieces
MP (microprocessor) selector 145, 14
6 is connected to the arithmetic units 137, 138, 139 via a common data conductor 151. An external storage 150 for warning data can be connected to the arithmetic unit 137, for example. Photoelectric information system 147,
148 and 149 are connected to the network 24, so that the test unit 135 can communicate data with all functional units of the entire system connected to the network 24. Inspection unit 135 operates as follows. Three calculation units 137, 138, 139
is monitored by two MP selectors 143 and 144,
At this time, the MP selector 143 normally selects the
37, it operates as an interrogation period determination circuit. MP selector 1 of all calculation units 137 to 139
43 receives simultaneous interrogation cycles, the test unit is normal. If the interrogation period of one arithmetic unit does not match the interrogation period of the other two arithmetic units, this arithmetic unit is cut off via the two MP selectors 143,144. These MP selectors 143 and 144 mutually check the same information state. In this case, if a mismatch occurs,
One of the sequential computing units takes over the testing of the MP selectors until one of both selectors is shut off as defective. This ensures that the internal reliability of test unit 135 is higher than the individual reliability of the individual circuits to be tested.
The test unit 135 interrogates each functional unit of the energy supply device with the key address associated with this unit. Based on this, the responding unit outputs the addressed data telegram to the inspection unit 135. This telegram contains encoded operating data and also contains the address of this unit. Inside the inspection unit, the identified data is analyzed by an analysis program.
It is compared with set values stored in the memories 140, 141, and 142. In this way, you can find out whether the unit in question is normal. When this unit is abnormal, it is disconnected from the inspection unit 135 and connected to the unit that takes over the function subsequent to the list. The corresponding switching command reaches the unit in the form of an addressed digital phototelegram. In this case, data communication to and from the inspection unit 135 is controlled by photoelectric information systems 147, 148, and 149 at regular intervals. A corresponding address for the command message or the challenge message is prepared via the above-mentioned system.

FIG. 12 shows a circuit diagram of the internal principle of the measuring and switching unit 115 of FIG. This unit includes an A/D converter 152 and a switching unit 15.
Consists of 7. It is advantageous here that the transmission unit 110 with its internal circuitry is also shown. This transmission unit includes an encoder 153, a transmitter 154,
It consists of a receiver 155 and a decoder 156, which are interconnected as shown in the circuit diagram. The mode of operation of the measuring and switching unit 115 will be explained using the example of the auxiliary turbine 112. When the auxiliary turbine 112 is in operation, a sensor 158 measures, for example, the output voltage of the generator 113 and inputs it to the A/D converter 152 in the form of a corresponding analog signal. This converter creates a corresponding digital signal and sends it to encoder 153. The encoder 153 assigns the address of the inspection unit 135 to the signal and further transmits the telegram, which is now sufficient in content, to the transmitter 154. When the corresponding addressed message of the inspection unit 135 is input via the receiver 155 and the decoder 156, this message is sent to the transmitter 15 by the horizontal coupling 160.
Guaranteed to only send to 4. Transmitter 154 and receiver 155 are connected to network 24 via optical conductors 161 and 162 and communicate corresponding telegrams in the form of digital optical signals. Other quantities such as turbine speed, generator current, oil pressure can also be measured by means of further sensors, and this test unit 1
It can be sent to 35. When a defect in the auxiliary turbine is detected by the inspection unit 135, a telegram addressed to the switching unit 157 via the network 24 arrives via the receiver 155 together with a shutdown command, and this telegram is sent to the switching unit 157 using the decoder 156. to identify and read. Based on this, the decoder sends a corresponding signal to the switching unit 157. Depending on the content of the message, the switching unit 157 switches the auxiliary turbine 11
2. Disconnect all operational connections of the aircraft with generator 113 and pump 114. In this case, for example, a switch 159 that shuts off the generator 113 may be installed.

FIG. 13 shows a network analyzer 163 connected to a portion of the optical fiber network 24. In FIG. The analyzer has a number of optical fiber output ends 164 and input ends 165, respectively. To test the light guide 167, a coupling point 168 is connected via a test conductor 166 to one of the optical fiber output ends 164. Furthermore, the coupling point 169 is connected via a further test conductor 170 to one of the optical fiber input ends 165.
The optical signal emitted from the network analyzer 163 and introduced into the coupling point 168 causes the optical signal to exit the coupling point 169,
It is checked whether the optical signal introduced into the circuit analyzer via the test conductor 170 corresponds to a normal or abnormal optical conductor. This includes the fact that the network 24 has a very low attenuation for the operating signal but a large attenuation for the test signal, and that a reliably measurable attenuation is introduced from one coupling point to the other. must occur in the conductor. Disturbing effects of neighboring conductors introduced via other coupling points can thus be eliminated. Different attenuations of the network 24 for the operating and test signals can be achieved, for example, by using different colors for both signaling types, red for the operating signal and green for the test signal. If necessary, the color dependence of the attenuation of the network can be improved by coloring the material of the light guide.

