Aircraft GPS signal combination control circuit and aircraft

Abstract

The utility model discloses an aircraft GPS signal combining control circuit and an aircraft. Comprising a first GPS antenna, a second GPS antenna, a channel switching module, a control circuit and a combiner. The second GPS antenna is arranged outside the aircraft protection cover, and the first GPS antenna is arranged on the surface of the aircraft body; the second GPS antenna is connected with a port B of the combiner; the first GPS antenna is connected with a port A of the combiner; a port C of the combiner is an output end; the control circuit and the channel switching module are arranged in the combiner; a port B of the combiner is connected with a second input end of the channel switching module; a port A of the combiner is connected with a first input end of the channel switching module; a port C of the combiner is connected with the output end of the channel switching module; and the control circuit is connected with the channel switching module. The inertial navigation system enters the integrated navigation mode, so that the safe flight of the aircraft is ensured.

Description

Technical Field

[0001] This application relates to the technical field of aircraft signal transmission, and particularly to an aircraft GPS signal combining control circuit and an aircraft. Background Art

[0002] Due to the problem that the GPS signal of the aircraft is blocked, during the design process of the aircraft, two paths of GPS signals are provided. One path of GPS signal has an unobstructed field of view, and the other path of GPS signal is in a blocked state when in the folded state. After passing through a combiner, the two paths of GPS signals can output one path of GPS signal, and this path of GPS signal is transmitted to the inertial navigation system. After being calculated by the inertial navigation system, accurate position, speed, attitude and other information are provided for the aircraft, so as to guide the aircraft to fly along the given route.

[0003] However, under certain special working conditions, such as when the folding aircraft is initially in a protective cover, and the protective cover uses carbon fiber material, which further enhances the shielding effect. After testing, most of the GPS signals are absent or very weak, resulting in the inertial navigation system (INS) being unable to enter the integrated navigation mode, posing a safety hazard to the positioning and flight of the aircraft. This solution aims to solve the problem that the INS can reliably and stably receive the GPS signal under special working conditions. Utility Model Content

[0004] By providing an aircraft GPS signal combining control circuit in an embodiment of this application, the problem in the prior art that in special working conditions, the shielding effect of the aircraft GPS signal is enhanced, resulting in the inertial navigation system being unable to enter the integrated navigation mode is solved; it is realized that in special working conditions, the aircraft GPS signal can be stably and reliably transmitted to the inertial navigation system, and the inertial navigation system enters the integrated navigation mode, thereby ensuring the safe flight of the aircraft.

[0005] In a first aspect, an embodiment of the present utility model provides a GPS signal combining control circuit for an aircraft, which includes a first GPS antenna, a second GPS antenna, a channel switching module, a control circuit, and a combiner; the second GPS antenna is disposed outside the aircraft protective cover, and the first GPS antenna is disposed on the surface of the aircraft fuselage; the second GPS antenna is connected to port B of the combiner; the first GPS antenna is connected to port A of the combiner; port C of the combiner is the output end; the control circuit and the channel switching module are disposed inside the combiner; port B of the combiner is connected to the second input end of the channel switching module; port A of the combiner is connected to the first input end of the channel switching module; port C of the combiner is connected to the output end of the channel switching module; the control circuit is connected to the channel switching module, and the control circuit is configured to control the operation of the channel switching module, and under different control signals, control the first input end or the second input end of the channel switching module to be respectively communicated with the output end of the channel switching module.

[0006] In combination with the first aspect, in a possible implementation manner, an inertial navigation system is further included; port C of the combiner is connected to the inertial navigation system.

[0007] In combination with the first aspect, in a possible implementation manner, a flight control computer and a power distribution management unit are further included; the flight control computer is connected to the control end of the control circuit; and is configured to output an instruction signal to the control circuit based on the aircraft state; the power distribution management unit is connected to the power supply end of the control circuit and is configured to control the control signal output by the control circuit to the channel switching module based on the instruction signal.

[0008] In combination with the first aspect, in a possible implementation manner, an electrical separation plug is further included; the electrical separation plug includes a plug and a socket; the plug and the socket are respectively disposed on the aircraft protective cover and the aircraft fuselage, and the plug is configured to be disconnected as the aircraft protective cover separates; the second GPS antenna is connected to the plug, and port B of the combiner is connected to the socket.

