CN101916069A - Redundancy configuration structure of fly-by-wire flight control simulation backup system - Google Patents
Redundancy configuration structure of fly-by-wire flight control simulation backup system Download PDFInfo
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Abstract
The invention belongs to an avionics technology and relates to an improved redundancy configuration structure of a fly-by-wire flight control simulation backup system. The redundancy configuration structure consists of four simulation backup control law modules, four quad-redundancy monitoring voters, four summators and four single-pole double-throw host/standby change-over switches. The invention omits two double-redundancy monitors; the output end of a B channel simulation control law module (2) is connected with a second contact K2b of a B channel host/standby change-over switch K2; and the output end of a D channel simulation control law module (4) is connected with a second contact K4b of a D channel host/standby change-over switch K4. The invention can ensure that the four channels can simultaneously work, avoid the resource waste, improve the reliability of the system and simplify the structure of the system.
Description
Technical field
The invention belongs to avionics, relate to improvement redundancy configuration structure of fly-by-wire flight control simulation backup system.
Background technology
Present redundancy configuration structure of fly-by-wire flight control simulation backup system is referring to Fig. 1, and it is made up of 4 analogue back-up control law modules, 4 four remainings monitoring voting machines, 4 totalizers, 4 active/standby switches of single-pole double-throw (SPDT) and two two remaining watch-dogs.4 analogue back-up control law modules are respectively A channel analogue back-up control law modules 1, B tunnels analogy backup control law module 2, C-channel analogue back-up control law module 3 and D tunnels analogy backup control law module 4,4 four remaining monitoring voting machines are respectively A channel monitoring voting machines 5, B channel monitoring voting machine 6, C-channel monitoring voting machine 7 and D channel monitoring voting machine 8,4 totalizers are respectively A channel totalizers 9, B passage totalizer 10, C-channel totalizer 11 and 12,4 active/standby switches of D passage totalizer are respectively the active/standby switch K1 of A channel, the active/standby switch K2 of B passage, active/standby switch K3 of C-channel and the active/standby switch K4 of D passage; Two two remaining watch-dogs are first liang of remaining watch-dog 13 and second liang of remaining watch-dog 14.The first input end 5a of A channel monitoring voting machine 5 respectively with the second input end 6b of B channel monitoring voting machine 6, the 3rd input end 7c of C-channel monitoring voting machine 7 and the four-input terminal 8d of D channel monitoring voting machine 8 are connected, the second input end 5b of A channel monitoring voting machine 5 respectively with the 3rd input end 6c of B channel monitoring voting machine 6, the second input end 7d of C-channel monitoring voting machine 7 and the first input end 8a of D channel monitoring voting machine 8 are connected, the 3rd input end 5c of A channel monitoring voting machine 5 respectively with the four-input terminal 6d of B channel monitoring voting machine 6, the first input end 7a of C-channel monitoring voting machine 7 and the second input end 8b of D channel monitoring voting machine 8 are connected, the four-input terminal 5d that A channel is monitored voting machine 5 respectively with the first input end 6a of B channel monitoring voting machine 6, second input end 7b of C-channel monitoring voting machine 7 and the 3rd input end 8c of D channel monitoring voting machine 8 are connected; The output terminal 5e of A channel monitoring voting machine 5 is output terminals of A channel monitoring voting machine, the output terminal 6e of B channel monitoring voting machine 6 is output terminals of B channel monitoring voting machine, the output terminal 7e of C-channel monitoring voting machine 7 is output terminals of C-channel monitoring voting machine, and the output terminal 8e of D channel monitoring voting machine 8 is output terminals of D channel monitoring voting machine.The output terminal 