CN110989660A - Automatic flight control system's balancing adapter - Google Patents
Automatic flight control system's balancing adapter Download PDFInfo
- Publication number
- CN110989660A CN110989660A CN201911134495.6A CN201911134495A CN110989660A CN 110989660 A CN110989660 A CN 110989660A CN 201911134495 A CN201911134495 A CN 201911134495A CN 110989660 A CN110989660 A CN 110989660A
- Authority
- CN
- China
- Prior art keywords
- switch
- interface
- relay
- automatic
- trim
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 84
- 238000009966 trimming Methods 0.000 claims abstract description 21
- 238000010586 diagram Methods 0.000 description 8
- 238000004132 cross linking Methods 0.000 description 4
- 238000004891 communication Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Toys (AREA)
Abstract
The embodiment of the invention discloses a trim adapter of an automatic flight control system, which comprises: a first relay, a second relay and a third relay; when the first control coil receives the automatic balancing signal, the first relay conducts the first end and the third end of the first switch, the second switch and the third switch respectively; when the second control coil receives the automatic balancing forward rotation signal, the second relay conducts the first end and the third end of the fourth switch and the third end of the fifth switch respectively, and transmits a motor control signal input by the ninth interface to the second interface; and when the third control coil receives the automatic balancing reverse signal, the third relay conducts the first end and the third end of the sixth switch and the third end of the seventh switch respectively, and the motor control signal input by the ninth interface is output to the third interface. The embodiment of the invention solves the problem that automatic trimming is difficult to realize because an automatic flight control system additionally arranged on the existing airplane cannot be crosslinked with a manual trimming control system configured on the airplane.
Description
Technical Field
The present application relates to, but is not limited to, the field of automatic flight control technologies, and in particular, to a trim adapter for an automatic flight control system.
Background
The current aircraft is generally provided with a manual trim control system, and manual trim control can be realized. Based on the requirement on the control performance of the airplane, the requirement for additionally arranging an automatic flight control system on the airplane is provided.
After the automatic flight control system is additionally arranged on the airplane, the automatic flight control system is difficult to be crosslinked with a manual trim control system arranged on the airplane, so that the automatic trim function cannot be realized.
Disclosure of Invention
In order to solve the above technical problems, an embodiment of the present invention provides a trim adapter for an automatic flight control system, so as to solve a problem that automatic trimming is difficult to achieve due to the fact that an automatic flight control system installed on an existing aircraft cannot be cross-linked with a manual trim control system configured on the aircraft.
The embodiment of the invention provides a trim adapter of an automatic flight control system, which comprises: the first relay, the second relay, the third relay and a socket arranged on the balancing adapter;
the first relay comprises a first switch, a second switch, a third switch and a first control coil, first ends of the first switch, the second switch and the third switch are connected to a first interface, a second interface and a third interface of the socket in a one-to-one correspondence mode, second ends of the first switch, the second switch and the third switch are respectively connected to a fourth interface, a fifth interface and a sixth interface of the socket, third ends of the third switch and the third switch are connected to corresponding ports of the second relay and the third relay in a one-to-one correspondence mode, an input end of the first control coil is connected to a seventh interface of the socket, and an output end of the first control coil is grounded through an eighth interface;
the first relay is configured to conduct the first terminal and the second terminal of each of the first switch, the second switch and the third switch when the first control coil does not receive the automatic trimming signal transmitted through the seventh interface, and is further configured to conduct the first terminal and the third terminal of each of the first switch, the second switch and the third switch when the first control coil receives the automatic trimming signal transmitted through the seventh interface;
the second relay comprises a fourth switch, a fifth switch and a second control coil, and the third relay comprises a sixth switch, a seventh switch and a third control coil; the first end of the fourth switch is connected to the ninth jack of the socket, the second end of the fourth switch is connected to the first end of the sixth switch, and the third end of the fourth switch is connected to the third end of the second switch; the first end of the fifth switch is grounded, the second end of the fifth switch is open, and the third end of the fifth switch is connected to the third end of the first switch; the input end of the second control coil is connected to the tenth interface of the socket, and the output end of the second control coil is connected to the first end of the seventh switch; the second end of the sixth switch is open, and the third end is connected to the third end of the third switch; a ground wire is arranged between the first end of the seventh switch and the output end of the second control coil, the second end of the seventh switch is open, and the third end of the seventh switch is connected to the third end of the first switch; the input end of the third control coil is connected to the eleventh interface of the socket, and the output end of the third control coil is grounded; under the condition that the control coil does not receive the signal, the first ends and the second ends of all the switches in the relay of the control coil are communicated;
the second relay is configured to conduct the first end and the third end of the fourth switch and the third switch respectively and transmit the motor control signal input by the ninth interface to the second interface through the fourth switch and the second switch when the motor control signal is input to the second relay by the ninth interface and the second control coil receives the automatic balancing forward rotation signal transmitted by the tenth interface;
and the third relay is configured to turn on the first terminal and the third terminal of the sixth switch and the seventh switch respectively and transmit the motor control signal input from the ninth interface to the third interface through the sixth switch and the third switch when the motor control signal is input from the ninth interface to the third relay and the third control coil receives the auto-trim reverse signal transmitted from the eleventh interface.
