CN101916069B - 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
本发明属于航空电子技术，涉及对电传飞控模拟备份系统余度配置结构的改进。它由4个模拟备份控制律模块、4个四余度监控表决器、4个加法器和4个单刀双掷主/备转换开关组成。本发明省掉了两个两余度监控器，B通道模拟备份控制律模块[2]的输出端与B通道主/备转换开关K2的第二触点K2b连接，D通道模拟备份控制律模块[4]的输出端与D通道主/备转换开关K4的第二触点K4b连接。本发明能保证四通道能够同时工作，避免了浪费资源，提高了系统的可靠性，简化了系统结构。
The invention belongs to the avionics technology and relates to the improvement of the redundancy configuration structure of the fly-by-wire flight control simulation backup system. It consists of 4 analog backup control law modules, 4 four-redundancy monitoring voters, 4 adders and 4 single-pole double-throw main/standby transfer switches. The present invention saves two dual-redundancy monitors, the output end of the B channel analog backup control law module [2] is connected with the second contact K2b of the B channel main/standby switch K2, and the D channel analog backup control law module The output end of [4] is connected to the second contact K4b of the main/standby changeover switch K4 of the D channel. The invention can ensure that the four channels can work at the same time, avoid wasting resources, improve the reliability of the system, and simplify the system structure.
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 module 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 machine 5, B channel monitoring voting machine 6, C-channel monitoring voting machine 7 and D channel monitoring voting machine 8; 4 totalizers are respectively that A channel totalizer 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, the 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 is connected 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 respectively; The second input end 5b of A channel monitoring voting machine 5 is connected 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 respectively; The 3rd input end 5c of A channel monitoring voting machine 5 is connected 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 respectively, and the four-input terminal 5d of A channel monitoring voting machine 5 is connected with the first input end 6a of B channel monitoring voting machine 6, the second input end 7b of C-channel monitoring voting machine 7 and the 3rd input end 8c of D channel monitoring voting machine 8 respectively; 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 are participated 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 is participated 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 monitor monitors results do not participate in the control of the first, second, third and the 44 remaining voting watch-dog.Under emergent back-up job pattern; The actuator control logic circuit is controlled A channel, B passage, C-channel and D passage first, second, third and the four or four remaining voting watch-dog according to first and second liang of remaining monitor monitors results; For example first liang of remaining monitor monitors result " normally ", then the voting watch-dog operate as normal of A channel and B passage; First liang of remaining monitor monitors result " fault ", then the voting watch-dog of A channel and B passage is not participated 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 high, the simple in structure redundancy configuration structure of fly-by-wire flight control simulation backup system of resource, reliability of working simultaneously, avoid waste.
Technical scheme of the present invention is: redundancy configuration structure of fly-by-wire flight control simulation backup system; It is made up of 4 analogue back-up control law modules, 4 four remainings monitoring voting machines, 4 totalizers and 4 active/standby switches of single-pole double-throw (SPDT); 4 analogue back-up control law modules are respectively A channel analogue back-up control law module 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 machine 5, B channel monitoring voting machine 6, C-channel monitoring voting machine 7 and D channel monitoring voting machine 8; 4 totalizers are respectively that A channel totalizer 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, the 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 is connected 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 respectively; The second input end 5b of A channel monitoring voting machine 5 is connected 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 respectively; The 3rd input end 5c of A channel monitoring voting machine 5 is connected 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 respectively, and the four-input terminal 5d of A channel monitoring voting machine 5 is connected with the first input end 6a of B channel monitoring voting machine 6, the second input end 7b of C-channel monitoring voting machine 7 and the 3rd input end 8c of D channel monitoring voting machine 8 respectively; 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 first contact K2a 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 first contact K4a 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
Explain further details in the face of the present invention down.Referring to Fig. 2; Redundancy configuration structure of fly-by-wire flight control simulation backup system; It is made up of 4 analogue back-up control law modules, 4 four remainings monitoring voting machines, 4 totalizers and 4 active/standby switches of single-pole double-throw (SPDT); 4 analogue back-up control law modules are respectively A channel analogue back-up control law module 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 machine 5, B channel monitoring voting machine 6, C-channel monitoring voting machine 7 and D channel monitoring voting machine 8; 4 totalizers are respectively that A channel totalizer 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, the 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 is connected 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 respectively; The second input end 5b of A channel monitoring voting machine 5 is connected 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 respectively; The 3rd input end 5c of A channel monitoring voting machine 5 is connected 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 respectively, and the four-input terminal 5d of A channel monitoring voting machine 5 is connected with the first input end 6a of B channel monitoring voting machine 6, the second input end 7b of C-channel monitoring voting machine 7 and the 3rd input end 8c of D channel monitoring voting machine 8 respectively; 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 first contact K2a 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 first contact K4a 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 are participated 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 through 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 are participated 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 monitor monitors 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 break off the one or four remaining voting watch-dog, promptly the output signal of A channel A channel analogue back-up control law module 1 is not participated in actuator control.
Claims (1)
1. redundancy configuration structure of fly-by-wire flight control simulation backup system; It is made up of 4 analogue back-up control law modules, 4 four remainings monitoring voting machines, 4 totalizers and 4 active/standby switches of single-pole double-throw (SPDT); 4 analogue back-up control law modules are respectively A channel analogue back-up control law module [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 machine [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], and 4 active/standby switches are respectively the active/standby switch K1 of A channel, the active/standby switch K2 of B passage, the 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] is connected 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] respectively; Second input end [5b] of A channel monitoring voting machine [5] is connected 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] respectively; The 3rd input end [5c] of A channel monitoring voting machine [5] is connected 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] respectively, and the four-input terminal [5d] of A channel monitoring voting machine [5] is connected 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] respectively; 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 first contact K2a 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 first contact K4a of the active/standby switch K4 of D passage.
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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 |
| CN105204431B (en) * | 2015-08-11 | 2018-01-30 | 中国航空工业集团公司西安飞机设计研究所 | Four remaining signal monitoring means of votings and equipment |
| CN105116717B (en) * | 2015-08-11 | 2018-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Four remaining signal monitoring methods and device |
| CN105204327B (en) * | 2015-08-24 | 2017-08-29 | 北京航空航天大学 | The non-similar actuating system reliability confirmation method of aircraft based on minimal path non cross link |
| 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 | A fly-by-wire flight control system that meets airworthiness requirements |
| 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 |
| 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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