9c of A channel totalizer 9 is connected with the first input end 5a of A channel monitoring voting machine 5, the second input end 9b of A channel totalizer 9 is connected with A channel rudder face feedback signal output terminal PA, and the first input end 9a of A channel totalizer 9 is connected with the common port K1c of the active/standby switch K1 of A channel; The output terminal 10c of B passage totalizer 10 is connected with the first input end 6a of B channel monitoring voting machine 6, the second input end 10b of B passage totalizer 10 is connected with B passage rudder face feedback signal output terminal PB, and the first input end 10a of B passage totalizer 10 is connected with the common port K2c of the active/standby switch K2 of B passage; The output terminal 11c of C-channel totalizer 11 is connected with the first input end 7a of C-channel monitoring voting machine 7, the second input end 11b of C-channel totalizer 11 is connected with C-channel rudder face feedback signal output terminal PC, and the first input end 11a of C-channel totalizer 11 is connected with the common port K3c of the active/standby switch K3 of C-channel; The output terminal 12c of D passage totalizer 12 is connected with the first input end 8a of D channel monitoring voting machine 8, the second input end 12b of D passage totalizer 12 is connected with D passage rudder face feedback signal output terminal PD, and the first input end 12a of D passage totalizer 12 is connected with the common port K4c of the active/standby switch K4 of D passage.The first contact K1a of the active/standby switch K1 of A channel is connected with the output terminal of A channel analogue back-up control law module 1, and the second contact K1b of the active/standby switch K1 of A channel is connected with the rudder face command signal output terminal FA of A channel flight control computer; The second contact K2b of the active/standby switch K2 of B passage is connected with the rudder face command signal output terminal FB of B passage flight control computer; The first contact K3a of the active/standby switch K3 of C-channel is connected with the output terminal of C-channel analogue back-up control law module 3, and the second contact K3b of the active/standby switch K3 of C-channel is connected with the rudder face command signal output terminal FC of C-channel flight control computer; The first contact K4a of the active/standby switch K4 of D passage is connected with the output terminal of C-channel analogue back-up control law module 3, and the second contact K4b of the active/standby switch K4 of D passage is connected with the rudder face command signal output terminal FD of D passage flight control computer.The control end K1d of the active/standby switch K1 of A channel is connected with the active/standby switching signal output terminal of A channel flight control computer, the control end K2d of the active/standby switch K2 of B passage is connected with the active/standby switching signal output terminal of B passage flight control computer, the control end of the active/standby switch K3 of C-channel is connected with the active/standby switching signal output terminal of C-channel flight control computer, and the control end K4d of the active/standby switch K4 of D passage is connected with the active/standby switching signal output terminal of D passage flight control computer.The output terminal of B tunnels analogy backup control law module 2 is connected with the second input end 13b of first liang of remaining watch-dog 13, the first input end 13a of first liang of remaining watch-dog 13 is connected with the output terminal of A channel analogue back-up control law module 1, and the output terminal of first liang of remaining watch-dog 13 is connected with the input end of A channel with B passage rudder face actuator control logic circuit; The output terminal of D tunnels analogy backup control law module 4 is connected with the second input end 14b of second liang of remaining watch-dog 14, the first input end 14a of second liang of remaining watch-dog 14 is connected with the output terminal of C-channel analogue back-up control law module 3, and the output terminal of second liang of remaining watch-dog 14 is connected with the input end of C-channel with D passage rudder face actuator control logic circuit.