Optionally, in the trim adapter of an automatic flight control system as described above, the first interface, the second interface, and the third interface of the socket are connected to the total negative line, the positive rotation line, and the positive reverse rotation line of the control motor in a one-to-one correspondence, the fourth interface, the fifth interface, and the sixth interface of the socket are connected to the total negative line, the positive manual rotation line, and the positive manual reverse rotation line of the manual trim control system in a one-to-one correspondence, and the seventh interface is connected to the automatic trim through line of the automatic flight control system.
Alternatively, in the trim adapter of an automatic flight control system as described above,
the first relay is further configured to send a manual forward rotation signal or a manual reverse rotation signal to the control motor through the manual trim control system when the first end and the second end of each of the first switch, the second switch and the third switch are conducted, and is further configured to send an automatic trim forward rotation signal or an automatic trim reverse rotation signal to the control motor through the automatic flight control system when the first end and the third end of each of the first switch, the second switch and the third switch are conducted.
Optionally, in the balancing adapter of the automatic flight control system as described above, the ninth interface, the tenth interface, and the eleventh interface are connected to the motor control positive line, the automatic balancing positive rotation line, and the automatic balancing reverse rotation line of the automatic flight control system in a one-to-one correspondence, where the seventh interface continuously transmits the motor control signal to the second relay or the third relay while transmitting the automatic balancing signal to the first control coil, and the tenth interface and the eleventh interface selectively receive the automatic balancing signal transmitted by the automatic flight control system.
Alternatively, in the trim adapter of an automatic flight control system as described above,
the second relay is also configured to transmit a motor control signal input by the ninth interface to a forward rotation line of the control motor when the tenth interface inputs an automatic balancing forward rotation signal and the first end and the third end of each of the fourth switch and the fifth switch are conducted, so that the control motor executes an automatic balancing forward rotation operation;
and the third relay is also configured to transmit a motor control signal input by the ninth interface to a reverse positive line of the control motor when the auto-balancing reverse signal is input by the eleventh interface and the first end and the third end of each of the sixth switch and the seventh switch are turned on, so that the control motor performs an auto-balancing reverse operation.
Optionally, in the trim adaptor of the automatic flight control system as described above, further comprising: a fourth relay and a fifth relay;
the fourth relay comprises an eighth switch and a fourth control coil, and the fifth relay comprises a ninth switch and a fifth control coil; the first end of the eighth switch is connected to the twelfth interface of the socket, the second end of the eighth switch is grounded, and the third end of the eighth switch is connected to the second interface of the socket; the input end of the fourth control coil is connected to the tenth interface, and the output end of the fourth control coil is grounded; the first end of the ninth switch is connected to the thirteenth interface of the socket, the second end of the ninth switch is grounded, and the third end of the ninth switch is connected to the third interface of the socket; the input end of the fifth control coil is connected to the eleventh interface, and the output end of the fifth control coil is grounded; and under the condition that the control coil does not receive the signal, the first ends and the second ends of all the switches in the relay to which the control coil belongs are communicated.
Optionally, in the trim adaptor of an automatic flight control system as described above, the twelfth interface is connected to an automatic trim forward feedback line of the automatic flight control system;
and the fourth relay is configured to conduct the first end and the third end of the eighth switch when the fourth control coil receives the automatic balancing forward rotation signal input through the tenth interface, so that the control motor transmits the automatic balancing forward rotation feedback signal to the automatic flight control system through the forward rotation forward line, the second interface, the eighth switch and the twelfth interface.