FIG. 14 shows the circuit network analyzer 163 of FIG.
The internal principle circuit diagram is shown. Circuit network analyzer 1
63 is a modulator 172 and a transmission switching circuit 17.
3 and a transmitter 174, and on the other hand a demodulator 175, a reception switching circuit 176, and a receiver 177, which are connected to the optical fiber network 24. Transmission switching circuit 17
There is a horizontal conductor between the receiver switching circuit 176 and the receiver switching circuit 176, and the side of this conductor is connected to the microprocessor 171. Transmitter 174 has the same number of fiber optic outputs that connect the coupling points to transmitter 174. A laser diode that emits green light is attached to the output end. Correspondingly, the receiver 177 also has the same number of fiber optic inputs that the coupling points connect to the receiver. As receiving element, a photodiode or a phototransistor is provided here which operates only in the color range of the test signal.
To test the circuit network 24, a predetermined laser diode is connected by a transmission switching circuit 173 under the control of a microprocessor 171, and amplitude modulation of a constant frequency and amplitude is applied to the light from the diode. In this case, a corresponding modulating diode current is output by modulator 172. This optical signal is connected to a laser diode (see Figure 13). At the same time, the same receiving element is connected to the demodulator 175 by the receiving switching circuit 176.
Said receiving element belongs to the straight light guide 167 to be tested. In this case, this receiving element converts the optical signal into a corresponding electrical signal. Inside the demodulator 175, the modulated signal is restored from the electrical signal and supplied to an A/D converter (not shown). This converter is
A digital signal corresponding to the signal voltage is output to the microprocessor 171. This processor stores the voltage measured on the branch associated with network 24 (light guide 167) and compares this voltage value with a similarly stored target value for the branch. Since the test signal and the modulation maintain their amplitudes constant, a difference between the target and actual values occurs only when there is a defect in the test branch of network 24. Microprocessor 171 controls all switching processes performed by transmission switching circuit 173 and reception switching circuit 176. In this case, this processor defines individual test circuits for all branches of the network 24 according to an internal program and sends data corresponding to the individual states of the network 24 to one of the calculation units of the test unit 135. To increase reliability, three network analyzers 163 can be connected in parallel. Therefore, the connection end corresponding to the position 178 is connected to each one of the arithmetic units 137 and 137 of the inspection unit 135, respectively.
138, 139 must be connected. Advantageously, the network analyzer is formed as an internal component of test unit 135.

In the case of the above-described arrangement, the optical signals communicated via the network of light guides 20 and 24 are not limited to the modulation scheme described, but rather can be pulse-frequency modulated, depending on the conditions of use. Other modulation schemes are also possible, such as (PFM) or pulse code modulation (PCM).

The monitoring and control of the present invention by the inspection unit 135, which communicates digitally using the measuring and switching units 115, 131, 124, is not limited to the illustrated energy supply device, but can also be applied to, for example, a device that transmits control signals to peripheral units. Expandable for equipped aircraft. In particular, in connection with individual emergencies, for example in the case of a rudder failure, the inspection unit 1
35 memory special emergency programs are available. The greatest significance of this invention is that it can be applied to equipment and systems that require extremely high reliability. This includes, for example, the control of spacecraft, the process control of nuclear power plants, the power supply equipment for hospitals, in particular operating rooms or intensive care units.

[Brief explanation of drawings]

FIG. 1 is an external view of an aircraft device according to the present invention. FIG. 2 is a circuit diagram of the main control circuit. FIG. 3 is a schematic diagram of an optical device for scanning the position of the control stick. Fourth
The figure is a block circuit diagram of force simulation. FIG. 5 is a circuit diagram of the mixing unit. FIG. 6 is a block circuit diagram of a photoelectric information system. FIG. 7 is a block circuit diagram of the servo unit. FIG. 8 is a schematic diagram of the display/operation device. FIG. 9 is a block circuit diagram of the dialogue device. FIG. 10 is an internal principle circuit diagram of the energy supply device according to the present invention. FIG. 11 is an internal principle circuit diagram of the inspection unit shown in FIG. 10. Figure 12 shows the first
0 is an internal principle circuit diagram of the measurement/switching unit and transmission unit shown in FIG. FIG. 13 is a schematic diagram of a circuit network analyzer to which a part of the circuit network is attached. Figure 14 shows the first
The internal principle circuit diagram of the circuit network analyzer shown in Figure 3. Reference symbols in the figure: 1, 2, 3, 4, 5... control wing, 9... control function, 10... signal processor,
11, 12... light guide, 14... servo unit, 15... mixer, 16, 17, 18... information system, 24... circuit network.