The principle of work of redundancy configuration structure of fly-by-wire flight control simulation backup system shown in Figure 1 is: under the normal mode of operation, the active/standby switching signal output terminal output low level of 4 flight control computers, the common port of 4 active/standby switch K1～K4 is connected with second contact, flight control computer instruction FA, FB, FC and the FD signal of A channel, B passage, C-channel and D passage participates in the control of the actuator of A channel, B passage, C-channel and D passage, and the output signal of the analogue back-up control law module 1 of A channel and the analogue back-up control law module 3 of C-channel is disconnected.Under the emergency pattern, the active/standby switching signal output terminal output high level of 4 flight control computers, the common port of 4 active/standby switch K1～K4 is connected with first contact, the output signal of the analogue back-up control law module 1 of A channel and the analogue back-up control law module 3 of C-channel participates in the control of the actuator of A channel, B passage, C-channel and D passage, and flight control computer instruction FA, FB, FC and the FD signal of A channel, B passage, C-channel and D passage are disconnected.The first input end 13a of first liang of remaining watch-dog 13 of output signal input of the analogue back-up control law module 1 of A channel, the second input end 13b of first liang of remaining watch-dog 13 of output signal input of the analogue back-up control law module 2 of B passage, if the difference of above-mentioned two output signals is lower than the monitoring threshold value of first liang of remaining watch-dog 13, then the output signal of first liang of remaining watch-dog 13 is " normally "; If the difference of above-mentioned two output signals is higher than the monitoring threshold value of first liang of remaining watch-dog 13, then the output signal of first liang of remaining watch-dog 13 is " fault ", is somebody's turn to do " normally " or " fault " signal input A channel and B passage rudder face actuator control logic circuit and handles.Under normal mode of operation, first and second liang of remaining watch-dogs are monitored the emergent backup control law module of A channel and C-channel respectively, the monitored results of first and second liang of remaining watch-dogs is exported to the actuator control logic circuit, but first and second liang of remaining watch-dog monitored results do not participate in the control that the first, second, third and the 44 remaining is decided by vote watch-dog.Under emergent back-up job pattern, the actuator control logic circuit is according to first and second liang of remaining watch-dog monitored results control A channels, B passage, C-channel and D passages first, second, third and the four or four remaining voting watch-dog, for example first liang of remaining watch-dog monitored results " normally ", then the voting watch-dog operate as normal of A channel and B passage; First liang of remaining watch-dog monitored results " fault ", then the voting watch-dog of A channel and B passage does not participate in actuator control, and the control principle of C-channel and D passage is with A channel and B passage.
Its shortcoming is: the first, the real-time working passage has only two, and the wasting of resources is big, and the remaining degradation is fast, and reliability is low.Owing between per two remainings of analogue back-up control system, adopt two remaining watch-dogs of a special use to realize the relatively monitoring of two passages, in per two remainings, have only a passage in running order.If when in two remainings channel failure being arranged, this two remainings passage all is cut off, and causes the wasting of resources, reliability decrease.The second, need two two remaining watch-dogs, complex structure.
Summary of the invention
The objective of the invention is: propose a four-way work simultaneously, avoid waste resource, reliability height, redundancy configuration structure of fly-by-wire flight control simulation backup system simple in structure.
Technical scheme of the present invention is: redundancy configuration structure of fly-by-wire flight control simulation backup system, it is by 4 analogue back-up control law modules, 4 four remaining monitoring voting machines, 4 totalizers and 4 active/standby switches of single-pole double-throw (SPDT) are formed, 4 analogue back-up control law modules are respectively A channel analogue back-up control law modules 1, B tunnels analogy backup control law module 2, C-channel analogue back-up control law module 3 and D tunnels analogy backup control law module 4,4 four remaining monitoring voting machines are respectively A channel monitoring voting machines 5, B channel monitoring voting machine 6, C-channel monitoring voting machine 7 and D channel monitoring voting machine 8,4 totalizers are respectively A channel totalizers 9, B passage totalizer 10, C-channel totalizer 11 and 12,4 active/standby switches of D passage totalizer are respectively the active/standby switch K1 of A channel, the active/standby switch K2 of B passage, active/standby switch K3 of C-channel and the active/standby switch K4 of D passage; The first input end 5a of A channel monitoring voting machine 5 respectively with the second input end 6b of B channel monitoring voting machine 6, the 3rd input end 7c of C-channel monitoring voting