Optionally, in the trim adaptor of an automatic flight control system as described above, the thirteenth interface is connected to an automatic trim reversal feedback line of the automatic flight control system;
and the fifth relay is configured to conduct the first end and the third end of the ninth switch when the fifth control coil receives the automatic trimming reverse signal input through the eleventh interface, so that the control motor transmits the automatic trimming reverse feedback signal to the automatic flight control system through the reverse positive line, the third interface, the ninth switch and the thirteenth interface.
According to the trimming adapter of the automatic flight control system, after the automatic flight control system and the trimming adapter are additionally arranged on an airplane, when the automatic flight control system normally works, the manual trimming control system can be cut off through the trimming adapter and is converted into an automatic flight control system to control an elevator trimmer, so that the automatic trimming function is realized; when the automatic flight control system does not work or fails, the automatic flight control system is automatically switched into a manual trim operation mode through the trim adapter. That is to say, under the condition that the automatic balancing is realized by adopting the balancing adapter, the automatic balancing signal can be fed back to the automatic flight control system, and the automatic flight control system can monitor the automatic balancing signal in real time.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.
Fig. 1 is a schematic structural diagram of a trim adapter of an automatic flight control system according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a trim adapter and a cross-linking system of an automatic flight control system according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of another configuration of a trim adapter and a cross-linking system of an automatic flight control system according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a trim adapter of another automatic flight control system according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
The technical solution provided by the present invention is explained in detail by several specific examples below. The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.
Fig. 1 is a schematic structural diagram of a trim adapter of an automatic flight control system according to an embodiment of the present invention. The trim adapter of the automatic flight control system provided by the embodiment can comprise: a first relay J1, a second relay J2, a third relay J3, and a receptacle provided on the trim adaptor, the receptacle including a plurality of interfaces, fig. 1 illustrates the plurality of interfaces on the receptacle at the periphery of the trim adaptor.
In the trim adapter of the automatic flight control system provided by the embodiment of the invention, the first relay J1 is a three-group contact control relay, that is, the first relay J1 comprises a first switch K1, a second switch K2, a third switch K3 and a first control coil C1; the first ends of the first switch K1, the second switch K2 and the third switch K3 are connected to the first interface S1, the second interface S2 and the third interface S3 of the socket in a one-to-one correspondence manner, the second ends are connected to the fourth interface S4, the fifth interface S5 and the sixth interface S5 of the socket in a one-to-one correspondence manner, the third ends are respectively connected to corresponding ports of the second relay J2 and the third relay J3, the input end a of the first control coil C1 is connected to the seventh interface S7 of the socket, and the output end B is grounded through the eighth interface S8 of the socket.
Based on the internal structure of the first relay J1 and the connection relationship thereof, the first relay J1 is respectively linked with the second relay J2 and the third relay J3, and selectively receives a control signal transmitted to the first relay J1 through the second relay J2 or the third relay J3 according to the actual situation of the input signal. Therefore, the first relay J1 performs the functions of: is configured to turn on the first and second terminals of each of the first, second, and third switches K1, K2, and K3 when the first control coil C1 does not receive the auto-trim signal transmitted through the seventh interface S7, and is further configured to turn on the first and third terminals of each of the first, second, and third switches K1, K2, and K3 when the first control coil C1 receives the auto-trim signal transmitted through the seventh interface S7.
As can be seen from the function of the first relay J1. On the other hand, when the first end and the second end of each of the first switch K1, the second switch K2, and the third switch K3 are turned on, the fourth interface S4 of the socket is connected to the first interface S1, the fifth interface S5 is connected to the second interface S2, and the sixth interface S6 is connected to the third interface S3, so that signals can be transmitted to the first interface S1, the second interface S2, and the third interface S3 through the fourth interface S4, the fifth interface S5, and the sixth interface S6 in a one-to-one correspondence manner. On the other hand, when the first end and the third end of each of the first switch K1, the second switch K2, and the third switch K3 are turned on, the three sets of communication relationships are cut off, and the signals of the first interface S1, the second interface S2, and the third interface S3 are provided by other devices in the trim adaptor.