[0009] In combination with the first aspect, in a possible implementation manner, a boost circuit is further included; one end of the boost circuit is connected to the power distribution management unit; the other end of the boost circuit is connected to the power supply end of the control circuit.

[0010] In combination with the first aspect, in a possible implementation manner, the control circuit includes a first control circuit, a second control circuit, a third control circuit, and a fourth control circuit; the channel switching module includes MOS transistor Q1 and MOS transistor Q2; the first control circuit includes MOS transistor Q3, and the fourth control circuit includes MOS transistor Q4; the sources of the MOS transistor Q1 and the MOS transistor Q2 are both connected to port C of the combiner; the control terminal A of the first control circuit is connected to the flight control computer, the power supply terminal of the first control circuit is connected to the boost circuit, the gate of the MOS transistor Q3 is connected to the control terminal A, the drain of the MOS transistor Q3 is connected to the drain of the MOS transistor Q1, and the source of the MOS transistor Q3 is grounded; port A of the combiner is connected to the drain of the MOS transistor Q1; the control terminal B of the second control circuit is connected to the flight control computer, the power supply terminal of the second control circuit is connected to the boost circuit, and the output terminal of the second control circuit is connected to the gate and the source of the MOS transistor Q1; the control terminal C of the third control circuit is connected to the flight control computer, the power supply terminal of the third control circuit is connected to the boost circuit, and the output terminal of the third control circuit is connected to the gate and the source of the MOS transistor Q2; the control terminal D of the fourth control circuit is connected to the flight control computer, the power supply terminal of the fourth control circuit is connected to the boost circuit, the gate of the MOS transistor Q4 is connected to the control terminal D, the drain of the MOS transistor Q4 is connected to the drain of the MOS transistor Q2; port B of the combiner is connected to the drain of the MOS transistor Q2.

[0011] In the second aspect, an embodiment of the present invention provides an aircraft, and the aircraft adopts the above-mentioned aircraft GPS signal combining control circuit.

[0012] One or more technical solutions provided by this application have at least the following technical effects:

[0013] The embodiment of the present utility model adopts a first GPS antenna, a second GPS antenna, a channel switching module, a control circuit, a combiner and an inertial navigation system. The second GPS antenna is arranged outside the fuselage of the aircraft, and the first GPS antenna is arranged inside the fuselage of the aircraft; the positions of the first GPS antenna and the second GPS antenna on the aircraft are different; when one GPS signal is blocked, the other GPS antenna can be used to transmit the signal; the second GPS antenna is connected to port B of the combiner; the first GPS antenna is connected to port A of the combiner; port C of the combiner is connected to the inertial navigation system; the combiner can combine the signals of the first GPS antenna and the second GPS antenna into one signal and output it to the inertial navigation system; both the channel switching module and the control circuit are arranged inside the combiner, and port B of the combiner is connected to the second input end of the channel switching module; port A of the combiner is connected to the first input end of the channel switching module; port C of the combiner is connected to the output end of the channel switching module; when the signals of the first GPS antenna and the second GPS antenna are transmitted to the combiner, the GPS signals can be selected by the switching module; the control circuit is connected to the channel switching module, and the control circuit can control the operation of the channel switching module. When the control end A of the control circuit is at high level, the control end B is at low level, the control end C is at high level, and the control end D is at low level, the GPS signal at port B of the combiner is selected for output; when the control end A of the control circuit is at low level, the control end B is at high level, the control end C is at low level, and the control end D is at high level, the GPS signal at port A of the combiner is selected for output. This application solves the problem in the prior art that in special working conditions, the shielding effect of the GPS signal of the aircraft is strengthened, resulting in the inertial navigation system being unable to enter the integrated navigation mode; it realizes that in special working conditions, the GPS signal of the aircraft can be stably and reliably transmitted to the inertial navigation system, and the inertial navigation system enters the integrated navigation mode, thus ensuring the safe flight of the aircraft. Description of the Drawings

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the following will briefly introduce the drawings required for the description of the embodiments of the present utility model. Obviously, the drawings in the following description are some embodiments of the present utility model. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0015] Figure 1 It is a principle block diagram of a control circuit for combining GPS signals of an aircraft provided by an embodiment of the present application;

[0016] Figure 2 It is a circuit diagram of a control circuit and a channel switching module provided by an embodiment of the present application;

[0017] Figure 3 This is the circuit diagram of the boost circuit provided by the embodiment of the present application;

[0018] Figure 4 This is the flowchart of a flight vehicle GPS signal combining control circuit provided by the embodiment of the present application.