machine 7 and the four-input terminal 8d of D channel monitoring voting machine 8 are connected, the second input end 5b of A channel monitoring voting machine 5 respectively with the 3rd input end 6c of B channel monitoring voting machine 6, the second input end 7d of C-channel monitoring voting machine 7 and the first input end 8a of D channel monitoring voting machine 8 are connected, the 3rd input end 5c of A channel monitoring voting machine 5 respectively with the four-input terminal 6d of B channel monitoring voting machine 6, the first input end 7a of C-channel monitoring voting machine 7 and the second input end 8b of D channel monitoring voting machine 8 are connected, the four-input terminal 5d that A channel is monitored voting machine 5 respectively with the first input end 6a of B channel monitoring voting machine 6, second input end 7b of C-channel monitoring voting machine 7 and the 3rd input end 8c of D channel monitoring voting machine 8 are connected; The output terminal 5e of A channel monitoring voting machine 5 is output terminals of A channel monitoring voting machine, the output terminal 6e of B channel monitoring voting machine 6 is output terminals of B channel monitoring voting machine, the output terminal 7e of C-channel monitoring voting machine 7 is output terminals of C-channel monitoring voting machine, and the output terminal 8e of D channel monitoring voting machine 8 is output terminals of D channel monitoring voting machine; The output terminal 9c of A channel totalizer 9 is connected with the first input end 5a of A channel monitoring voting machine 5, the second input end 9b of A channel totalizer 9 is connected with A channel rudder face feedback signal output terminal PA, and the first input end 9a of A channel totalizer 9 is connected with the common port K1c of the active/standby switch K1 of A channel; The output terminal 10c of B passage totalizer 10 is connected with the first input end 6a of B channel monitoring voting machine 6, the second input end 10b of B passage totalizer 10 is connected with B passage rudder face feedback signal output terminal PB, and the first input end 10a of B passage totalizer 10 is connected with the common port K2c of the active/standby switch K2 of B passage; The output terminal 11c of C-channel totalizer 11 is connected with the first input end 7a of C-channel monitoring voting machine 7, the second input end 11b of C-channel totalizer 11 is connected with C-channel rudder face feedback signal output terminal PC, and the first input end 11a of C-channel totalizer 11 is connected with the common port K3c of the active/standby switch K3 of C-channel; The output terminal 12c of D passage totalizer 12 is connected with the first input end 8a of D channel monitoring voting machine 8, the second input end 12b of D passage totalizer 12 is connected with D passage rudder face feedback signal output terminal PD, and the first input end 12a of D passage totalizer 12 is connected with the common port K4c of the active/standby switch K4 of D passage; The first contact K1a of the active/standby switch K1 of A channel is connected with the output terminal of A channel analogue back-up control law module 1, and the second contact K1b of the active/standby switch K1 of A channel is connected with the rudder face command signal output terminal FA of A channel flight control computer; The second contact K2b of the active/standby switch K2 of B passage is connected with the rudder face command signal output terminal FB of B passage flight control computer; The first contact K3a of the active/standby switch K3 of C-channel is connected with the output terminal of C-channel analogue back-up control law module 3, and the second contact K3b of the active/standby switch K3 of C-channel is connected with the rudder face command signal output terminal FC of C-channel flight control computer; The second contact K4b of the active/standby switch K4 of D passage is connected with the rudder face command signal output terminal FD of D passage flight control computer; The control end K1d of the active/standby switch K1 of A channel is connected with the active/standby switching signal output terminal of A channel flight control computer, the control end K2d of the active/standby switch K2 of B passage is connected with the active/standby switching signal output terminal of B passage flight control computer, the control end of the active/standby switch K3 of C-channel is connected with the active/standby switching signal output terminal of C-channel flight control computer, and the control end K4d of the active/standby switch K4 of D passage is connected with the active/standby switching signal output terminal of D passage flight control computer; It is characterized in that the output terminal of B tunnels analogy backup control law module 2 is connected with the second contact K2b of the active/standby switch K2 of B passage, the output terminal of D tunnels analogy backup control law module 4 is connected with the second contact K4b of the active/standby switch K4 of D passage.
Advantage of the present invention is: four-way can be worked simultaneously, has avoided the waste resource, has improved the reliability of system, has simplified system architecture.
Description of drawings
Fig. 1 is the structural principle block diagram of existing redundancy configuration structure of fly-by-wire flight control simulation backup system.
Fig. 2 is a structural principle block diagram of the present invention.