The second relay J2 and the third relay J3 in the embodiment of the invention are both two sets of contact control relays, the second relay J2 includes a fourth switch K4, a fifth switch K5 and a second control coil C2, and the third relay J3 includes a sixth switch K6, a seventh switch K7 and a third control coil C3; a first terminal of the fourth switch K4 is connected to the ninth interface S9 of the socket, a second terminal is connected to the first terminal of the sixth switch K6, and a third terminal is connected to the third terminal of the second switch K2; the first end of the fifth switch K5 is grounded, the second end is open, and the third end is connected to the third end of the first switch K1; the input terminal a of the second control coil C2 is connected to the tenth interface S10 of the socket, and the output terminal B is connected to the first terminal of the seventh switch K7; the second terminal of the sixth switch K6 is open, and the third terminal is connected to the third terminal of the third switch K3; a ground wire is arranged between the first end of the seventh switch K7 and the output end B of the second control coil C2, the second end is open, and the third end is connected to the third end of the first switch K1; the input terminal a of the third control coil C3 is connected to the eleventh interface S11 of the socket, and the output terminal B is grounded.
It should be noted that, in the embodiment of the present invention, when the control coil does not receive a signal, the first ends of all the switches in the relay to which the control coil belongs are communicated with the second ends, that is, the first ends of all the switches are fixed ends, the second ends and the third ends are control ends, the first ends of the switches are communicated with the second ends in a default state, and the control coil receives the signal, and generates an electromagnetic attraction force to pull down the switches, so as to connect the first ends and the third ends.
Based on the internal structures and the connection structures of the second relay J2 and the third relay J3, it is known that the functions of the second relay J2 and the third relay J3 are as follows:
the second relay J2 is configured to, when the ninth interface S9 inputs a motor control signal to the second relay J2 and the second control coil C2 receives the auto-leveling forward rotation signal transmitted through the tenth interface S10, turn on the first and third terminals of the fourth switch K4 and the fifth switch K5, respectively, and transmit the motor control signal input through the ninth interface S9 to the second interface S2 through the fourth switch K4 and the second switch K2;
and a third relay J3 configured to turn on the first and third terminals of the sixth and seventh switches K6 and K7, respectively, and transmit the motor control signal input from the ninth interface S9 to the third interface S3 through the sixth and third switches K6 and K3, when the ninth interface S9 inputs the motor control signal to the third relay J3 and the third control coil C3 receives the auto-trim reverse rotation signal transmitted through the eleventh interface S11.
The automatic flight control system balancing adapter provided by the embodiment of the invention is applied to a flight control system, so that the automatic flight control system can be crosslinked with a manual balancing control system, the manual balancing control system can control a control motor, and the automatic flight control system can control the control motor, namely, the switching between the manual balancing control state and the automatic balancing control state is realized on the basis of realizing the automatic balancing function. In addition, the balancing adapter is simple in structure, convenient to implement, high in reliability, convenient to install, small in size and light in weight.
Optionally, fig. 2 is a schematic structural diagram of a trim adapter and a cross-linking system of an automatic flight control system according to an embodiment of the present invention, and fig. 2 specifically illustrates a connection relationship between the trim adapter and a control motor and a manual trim control system. The first interface S1, the second interface S2 and the third interface S3 of the socket are connected to a total negative line, a positive rotating line and a positive rotating line of a control motor in a one-to-one correspondence mode, the fourth interface S4, the fifth interface S5 and the sixth interface S6 of the socket are connected to a total negative line, a positive manual rotating line and a positive manual rotating line of a manual balancing control system in a one-to-one correspondence mode, and the seventh interface S7 is connected to an automatic balancing connecting line of an automatic flight control system.
Based on the connection relationship between the trim adapter and the control motor, the manual trim control system and the automatic flight control system, it can be known that the specific functions of the first relay J1 are as follows: and the first relay J1 is also configured to send a manual forward rotation signal or a manual reverse rotation signal to the control motor through the manual trim control system when the first end and the second end of each of the first switch K1, the second switch K2 and the third switch K3 are conducted. In the above embodiment, it has been explained that, in this case, the fourth interface S4 of the socket is connected to the first interface S1, the manual trim control system provides a total negative line signal to the control motor, the fifth interface S5 is connected to the second interface S2, the sixth interface S6 is connected to the third interface S3, and the manual trim control system selectively provides a manual forward rotation signal or a manual reverse rotation signal to the control motor.
The first relay J1 is further configured to send an auto-trim forward rotation signal or an auto-trim reverse rotation signal to the control motor through the auto-flight control system when the first terminal and the third terminal of each of the first switch K1, the second switch K2, and the third switch K3 are turned on. In this case, the signals on the forward rotation positive line and the reverse rotation positive line on the control motor are provided by the automatic flight control system, and a mode of realizing the automatic trim control by the cooperation of the automatic flight control system, the second relay J2 and the third relay J3 will be described in detail below.