[0019] Icons: 1 - First GPS antenna; 2 - Second GPS antenna; 3 - Channel switching module; 4 - Control circuit; 41 - First control circuit; 42 - Second control circuit; 43 - Third control circuit; 44 - Fourth control circuit; 5 - Combiner; 6 - Inertial navigation system; 7 - First high-frequency cable; 8 - Second high-frequency cable; 9 - Third high-frequency cable; 10 - Flight control computer; 11 - Power distribution management unit; 12 - Electrical separation and disconnection; 121 - Disconnection plug; 122 - Disconnection socket; 13 - Boost circuit. Detailed implementation manners

[0020] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0021] In the description of the embodiments of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the embodiments of the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention. The terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance. In addition, the terms "installed", "connected", "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present invention can be understood according to specific circumstances.

[0022] The embodiment of the present invention provides a flight vehicle GPS signal combining control circuit, as Figure 1As shown in the figure, it includes a first GPS antenna 1, a second GPS antenna 2, a channel switching module 3, a control circuit 4, and a combiner 5; the second GPS antenna 2 is arranged outside the aircraft protective cover, and the first GPS antenna 1 is arranged on the surface of the aircraft fuselage; the second GPS antenna 2 is connected to port B of the combiner 5; the first GPS antenna 1 is connected to port A of the combiner 5; port C of the combiner 5 is the output end; the control circuit 4 and the channel switching module 3 are arranged inside the combiner 5; port B of the combiner 5 is connected to the second input end of the channel switching module 3; port A of the combiner 5 is connected to the first input end of the channel switching module 3; port C of the combiner 5 is connected to the output end of the channel switching module 3; the control circuit 4 is connected to the channel switching module 3, and the control circuit 4 is configured to control the operation of the channel switching module 3, and under different control signals, control the first input end or the second input end of the channel switching module 3 to be respectively connected to the output end of the channel switching module 3.

[0023] In the embodiment of the present application, as Figure 1 shown in the figure, it further includes an inertial navigation system 6; port C of the combiner 5 is connected to the inertial navigation system 6.

[0024] Exemplarily, the second GPS antenna 2 is connected to port B of the combiner 5 through a second high-frequency cable 8; the first GPS antenna 1 is connected to port A of the combiner 5 through a first high-frequency cable 7; port C of the combiner 5 is connected to the inertial navigation system 6 through a third high-frequency cable 9; both the channel switching module 3 and the control circuit 4 are arranged inside the combiner 5.

[0025] Exemplarily, as Figure 1 shown in the figure, the first GPS antenna 1 and the second GPS antenna 2 are arranged at different positions on the aircraft; when one path of GPS signal is blocked, the other path of GPS antenna can be used to transmit the signal; the traditional combiner 5 does not require power supply and control, and can only combine the signals of the first GPS antenna 1 and the second GPS antenna 2 into one path of signal and output it to the inertial navigation system 6. In the present application, a channel switching module 3 and a control circuit 4 are arranged in the combiner 5, and when the signals of the first GPS antenna 1 and the second GPS antenna 2 are transmitted to the combiner 5, the GPS signals can be selected through the switching module, and the control circuit 4 is configured to control the operation of the channel switching module 3. When the control terminal A of the control circuit 4 is at high level, the control terminal B is at low level, the control terminal C is at high level, and the control terminal D is at low level, the GPS signal of port B of the combiner 5 is selected for output; when the control terminal A of the control circuit 4 is at low level, the control terminal B is at high level, the control terminal C is at low level, and the control terminal D is at high level, the GPS signal of port A of the combiner 5 is selected for output.