Embodiment
Below the present invention is described in further details.Referring to Fig. 2, redundancy configuration structure of fly-by-wire flight control simulation backup system, it is by 4 analogue back-up control law modules, 4 four remaining monitoring voting machines, 4 totalizers and 4 active/standby switches of single-pole double-throw (SPDT) are formed, 4 analogue back-up control law modules are respectively A channel analogue back-up control law modules 1, B tunnels analogy backup control law module 2, C-channel analogue back-up control law module 3 and D tunnels analogy backup control law module 4,4 four remaining monitoring voting machines are respectively A channel monitoring voting machines 5, B channel monitoring voting machine 6, C-channel monitoring voting machine 7 and D channel monitoring voting machine 8,4 totalizers are respectively A channel totalizers 9, B passage totalizer 10, C-channel totalizer 11 and 12,4 active/standby switches of D passage totalizer are respectively the active/standby switch K1 of A channel, the active/standby switch K2 of B passage, active/standby switch K3 of C-channel and the active/standby switch K4 of D passage; The first input end 5a of A channel monitoring voting machine 5 respectively with the second input end 6b of B channel monitoring voting machine 6, the 3rd input end 7c of C-channel monitoring voting machine 7 and the four-input terminal 8d of D channel monitoring voting machine 8 are connected, the second input end 5b of A channel monitoring voting machine 5 respectively with the 3rd input end 6c of B channel monitoring voting machine 6, the second input end 7d of C-channel monitoring voting machine 7 and the first input end 8a of D channel monitoring voting machine 8 are connected, the 3rd input end 5c of A channel monitoring voting machine 5 respectively with the four-input terminal 6d of B channel monitoring voting machine 6, the first input end 7a of C-channel monitoring voting machine 7 and the second input end 8b of D channel monitoring voting machine 8 are connected, the four-input terminal 5d that A channel is monitored voting machine 5 respectively with the first input end 6a of B channel monitoring voting machine 6, second input end 7b of C-channel monitoring voting machine 7 and the 3rd input end 8c of D channel monitoring voting machine 8 are connected; The output terminal 5e of A channel monitoring voting machine 5 is output terminals of A channel monitoring voting machine, the output terminal 6e of B channel monitoring voting machine 6 is output terminals of B channel monitoring voting machine, the output terminal 7e of C-channel monitoring voting machine 7 is output terminals of C-channel monitoring voting machine, and the output terminal 8e of D channel monitoring voting machine 8 is output terminals of D channel monitoring voting machine; The output terminal 9c of A channel totalizer 9 is connected with the first input end 5a of A channel monitoring voting machine 5, the second input end 9b of A channel totalizer 9 is connected with A channel rudder face feedback signal output terminal PA, and the first input end 9a of A channel totalizer 9 is connected with the common port K1c of the active/standby switch K1 of A channel; The output terminal 10c of B passage totalizer 10 is connected with the first input end 6a of B channel monitoring voting machine 6, the second input end 10b of B passage totalizer 10 is connected with B passage rudder face feedback signal output terminal PB, and the first input end 10a of B passage totalizer 10 is connected with the common port K2c of the active/standby switch K2 of B passage; The output terminal 11c of C-channel totalizer 11 is connected with the first input end 7a of C-channel monitoring voting machine 7, the second input end 11b of C-channel totalizer 11 is connected with C-channel rudder face feedback signal output terminal PC, and the first input end 11a of C-channel totalizer 11 is connected with the common port K3c of the active/standby switch K3 of C-channel; The output terminal 12c of D passage totalizer 12 is connected with the first input end 8a of D channel monitoring voting machine 8, the second input end 12b of D passage totalizer 12 is connected with D passage rudder face feedback signal output terminal PD, and the first input end 12a of D passage totalizer 12 is connected with the common port K4c of the active/standby switch K4 of D passage; The first contact K1a of the active/standby switch K1 of A channel is connected with the output terminal of A channel analogue back-up control law module 1, and the second contact K1b of the active/standby switch K1 of A channel is connected with the rudder face command signal output terminal FA of A channel flight control computer; The second contact K2b of the active/standby switch K2 of B passage is connected with the rudder face command signal output terminal FB of B passage flight control computer; The first contact K3a of the active/standby switch K3 of C-channel is connected with the output terminal of C-channel analogue back-up control law module 3, and the second contact K3b of the active/standby switch K3 of C-channel is connected with the rudder face command signal output terminal FC of C-channel flight control computer; The second contact K4b of the active/standby switch K4 of D passage is connected with the rudder face command signal output terminal FD of D passage flight control computer; The control end K1d of the active/standby switch K1 of A channel is connected with the active/standby switching signal output terminal of A channel flight control computer, the control end K2d of the active/standby switch K2 of B passage is connected with the active/standby switching signal output terminal of B passage flight control computer, the control end of the active/standby switch K3 of C-channel is connected with the active/standby switching signal output terminal of C-channel flight control computer, and the control end K4d of the active/standby switch K4 of D passage is connected with the active/standby switching signal output terminal of D passage flight control computer; It is characterized in that the output terminal of B tunnels analogy backup control law module 2 is connected with the second contact K2b of the active/standby switch K2 of B passage, the output terminal of D tunnels analogy backup control law module 4 is connected with the second contact K4b of the active/standby switch K4 of D passage.