Optionally, fig. 3 is another schematic structural diagram of a trim adapter and a cross-linking system of an automatic flight control system according to an embodiment of the present invention, and fig. 3 specifically illustrates a connection relationship between the trim adapter and the automatic flight control system. The ninth interface S9, the tenth interface S10 and the eleventh interface S11 are connected to a motor control positive line, an automatic balancing positive rotation line and an automatic balancing negative rotation line of the automatic flight control system in a one-to-one correspondence, wherein the seventh interface S7 transmits an automatic balancing signal to the first control coil C1, and the ninth interface S9 continuously transmits a motor control signal to the second relay J2 or the third relay J3.
To be noted, the tenth interface S10 and the eleventh interface S11 selectively receive the auto-trim signal transmitted by the auto-flight control system, the tenth interface S10 is used for inputting the auto-trim forward rotation signal, and the eleventh interface S11 is used for inputting the auto-trim reverse rotation signal, where the auto-trim forward rotation signal and the auto-trim reverse rotation signal are not input simultaneously.
Based on the connection relationship between the trim adapter and the automatic flight control system and the signal transmission mode of the automatic flight control system, it can be known that the specific functions of the second relay J2 and the third relay J3 are as follows:
a second relay J2, further configured to transmit the motor control signal input by the ninth interface S9 to the forward rotation line that controls the motor so that the control motor performs the auto-balancing forward rotation operation when the auto-balancing forward rotation signal is input by the tenth interface S10 and the first and third terminals of the fourth and fifth switches K4 and K5 are turned on, respectively; at this time, the total negative line of the control motor is grounded through the fifth switch K5.
A third relay J3, further configured to transmit the motor control signal input from the ninth interface S9 to a reverse rotation positive line that controls the motor so that the motor is controlled to perform an auto-trim reverse rotation operation, when the auto-trim reverse rotation signal is input from the eleventh interface S11 and the first and third terminals of the sixth and seventh switches K6 and K7 are turned on, respectively; at this time, the total negative line of the control motor is grounded through the seventh switch K7.
As can be seen from the above connection relationship and the functions of the second relay J2 and the third relay J3, when the automatic flight control system is turned on, the switching states of the two relays are always opposite, for example, when the first terminal and the third terminal of each of all the switches in the second relay J2 are turned on, the first terminal and the second terminal of each of all the switches in the third relay J3 are turned on. That is, at the same time, the auto-trim forward rotation signal is transmitted to the control motor only by the second relay J2, or the auto-trim reverse rotation signal is transmitted to the control motor only by the third relay J3.
Optionally, fig. 4 is a schematic structural diagram of a trim adapter of another automatic flight control system according to an embodiment of the present invention. On the basis of the structure of the balancing adapter shown in fig. 3, the balancing adapter provided by the embodiment of the present invention may further include: a fourth relay J4 and a fifth relay J5.
The fourth relay J4 and the fifth relay J5 in the embodiment of the present invention are both feedback signal relays, and the fourth relay J4 and the fifth relay J5 are a set of contact control relays. Wherein the fourth relay J4 includes an eighth switch K8 and a fourth control coil C4, and the fifth relay J5 includes a ninth switch K9 and a fifth control coil C5; the first end of the eighth switch K8 is connected to the twelfth interface S12 of the socket, the second end is grounded, and the third end is connected to the second interface S2 of the socket; the input end a of the fourth control coil C4 is connected to the tenth interface S10, and the output end B is grounded; the ninth switch K9 has a first terminal connected to the thirteenth port S13 of the socket, a second terminal connected to ground, and a third terminal connected to the third port S3 of the socket; the input end A of the fifth control coil C5 is connected to the eleventh interface S11, and the output end B is grounded; and under the condition that the control coil does not receive the signal, the first ends and the second ends of all the switches in the relay to which the control coil belongs are communicated.
In one implementation of an embodiment of the invention, the twelfth interface S12 is connected to an automatic trim forward feedback line of an automatic flight control system; based on the internal structure and the connection relationship of the fourth relay J4, the fourth relay J4 realizes the following functions: configured to turn on the first terminal and the third terminal of the eighth switch K8 when the fourth control coil C4 receives the auto-balancing forward rotation signal input through the tenth interface S10, so that the control motor transmits the auto-balancing forward rotation feedback signal to the auto-flight control system through the forward rotation positive line, the second interface S2, the eighth switch K8, and the twelfth interface S12; in this case, the ninth switch K9 feeds back a ground signal to the automatic flight control system through the thirteenth interface S13.