[0026] Exemplarily, the control circuit 4 is powered by 12V. When the control terminal A is 0V, the control terminal B is 5V, the control terminal C is 0V, and the control terminal D is 5V, the GPS signal output of port A of the combiner 5 is selected. On the contrary, when the control terminal A is 5V, the control terminal B is 0V, the control terminal C is 5V, and the control terminal D is 0V, the GPS signal output of port B of the combiner 5 is selected.

[0027] Exemplarily, the control circuit 4 can effectively control the operation of the channel switching module 3, allowing only one GPS signal to be effective each time, thereby suppressing the interference of signals from other channels, enabling the GPS signal to be stably and reliably transmitted to the inertial navigation system 6, and entering the integrated navigation mode, thus ensuring the safe flight of the aircraft.

[0028] In the embodiment of the present application, as Figure 1 and Figure 4 shown, it further includes a flight control computer 10 and a power distribution management unit 11; the flight control computer 10 is connected to the control terminal of the control circuit 4; and is configured to output an instruction signal to the control circuit 4 based on the aircraft state; the power distribution management unit 11 is connected to the power supply terminal of the control circuit 4 and is configured to control the control signal output by the control circuit 4 to the channel switching module 3 based on the instruction signal.

[0029] Exemplarily, the flight control computer 10 can send instructions to the control circuit 4.

[0030] Exemplarily, the flight control computer 10 sends a control instruction to the control circuit 4 to select the GPS signal output of port B of the combiner 5, transmit this signal to the inertial navigation system 6, and after a period of time, check whether the integrated navigation mode is entered in the inertial navigation system 6; the flight control computer 10 sends a control instruction to the control circuit 4 to select the GPS signal output of port A of the combiner 5, transmit this signal to the inertial navigation system 6, and after a period of time, check whether the integrated navigation mode is entered in the inertial navigation system 6.

[0031] Exemplarily, the power distribution management unit 11 can supply power to the control circuit 4.

[0032] Exemplarily, the voltage output by the power distribution management unit 11 is 5V.

[0033] In the embodiment of the present application, as Figure 1 shown, it further includes an electrical separation and disconnection plug 12; the electrical separation and disconnection plug 12 includes a disconnection plug 121 and a disconnection socket 122; the disconnection plug 121 and the disconnection socket 122 are respectively arranged on the aircraft protective cover and the aircraft fuselage, and the disconnection plug 121 is configured to be disconnected as the aircraft protective cover separates; the second GPS antenna 2 is connected to the disconnection plug 121, and port B of the combiner 5 is connected to the disconnection socket 122.

[0034] Exemplarily, the second GPS antenna 2 is connected to the electrical disconnect plug 12 through the second high-frequency cable 8, and the electrical disconnect plug 12 is connected to port B of the combiner 5 through the second high-frequency cable 8.

[0035] Exemplarily, the electrical disconnect plug 12 includes a disconnect plug 121 and a disconnect socket 122. The disconnect plug 121 can be plugged and unplugged on the disconnect socket 122. The disconnect socket 122 is arranged on the fuselage protective cover. The second GPS antenna 2 is connected to the disconnect plug 121 through the second high-frequency cable 8, and the disconnect socket 122 is connected to port B of the combiner 5 through the second high-frequency cable 8.

[0036] Exemplarily, as Figure 1 shown, in the initial state, the folding aircraft is inside the fuselage protective cover. The carbon fiber material used for the fuselage protective cover further enhances the shielding effect. By arranging a channel switching module 3 and a control circuit 4 in the combiner 5, when the signals of the first GPS antenna 1 and the second GPS antenna 2 are transmitted to the combiner 5, the GPS signals can be selected by the switching module. The control circuit 4 is configured to control the operation of the channel switching module 3. When the control terminal A of the control circuit 4 is at a high level, the control terminal B is at a low level, the control terminal C is at a high level, and the control terminal D is at a low level, the GPS signal of port B of the combiner 5 is selected for output; when the control terminal A of the control circuit 4 is at a low level, the control terminal B is at a high level, the control terminal C is at a low level, and the control terminal D is at a high level, the GPS signal of port A of the combiner 5 is selected for output. This allows only one GPS signal to be valid each time, thereby suppressing the interference of signals from other channels, enabling the GPS signal to be stably and reliably transmitted to the inertial navigation system 6 and enter the integrated navigation mode, thus ensuring the safe flight of the aircraft.