Principle of work of the present invention is: under the normal mode of operation, the active/standby switching signal output terminal output low level of 4 flight control computers, the common port of 4 active/standby switch K1～K4 is connected with second contact, flight control computer instruction FA, FB, FC and the FD signal of A channel, B passage, C-channel and D passage participates in the control of the actuator of A channel, B passage, C-channel and D passage, and the analogue back-up control law module 1,2,3 of A channel, B passage, C-channel and D passage and 4 output signal are disconnected; At this moment, the analogue back-up control law module 1,2,3 of not monitoring A channel, B passage, C-channel and D passage of the first, second, third and the 44 remaining voting watch-dog and 4 output signal, but the airborne software of the flight control computer by A channel, B passage, C-channel and D passage is monitored the analogue back-up control law module 1,2,3 of A channel, B passage, C-channel and D passage and 4 output signal.Under the emergency pattern, the active/standby switching signal output terminal output high level of 4 flight control computers, the common port of 4 active/standby switch K1～K4 is connected with first contact, the analogue back-up control law module 1,2,3 of A channel, B passage, C-channel and D passage and 4 output signal participate in the control of the actuator of A channel, B passage, C-channel and D passage, and flight control computer instruction FA, FB, FC and the FD signal of A channel, B passage, C-channel and D passage are disconnected; At this moment, the first, second, third and the 44 remaining voting watch-dog monitoring A channel, B passage, C-channel and the analogue back-up control law module 1,2,3 of D passage and 4 output signal, the output signal " fault " of A channel analogue back-up control law module 1 for example, then disconnect the one or four remaining voting watch-dog, promptly the output signal of A channel A channel analogue back-up control law module 1 does not participate in actuator control.