In one implementation of an embodiment of the invention, the thirteenth interface S13 is connected to an automatic trim inversion feedback line of an automatic flight control system; based on the internal structure and the connection relationship of the fifth relay J5, the fifth relay J5 realizes the following functions: configured to turn on the first terminal and the third terminal of the ninth switch K9 when the fifth control coil C5 receives the auto-trim reverse signal input through the eleventh interface S11, so that the control motor transmits the auto-trim reverse feedback signal to the auto-flight control system through the reverse positive line, the third interface S3, the ninth switch K9, and the thirteenth interface S13; in this case, the eighth switch K8 feeds back a ground signal to the automatic flight control system through the twelfth interface S12.
In addition, the housing of the trim adapter of the automatic flight control system provided by the above embodiments of the present invention is further provided with a grounding contact D1.
In practical application, based on the contact arrangement inside the socket, the corresponding relationship between the interface and the contact may be defined as follows: the first port S1 corresponds to the contact 7 of the socket, the second port S2 corresponds to the contact 1 of the socket, the third port S3 corresponds to the contact 14 of the socket, the fourth port S4 corresponds to the contact 2 of the socket, the fifth port S5 corresponds to the contact 15 of the socket, the sixth port S6 corresponds to the contact 16 of the socket, the seventh port S7 corresponds to the contact 5 of the socket, the eighth port corresponds to the contact 6 of the socket, the ninth port S9 corresponds to the contact 19 of the socket, the tenth port S10 corresponds to the contact 4 of the socket, the eleventh port S11 corresponds to the contact 17 of the socket, the twelfth port S12 corresponds to the contact 23 of the socket, and the thirteenth port S13 corresponds to the contact 11 of the socket.
According to the trimming adapter of the automatic flight control system, after the automatic flight control system and the trimming adapter are additionally arranged on an airplane, when the automatic flight control system normally works, the manual trimming control system can be cut off through the trimming adapter and converted into an automatic flight control system to control an elevator adjusting sheet, so that the automatic trimming function is realized; when the automatic flight control system does not work or fails, the automatic flight control system is automatically switched into a manual trim operation mode through the trim adapter. That is to say, under the condition that the automatic balancing is realized by adopting the balancing adapter, the automatic balancing signal can be fed back to the automatic flight control system, and the automatic flight control system can monitor the automatic balancing signal in real time.
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. A trim adapter for an automatic flight control system, comprising: the first relay, the second relay, the third relay and a socket arranged on the balancing adapter;
the first relay comprises a first switch, a second switch, a third switch and a first control coil, first ends of the first switch, the second switch and the third switch are connected to a first interface, a second interface and a third interface of the socket in a one-to-one correspondence mode, second ends of the first switch, the second switch and the third switch are respectively connected to a fourth interface, a fifth interface and a sixth interface of the socket, third ends of the third switch and the third switch are connected to corresponding ports of the second relay and the third relay in a one-to-one correspondence mode, an input end of the first control coil is connected to a seventh interface of the socket, and an output end of the first control coil is grounded through an eighth interface;
the first relay is configured to conduct the first terminal and the second terminal of each of the first switch, the second switch and the third switch when the first control coil does not receive the automatic trimming signal transmitted through the seventh interface, and is further configured to conduct the first terminal and the third terminal of each of the first switch, the second switch and the third switch when the first control coil receives the automatic trimming signal transmitted through the seventh interface;
the second relay comprises a fourth switch, a fifth switch and a second control coil, and the third relay comprises a sixth switch, a seventh switch and a third control coil; the first end of the fourth switch is connected to the ninth jack of the socket, the second end of the fourth switch is connected to the first end of the sixth switch, and the third end of the fourth switch is connected to the third end of the second switch; the first end of the fifth switch is grounded, the second end of the fifth switch is open, and the third end of the fifth switch is connected to the third end of the first switch; the input end of the second control coil is connected to the tenth interface of the socket, and the output end of the second control coil is connected to the first end of the seventh switch; the second end of the sixth switch is open, and the third end is connected to the third end of the third switch; a ground wire is arranged between the first end of the seventh switch and the output end of the second control coil, the second end of the seventh switch is open, and the third end of the seventh switch is connected to the third end of the first switch; the input end of the third control coil is connected to the eleventh interface of the socket, and the output end of the third control coil is grounded; under the condition that the control coil does not receive the signal, the first ends and the second ends of all the switches in the relay of the control coil are communicated;
the second relay is configured to conduct the first end and the third end of the fourth switch and the third switch respectively and transmit the motor control signal input by the ninth interface to the second interface through the fourth switch and the second switch when the motor control signal is input to the second relay by the ninth interface and the second control coil receives the automatic balancing forward rotation signal transmitted by the tenth interface;
and the third relay is configured to turn on the first terminal and the third terminal of the sixth switch and the seventh switch respectively and transmit the motor control signal input from the ninth interface to the third interface through the sixth switch and the third switch when the motor control signal is input from the ninth interface to the third relay and the third control coil receives the auto-trim reverse signal transmitted from the eleventh interface.