[0037] In the embodiment of the present application, as Figure 2As shown in the figure, the control circuit 4 includes a first control circuit 41, a second control circuit 42, a third control circuit 43, and a fourth control circuit 44; the channel switching module 3 includes an MOS transistor Q1 and an MOS transistor Q2; the first control circuit 41 includes an MOS transistor Q3, and the fourth control circuit 44 includes an MOS transistor Q4; the sources of the MOS transistor Q1 and the MOS transistor Q2 are both connected to the port C of the combiner 5; the control terminal A of the first control circuit 41 is connected to the flight control computer 10, the power supply terminal of the first control circuit 41 is connected to the boost circuit 13, the gate of the MOS transistor Q3 is connected to the control terminal A, the drain of the MOS transistor Q3 is connected to the drain of the MOS transistor Q1, and the source of the MOS transistor Q3 is grounded; the port A of the combiner 5 is connected to the drain of the MOS transistor Q1; the control terminal B of the second control circuit 42 is connected to the flight control computer 10, the power supply terminal of the second control circuit 42 is connected to the boost circuit 13, and the output terminal of the second control circuit 42 is connected to the gate and the source of the MOS transistor Q1; the control terminal C of the third control circuit 43 is connected to the flight control computer 10, the power supply terminal of the third control circuit 43 is connected to the boost circuit 13, and the output terminal of the third control circuit 43 is connected to the gate and the source of the MOS transistor Q2; the control terminal D of the fourth control circuit 44 is connected to the flight control computer 10, the power supply terminal of the fourth control circuit 44 is connected to the boost circuit 13, the gate of the MOS transistor Q4 is connected to the control terminal D, the drain of the MOS transistor Q4 is connected to the drain of the MOS transistor Q2; the port B of the combiner 5 is connected to the drain of the MOS transistor Q2.

[0038] Exemplarily, the first control circuit 41 includes an MOS transistor Q3, and the on-off of the MOS transistor Q3 can be controlled by the flight control computer 10; the fourth control circuit 44 includes an MOS transistor Q4, and the on-off of the MOS transistor Q4 can be controlled by the flight control computer 10.

[0039] Exemplarily, when the MOS transistor Q3 is in the off state, that is, when a low level is input to the control terminal A of the first control circuit 41, the MOS transistor Q1 is in the on state. At this time, the control terminal B is at a high level, the control terminal C is at a low level, the MOS transistor Q4 is in the on state, that is, when a high level is input to the control terminal D of the fourth circuit, the MOS transistor Q2 is in the off state. The GPS signal output of the port A of the combiner 5 is selected.

[0040] Exemplarily, when the MOS transistor Q3 is in the on state, that is, when a high level is input to the control terminal A of the first control circuit 41, the MOS transistor Q1 is in the off state. At this time, the control terminal B is at a low level, the control terminal C is at a high level, the MOS transistor Q4 is in the off state, that is, a low level is input to the control terminal D of the fourth circuit, and the MOS transistor Q2 is in the on state. The GPS signal output from port B of the selection combiner 5 is selected.

[0041] An embodiment of the present invention provides a flight vehicle GPS signal combining control circuit, and the principle of realizing channel switching is as follows:

[0042] The flight control computer 10 determines the inputs of the control terminal A, the control terminal B, the control terminal C, and the control terminal D based on the current state of the flight vehicle. When the flight vehicle is inside the flight vehicle protection cover, the signal output by the flight control computer to the control terminal A is high, the signal output to the control terminal B is low, the signal output to the control terminal C is high, and the signal output to the control terminal D is low, so that VG2 is turned on and VG1 is turned off, thereby selecting the second GPS antenna 2 connected to port B of the combiner 5 to provide a signal for the inertial navigation; after the flight vehicle completes the cover ejection action, the signal output by the flight control computer to the control terminal A is low, the signal output to the control terminal B is high, the signal output to the control terminal C is low, and the signal output to the control terminal D is high, so that VG1 is turned on and VG2 is turned off, thereby selecting the first GPS antenna 1 connected to port A of the combiner 5 to provide a signal for the inertial navigation.