Claims (1)
1. redundancy configuration structure of fly-by-wire flight control simulation backup system, it is by 4 analogue back-up control law modules, 4 four remaining monitoring voting machines, 4 totalizers and 4 active/standby switches of single-pole double-throw (SPDT) are formed, 4 analogue back-up control law modules are respectively A channel analogue back-up control law modules [1], B tunnels analogy backup control law module [2], C-channel analogue back-up control law module [3] and D tunnels analogy backup control law module [4], 4 four remaining monitoring voting machines are respectively A channel monitoring voting machines [5], B channel monitoring voting machine [6], C-channel monitoring voting machine [7] and D channel monitoring voting machine [8], 4 totalizers are respectively A channel totalizer [9], B passage totalizer [10], C-channel totalizer [11] and D passage totalizer [12], 4 active/standby switches are respectively the active/standby switch K1 of A channel, the active/standby switch K2 of B passage, active/standby switch K3 of C-channel and the active/standby switch K4 of D passage; The first input end [5a] of A channel monitoring voting machine [5] respectively with second input end [6b] of B channel monitoring voting machine [6], the 3rd input end [7c] of C-channel monitoring voting machine [7] and the four-input terminal [8d] of D channel monitoring voting machine [8] are connected, second input end [5b] of A channel monitoring voting machine [5] respectively with the 3rd input end [6c] of B channel monitoring voting machine [6], second input end [7d] of C-channel monitoring voting machine [7] and the first input end [8a] of D channel monitoring voting machine [8] are connected, the 3rd input end [5c] of A channel monitoring voting machine [5] respectively with the four-input terminal [6d] of B channel monitoring voting machine [6], the first input end [7a] of C-channel monitoring voting machine [7] and second input end [8b] of D channel monitoring voting machine [8] are connected, the four-input terminal [5d] that A channel is monitored voting machine [5] respectively with the first input end [6a] of B channel monitoring voting machine [6], second input end [7b] of C-channel monitoring voting machine [7] and the 3rd input end [8c] of D channel monitoring voting machine [8] are connected; The output terminal [5e] of A channel monitoring voting machine [5] is the output terminal of A channel monitoring voting machine, the output terminal [6e] of B channel monitoring voting machine [6] is the output terminal of B channel monitoring voting machine, the output terminal [7e] of C-channel monitoring voting machine [7] is the output terminal of C-channel monitoring voting machine, and the output terminal [8e] of D channel monitoring voting machine [8] is the output terminal of D channel monitoring voting machine; The output terminal [9c] of A channel totalizer [9] is connected with the first input end [5a] of A channel monitoring voting machine [5], second input end [9b] of A channel totalizer [9] is connected with A channel rudder face feedback signal output terminal PA, and the first input end [9a] of A channel totalizer [9] is connected with the common port K1c of the active/standby switch K1 of A channel; The output terminal [10c] of B passage totalizer [10] is connected with the first input end [6a] of B channel monitoring voting machine [6], second input end [10b] of B passage totalizer [10] is connected with B passage rudder face feedback signal output terminal PB, and the first input end [10a] of B passage totalizer [10] is connected with the common port K2c of the active/standby switch K2 of B passage; The output terminal [11c] of C-channel totalizer [11] is connected with the first input end [7a] of C-channel monitoring voting machine [7], second input end [11b] of C-channel totalizer [11] is connected with C-channel rudder face feedback signal output terminal PC, and the first input end [11a] of C-channel totalizer [11] is connected with the common port K3c of the active/standby switch K3 of C-channel; The output terminal [12c] of D passage totalizer [12] is connected with the first input end [8a] of D channel monitoring voting machine [8], second input end [12b] of D passage totalizer [12] is connected with D passage rudder face feedback signal output terminal PD, and the first input end [12a] of D passage totalizer [12] is connected with the common port K4c of the active/standby switch K4 of D passage; The first contact K1a of the active/standby switch K1 of A channel is connected with the output terminal of A channel analogue back-up control law module [1], and the second contact K1b of the active/standby switch K1 of A channel is connected with the rudder face command signal output terminal FA of A channel flight control computer; The second contact K2b of the active/standby switch K2 of B passage is connected with the rudder face command signal output terminal FB of B passage flight control computer; The first contact K3a of the active/standby switch K3 of C-channel is connected with the output terminal of C-channel analogue back-up control law module [3], and the second contact K3b of the active/standby switch K3 of C-channel is connected with the rudder face command signal output terminal FC of C-channel flight control computer; The second contact K4b of the active/standby switch K4 of D passage is connected with the rudder face command signal output terminal FD of D passage flight control computer; The control end K1d of the active/standby switch K1 of A channel is connected with the active/standby switching signal output terminal of A channel flight control computer, the control end K2d of the active/standby switch K2 of B passage is connected with the active/standby switching signal output terminal of B passage flight control computer, the control end of the active/standby switch K3 of C-channel is connected with the active/standby switching signal output terminal of C-channel flight control computer, and the control end K4d of the active/standby switch K4 of D passage is connected with the active/standby switching signal output terminal of D passage flight control computer; It is characterized in that, the output terminal of B tunnels analogy backup control law module [2] is connected with the second contact K2b of the active/standby switch K2 of B passage, and the output terminal of D tunnels analogy backup control law module [4] is connected with the second contact K4b of the active/standby switch K4 of D passage.