2. The trim adaptor for an automatic flight control system according to claim 1, wherein the first, second and third interfaces of the socket are connected to the total negative line, the positive forward line and the positive reverse line of the control motor in a one-to-one correspondence, the fourth, fifth and sixth interfaces of the socket are connected to the total negative line, the positive manual forward line and the positive manual reverse line of the manual trim control system in a one-to-one correspondence, and the seventh interface is connected to the automatic trim switch-on line of the automatic flight control system.
3. The trim adaptor of an automatic flight control system according to claim 2,
the first relay is further configured to send a manual forward rotation signal or a manual reverse rotation signal to the control motor through the manual trim control system when the first end and the second end of each of the first switch, the second switch and the third switch are conducted, and is further configured to send an automatic trim forward rotation signal or an automatic trim reverse rotation signal to the control motor through the automatic flight control system when the first end and the third end of each of the first switch, the second switch and the third switch are conducted.
4. The trim adaptor of an auto-flight control system according to claim 2, wherein the ninth interface, the tenth interface and the eleventh interface are connected to a motor control positive line, an auto-trim positive rotation line and an auto-trim reverse rotation line of the auto-flight control system in a one-to-one correspondence, wherein the seventh interface continuously transmits the motor control signal to the second relay or the third relay while the seventh interface transmits the auto-trim signal to the first control coil, and the tenth interface and the eleventh interface selectively receive the auto-trim signal transmitted by the auto-flight control system.
5. The trim adaptor of an automatic flight control system according to claim 4,
the second relay is also configured to transmit a motor control signal input by the ninth interface to a forward rotation line of the control motor when the tenth interface inputs an automatic balancing forward rotation signal and the first end and the third end of each of the fourth switch and the fifth switch are conducted, so that the control motor executes an automatic balancing forward rotation operation;
and the third relay is also configured to transmit a motor control signal input by the ninth interface to a reverse positive line of the control motor when the auto-balancing reverse signal is input by the eleventh interface and the first end and the third end of each of the sixth switch and the seventh switch are turned on, so that the control motor performs an auto-balancing reverse operation.
6. The trim adaptor for an automatic flight control system according to claim 4, further comprising: a fourth relay and a fifth relay;
the fourth relay comprises an eighth switch and a fourth control coil, and the fifth relay comprises a ninth switch and a fifth control coil; the first end of the eighth switch is connected to the twelfth interface of the socket, the second end of the eighth switch is grounded, and the third end of the eighth switch is connected to the second interface of the socket; the input end of the fourth control coil is connected to the tenth interface, and the output end of the fourth control coil is grounded; the first end of the ninth switch is connected to the thirteenth interface of the socket, the second end of the ninth switch is grounded, and the third end of the ninth switch is connected to the third interface of the socket; the input end of the fifth control coil is connected to the eleventh interface, and the output end of the fifth control coil is grounded; and under the condition that the control coil does not receive the signal, the first ends and the second ends of all the switches in the relay to which the control coil belongs are communicated.
7. The trim adaptor for an automatic flight control system according to claim 6, wherein the twelfth interface is connected to an automatic trim forward feedback line of an automatic flight control system;
and the fourth relay is configured to conduct the first end and the third end of the eighth switch when the fourth control coil receives the automatic balancing forward rotation signal input through the tenth interface, so that the control motor transmits the automatic balancing forward rotation feedback signal to the automatic flight control system through the forward rotation forward line, the second interface, the eighth switch and the twelfth interface.