[0043] In the embodiment of the present application, as Figure 2 and Figure 3 shown, a boost circuit 13 is further included; one end of the boost circuit 13 is connected to the power distribution management unit 11; the other end of the boost circuit 13 is connected to the power supply terminal of the control circuit 4.

[0044] Exemplarily, the boost circuit 13 includes a DC-DC module, a first capacitor C1, a second capacitor C2, a third capacitor C3, and a fourth capacitor C4. The first capacitor C1 and the second capacitor C2 are connected in parallel, one end is connected to the power distribution management unit 11, and the other end is grounded. The third capacitor C3 and the fourth capacitor C4 are connected in parallel, one end is connected to the power supply terminal of the control circuit 4, and the other end is grounded. One end of the DC-DC module is connected to the power distribution management unit 11, and the other end is connected to the power supply terminal of the control circuit 4.

[0045] Exemplarily, the voltage output by the power distribution management unit 11 is 5V, and the boost circuit 13 can convert the 5V voltage into 12V for use by the control circuit 4.

[0046] In the embodiment of the present application, the control circuit 4 can effectively control the operation of the channel switching module 3, allowing only one GPS signal to be valid each time. When the flight control computer 10 sets the control terminal A to a high level, the control terminal B to a low level, the control terminal C to a high level, and the control terminal D to a low level, the signal of the second GPS antenna 2 arranged outside the fuselage becomes valid. When the flight control computer 10 sets the control terminal A to a low level, the control terminal B to a high level, the control terminal C to a low level, and the control terminal D to a high level, the signal of the first GPS antenna 1 arranged inside the fuselage becomes valid.

[0047] With the control circuit 4 and the channel switching module 3 of the present application, when the wings are in the folded state, after multiple ground tests, it can enter the integrated navigation mode, and the number of available satellites displayed by the ground station is 17 - 18; when a fuselage protection cover is added to the aircraft, through ground tests, it can enter the integrated navigation mode, and the number of available satellites displayed by the ground station is 16 - 17.

[0048] The embodiment of the present utility model provides a flight vehicle GPS signal combining control circuit, and its test steps are as follows:

[0049] For convenience of description, here the ports A to C are referred to as channel 1, and the ports B to C are referred to as channel 2

[0050] (1) As Figure 4 shown, first, the flight vehicle is tested multiple times under the condition of having a fuselage protection cover. After the whole machine is powered on normally, the flight control computer 10 sends a channel 2 instruction to the control circuit 4. Through the channel switching module 3, the channel of port B of the combiner 5 is selected and then transmitted to the inertial navigation system 6. After 3 minutes, the inertial navigation system 6 enters the integrated navigation mode.

[0051] (2) Secondly, after removing the fuselage protection cover and unfolding the wings, the flight control computer 10 will send a channel 1 instruction to the control circuit 4. Through the channel switching module 3, the channel of port A of the combiner 5 is selected and then transmitted to the inertial navigation system 6. After 10 seconds, the inertial navigation system 6 enters the integrated navigation mode.

[0052] (3) Finally, the flight control computer 10 sends a channel 2 instruction to the control circuit 4, and it enters the integrated navigation mode again after 10s.

[0053] According to the above steps, a total of 15 tests are conducted, and the inertial navigation can enter the integrated navigation mode each time.

[0054] The embodiment of the present utility model provides a flight vehicle, and the flight vehicle includes the above-mentioned flight vehicle GPS signal combining control circuit.

[0055] The various embodiments in this specification are described in a progressive manner. For the same or similar parts among the various embodiments, reference can be made to each other. Each embodiment focuses on the differences from other embodiments.

[0056] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit the present application. Although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present application.