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| CN2010102596800A CN101916069B (en) | 2010-08-19 | 2010-08-19 | Redundancy configuration structure of fly-by-wire flight control simulation backup system |
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| CN2010102596800A CN101916069B (en) | 2010-08-19 | 2010-08-19 | Redundancy configuration structure of fly-by-wire flight control simulation backup system |
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| CN101916069B CN101916069B (en) | 2012-11-07 |
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| CN105116717A (en) * | 2015-08-11 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | Quad-redundant signal monitoring method and device |
| CN105204327A (en) * | 2015-08-24 | 2015-12-30 | 北京航空航天大学 | Airplane dissimilar redundancy hybrid actuation system reliability confirmation method based on minimal path disjoint |
| CN105204431A (en) * | 2015-08-11 | 2015-12-30 | 中国航空工业集团公司西安飞机设计研究所 | Monitoring-determining method and device for four redundancy signals |
| CN105334845A (en) * | 2015-11-25 | 2016-02-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Incidence angle redundancy management method for mechanical dual-redundancy and electrical four-redundancy |
| CN106200669A (en) * | 2015-04-29 | 2016-12-07 | 陕西飞机工业（集团）有限公司 | A kind of aircraft automatic flight control system signal source four remaining processing method |
| CN106853868A (en) * | 2015-12-08 | 2017-06-16 | 中国航空工业第六八研究所 | A kind of steering wheel of four remainings Flying by wire system starts method |
| CN111142369A (en) * | 2019-12-27 | 2020-05-12 | 中国航空工业集团公司西安飞机设计研究所 | Fly-by-wire flight control system capable of meeting airworthiness requirement |
| CN111522331A (en) * | 2020-05-20 | 2020-08-11 | 中国商用飞机有限责任公司 | Flight control system quad-redundancy signal monitoring voting method |
| CN113504720A (en) * | 2021-09-07 | 2021-10-15 | 中国商用飞机有限责任公司 | Backup control system based on distributed fly-by-wire architecture and working method |
| CN114002943A (en) * | 2021-09-30 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Architecture of backup system of telex flight control system |
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| CN106200669A (en) * | 2015-04-29 | 2016-12-07 | 陕西飞机工业（集团）有限公司 | A kind of aircraft automatic flight control system signal source four remaining processing method |
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| CN105334845A (en) * | 2015-11-25 | 2016-02-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Incidence angle redundancy management method for mechanical dual-redundancy and electrical four-redundancy |
| CN105334845B (en) * | 2015-11-25 | 2020-05-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Mechanical dual-redundancy electrical four-redundancy angle-of-attack redundancy management method |
| CN106853868A (en) * | 2015-12-08 | 2017-06-16 | 中国航空工业第六八研究所 | A kind of steering wheel of four remainings Flying by wire system starts method |
| CN111142369A (en) * | 2019-12-27 | 2020-05-12 | 中国航空工业集团公司西安飞机设计研究所 | Fly-by-wire flight control system capable of meeting airworthiness requirement |
| CN111522331A (en) * | 2020-05-20 | 2020-08-11 | 中国商用飞机有限责任公司 | Flight control system quad-redundancy signal monitoring voting method |
| CN111522331B (en) * | 2020-05-20 | 2021-05-04 | 中国商用飞机有限责任公司 | Flight control system quad-redundancy signal monitoring voting method |
| CN113504720A (en) * | 2021-09-07 | 2021-10-15 | 中国商用飞机有限责任公司 | Backup control system based on distributed fly-by-wire architecture and working method |
| CN114002943A (en) * | 2021-09-30 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Architecture of backup system of telex flight control system |
| CN114002943B (en) * | 2021-09-30 | 2024-05-24 | 中航通飞华南飞机工业有限公司 | Framework of backup system of fly-by-wire control system |
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