8. The trim adaptor of an automatic flight control system according to claim 6, characterized in that the thirteenth interface is connected to an automatic trim reversal feedback line of an automatic flight control system;
and the fifth relay is configured to conduct the first end and the third end of the ninth switch when the fifth control coil receives the automatic trimming reverse signal input through the eleventh interface, so that the control motor transmits the automatic trimming reverse feedback signal to the automatic flight control system through the reverse positive line, the third interface, the ninth switch and the thirteenth interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911134495.6A CN110989660A (en) | 2019-11-19 | 2019-11-19 | Automatic flight control system's balancing adapter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911134495.6A CN110989660A (en) | 2019-11-19 | 2019-11-19 | Automatic flight control system's balancing adapter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110989660A true CN110989660A (en) | 2020-04-10 |
Family
ID=70084962
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911134495.6A Pending CN110989660A (en) | 2019-11-19 | 2019-11-19 | Automatic flight control system's balancing adapter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110989660A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112666929A (en) * | 2020-12-29 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Automatic balancing system for airplane state switching |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3378217A (en) * | 1966-09-02 | 1968-04-16 | Bendix Corp | Trim disconnect device for an aircraft control system |
| CN103043218A (en) * | 2012-12-10 | 2013-04-17 | 江西洪都航空工业集团有限责任公司 | Structure for implementing novel tandem aircraft trim control logic |
| CN105892482A (en) * | 2016-04-01 | 2016-08-24 | 哈尔滨飞机工业集团有限责任公司 | Trimming adapter of automatic flight control system |
| CN207360567U (en) * | 2017-10-18 | 2018-05-15 | 河北天启通宇航空器材科技发展有限公司 | The auto-trim circuit of gyroplane |
| CN110450940A (en) * | 2019-06-24 | 2019-11-15 | 陕西飞机工业（集团）有限公司 | A kind of elevator trimming control circuit of aircraft |
-
2019
- 2019-11-19 CN CN201911134495.6A patent/CN110989660A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3378217A (en) * | 1966-09-02 | 1968-04-16 | Bendix Corp | Trim disconnect device for an aircraft control system |
| CN103043218A (en) * | 2012-12-10 | 2013-04-17 | 江西洪都航空工业集团有限责任公司 | Structure for implementing novel tandem aircraft trim control logic |
| CN105892482A (en) * | 2016-04-01 | 2016-08-24 | 哈尔滨飞机工业集团有限责任公司 | Trimming adapter of automatic flight control system |
| CN207360567U (en) * | 2017-10-18 | 2018-05-15 | 河北天启通宇航空器材科技发展有限公司 | The auto-trim circuit of gyroplane |
| CN110450940A (en) * | 2019-06-24 | 2019-11-15 | 陕西飞机工业（集团）有限公司 | A kind of elevator trimming control circuit of aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112666929A (en) * | 2020-12-29 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Automatic balancing system for airplane state switching |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105786742B (en) | Server serial port switching device and method and server | |
| CN108495224A (en) | A kind of communication system | |
| CN106921405A (en) | A kind of radio frequency front-end device | |
| CN1716682B (en) | Matrix type radio frequency switch intelligent switching control series | |
| CN103532177A (en) | Portable charger and method of operating the same | |
| CN110989660A (en) | Automatic flight control system's balancing adapter | |
| CN208241832U (en) | A kind of communication system | |
| CN107395221A (en) | A kind of LTE frequency ranges switching device, switching method and mobile terminal | |
| CN203232300U (en) | Multichannel hybrid remote-operated control system | |
| CN111711552B (en) | Terminal resistor access circuit, servo driver and control system | |
| CN212515785U (en) | High-speed USB TYPE-C interface device supporting bidirectional transmission and graphic signal generator | |
| US20020146987A1 (en) | Universal communication device | |
| CN105406910B (en) | Optical path backup and mimo transmission system, near-end device, far end device | |
| GB2585459A (en) | Lossless microwave switch | |
| AU2020100101A4 (en) | Bluetooth switch socket | |
| CN115277282A (en) | CAN node, working method thereof and CAN bus | |
| KR102162464B1 (en) | Parallel inverter system | |
| CN220962172U (en) | Material object signal and simulation signal disconnection switching module for system verification | |
| CN214751424U (en) | Reconfigurable bus network among multiple aircrafts | |
| CN219268856U (en) | Bluetooth wireless communication system and intelligent device | |
| CN202696597U (en) | Radio frequency conversion equipment | |
| CN214335524U (en) | RS485 and RS422 compatible structure for automatic flow control of hardware | |
| CN216848552U (en) | S.BUS many-to-one remote control system | |
| CN214896592U (en) | Serial port communication switching system | |
| CN205545498U (en) | Controlling means simply telephones |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20200410 |