Claims

1. A GPS signal combining control circuit for an aircraft, characterized in that, It includes a first GPS antenna (1), a second GPS antenna (2), a channel switching module (3), a control circuit (4), and a combiner (5); The second GPS antenna (2) is disposed outside the aircraft protective cover, and the first GPS antenna (1) is disposed on the surface of the aircraft fuselage; The second GPS antenna (2) is connected to port B of the combiner (5); the first GPS antenna (1) is connected to port A of the combiner (5); port C of the combiner (5) is the output terminal; The control circuit (4) and the channel switching module (3) are disposed inside the combiner (5); Port B of the combiner (5) is connected to the second input terminal of the channel switching module (3); port A of the combiner (5) is connected to the first input terminal of the channel switching module (3); port C of the combiner (5) is connected to the output terminal of the channel switching module (3); The control circuit (4) is connected to the channel switching module (3), and the control circuit (4) is configured to control the operation of the channel switching module (3), and under different control signals, control the first input terminal or the second input terminal of the channel switching module (3) to be respectively communicated with the output terminal of the channel switching module (3).

2. The aircraft GPS signal combining control circuit according to claim 1, wherein It further includes an inertial navigation system (6); Port C of the combiner (5) is connected to the inertial navigation system (6).

3. The aircraft GPS signal combining control circuit according to claim 1, wherein It further includes a flight control computer (10) and a power distribution management unit (11); The flight control computer (10) is connected to the control terminal of the control circuit (4); and is configured to output an instruction signal to the control circuit (4) based on the aircraft state; The power distribution management unit (11) is connected to the power supply terminal of the control circuit (4), and is configured to control the control signal output by the control circuit (4) to the channel switching module (3) based on the instruction signal.

4. The aircraft GPS signal combining control circuit according to claim 1, characterized in that, It further includes an electrical separation plug (12); The electrical separation plug (12) includes a plug (121) and a socket (122); the plug (121) and the socket (122) are respectively disposed on the aircraft protective cover and the aircraft fuselage, and the plug (121) is configured to be disconnected as the aircraft protective cover separates; The second GPS antenna (2) is connected to the plug (121), and port B of the combiner (5) is connected to the socket (122).

5. The aircraft GPS signal combining control circuit according to claim 3, wherein, It further includes a boost circuit (13); One end of the boost circuit (13) is connected to the power distribution management unit (11); the other end of the boost circuit (13) is connected to the power supply terminal of the control circuit (4).

6. The aircraft GPS signal combining control circuit according to claim 5, wherein The control circuit (4) includes a first control circuit (41), a second control circuit (42), a third control circuit (43), and a fourth control circuit (44); The channel switching module (3) includes MOS transistor Q1 and MOS transistor Q2; The first control circuit (41) includes MOS transistor Q3, and the fourth control circuit (44) includes MOS transistor Q4; The sources of the MOS transistor Q1 and the MOS transistor Q2 are both connected to port C of the combiner (5); The control terminal A of the first control circuit (41) is connected to the flight control computer (10), the power supply terminal of the first control circuit (41) is connected to the boost circuit (13), the gate of the MOS transistor Q3 is connected to the control terminal A, the drain of the MOS transistor Q3 is connected to the drain of the MOS transistor Q1, and the source of the MOS transistor Q3 is grounded; Port A of the combiner (5) is connected to the drain of the MOS transistor Q1; The control terminal B of the second control circuit (42) is connected to the flight control computer (10), the power supply terminal of the second control circuit (42) is connected to the boost circuit (13), and the output terminal of the second control circuit (42) is connected to the gate and the source of the MOS transistor Q1; The control terminal C of the third control circuit (43) is connected to the flight control computer (10), the power supply terminal of the third control circuit (43) is connected to the boost circuit (13), and the output terminal of the third control circuit (43) is connected to the gate and the source of the MOS transistor Q2; The control terminal D of the fourth control circuit (44) is connected to the flight control computer (10), the power supply terminal of the fourth control circuit (44) is connected to the boost circuit (13), the gate of the MOS transistor Q4 is connected to the control terminal D, and the drain of the MOS transistor Q4 is connected to the drain of the MOS transistor Q2; Port B of the combiner (5) is connected to the drain of the MOS transistor Q2.

7. An aircraft, characterized in that, The aircraft adopts the aircraft GPS signal combining control circuit according to any one of claims 1-6.

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