Claims (1)

[Claims] 1. Equipped with a passive conductor system formed from a branched optical conductor to which a control function unit that transmits digital optical signals and generates control commands and a servo unit that operates the control blades are connected. A control signal transmission device for an aircraft that processes and transmits digital control signals, characterized in that the light guides 11 and 12 form one network multiplexed in a mesh pattern. 2. The device according to claim 1, wherein the control blades 1, 2, 3, 4, 5 are controlled and operated by an intelligent memory 87 and an arithmetic unit 81 in the servo unit 14. 3. The servo unit 14 includes a position detector 78 that outputs a signal corresponding to the current movement position of the control blades 1, 2, 3, 4, 5 in response to an interrogation signal. The device according to scope 1. 4. Claim 1, characterized in that a primary circuit network 20 on the cockpit side formed in a mesh shape with light guides is provided for signal communication between the control function section 9 and the mixer 15. The device according to any one of items 1 to 3. 5 The control function section 9 includes a photoelectric device 25 that scans the position, and a light emitting diode 30 disposed on the movable section 29 and a light receiving element 26 disposed on the fixed section 25a face each other or in opposite directions across the sky. The device according to any one of claims 1 to 4, characterized in that it is installed in a. 6 The control stick 9a is equipped with a force simulator 3 that can be addressed using an electric simulator unit 37.
5, the support of the electric motor 38 is fixed to the frame of the control stick, and the shaft 38a of this motor is fixed to the control stick itself. Claim 1
The device according to any one of items 1 to 5. 7. Any one of claims 1 to 6, characterized in that at least one display and operating unit 92 connected to the mixer via the primary network 20 has a screen 95 and a keyboard 95a. The device according to item 1. 8. The display/operation unit 92 is connected to an interaction device 100 having a language analysis unit 101 and a language synthesis unit 102. Device. 9. Claims characterized in that each of the information systems 16, 17, and 18 includes at least one memory 56, processor 53, code modulator 59, decoder/demodulator 62, transmitter 65, and receiver 68. The device according to paragraph 1. 10 All light guides, signal processors 10, mixers 1 installed in the network 24 and the primary network 20
5. Claim 1, characterized in that the information systems 16, 17, and 18 are all arranged in triple parallel.
9. The device according to any one of items 9 to 9. 11 The energy supply of the device is carried out using individual energy sources 8, 112, 120, 128 equipped with measuring and switching units 106, 115, 124, 131, said measuring and switching units being connected to three parallel transmission units 110. Claims 1 to 1 are characterized in that they are connected to the circuit network 24 via the circuit network and to the inspection unit 135 via this circuit network.
The device according to any one of item 0. 12. Device according to claim 11, characterized in that the energy source is an aircraft drive unit 8, an auxiliary turbine 112, a prograde turbine 120 or an electric battery 128. 13 Each transmission unit 110 includes an encoder 153,
A patent comprising a decoder 156, a transmitter 154, and a receiver 155, the encoder and the decoder are commonly connected, the encoder is connected to the transmitter, and the decoder is connected to the receiver. The apparatus according to claim 11 or 12. 14 Measurement/switching unit 106, 115, 12
4,131 is an analog-to-digital converter 152 connected to a sensor 158 and a switching unit 15
14. Device according to claim 11, characterized in that the measuring and switching unit cooperates with a transmission unit 110. 15 The inspection unit 135 includes three processor units 137, 138, 139 each having one memory 140, 141, 142, three photoelectric information systems, and two microprocessor selectors 145, 146. Any one of claims 11 to 14, characterized in that
The equipment described in section. 16. The device according to any one of claims 11 to 15, characterized in that an external storage device 150 for warning data can be connected to the inspection unit 135. 17 For the inspection unit 135, the circuit network 24
at least one network analyzer 163 for monitoring
17. The device according to any one of claims 11 to 16, characterized in that: 18 Each network analyzer 163 is connected to the test unit 1
35 one processor unit 135, 13
18. The device according to claim 15 or 17, characterized in that it is connected to a 8,139. 19. Device according to any one of claims 17 to 18, characterized in that each network analyzer 163 operates with a light signal, for example a red color, which is different from the drive signal, for example a green color. 20. Apparatus according to any one of claims 15 to 19, characterized in that the inspection unit 135 itself monitors and controls the units to which it is connected. 21. Device according to any one of claims 1 to 20, characterized in that the light guides of the network 24 are made of optical fiber conductors and are colored.