An aircraft steering gear rudder lock unlocking control circuit

Abstract

The present invention provides a control circuit for unlocking a servo and rudder lock of an aircraft (such as a missile, a drone, etc.). The circuit of the present invention is suitable for aircraft with servo locking torque requirements. The circuit of the present invention comprises a servo lock voltage acquisition circuit, an external command receiving circuit, a logic operation circuit, an isolated DC / DC and its control end circuit, and a multi-energy automatic identification circuit. Based on the characteristics of the aircraft energy system, the present invention makes full use of the servo control power supply and the power supply to design a circuit for unlocking and maintaining the servo and rudder lock in the unlocked state: when the servo is in the working state, the servo lock uses the power supply to unlock the servo, thereby improving the working reliability of the servo lock and avoiding accidents of the aircraft due to failure of the servo lock; when the servo is in the testing state, the servo needs to release the servo lock from the locked state due to testing, and a low-voltage unlocking circuit needs to be designed to meet the user's unlocking needs.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft rudder lock control and relates to an aircraft steering gear rudder lock unlocking control circuit. Background Art

[0002] For safety reasons, aircraft typically require a fixed initial position for their servos, which are maintained by rudder locks. When the aircraft is in test mode (such as ground testing or combat readiness), the servos must be locked; when the aircraft is in operation, the rudder locks must be unlocked. Reliable locking, unlocking, and maintaining the unlocked state of the rudder locks are crucial to the success of the aircraft's mission.

[0003] Working mode: The working mode described in the present invention refers to the mode in which the aircraft relies on its own energy system to complete its work tasks.

[0004] Test mode: The test mode described in the present invention refers to a mode in which the aircraft relies on an external energy source (such as a ground power supply or an aircraft onboard power supply) system to complete functional testing.

[0005] The rudder lock is typically released through electromagnetic attraction. In circuits, the rudder lock is typically equivalent to a resistor and inductor, requiring current to generate the electromagnetic attraction. Therefore, the electrical design must determine the type of rudder lock based on the aircraft's actual operating conditions. When the rudder lock is activated and released, a high current is required to overcome the load torque. Once released, a lower current is required to maintain the release state despite vibration and other conditions. When the servo is in test mode, high load torque release conditions are not required, and the current requirement is relatively low. This characteristic of the rudder lock requires consideration of operating conditions, heat generation, and aircraft energy resources when designing the rudder lock control circuit.

[0006] Depending on the characteristics of the aircraft's energy system, you can usually choose to use low-voltage unlocking (control voltage unlocking) or high-voltage unlocking (power supply unlocking). Low-voltage unlocking and maintaining the unlocked state usually requires a large current, which places high demands on the aircraft's control power supply. In addition, long-term operation of high current can cause heating of the rudder lock. High-voltage unlocking and maintaining the unlocked state can borrow the aircraft's high-voltage power supply. Because the high-voltage power supply has more energy, it can meet the requirements of reliably unlocking and maintaining the unlocked state of the servo when the aircraft is performing a mission. At the same time, the high voltage in the test mode places high demands on testers and test equipment, and consideration should be given to avoiding safety hazards introduced by test equipment or testers. Summary of the Invention

[0007] In response to the above problems, the present invention proposes an aircraft servo lock unlocking control circuit, which fully utilizes the characteristics of the energy system on the aircraft, takes into account the characteristics of the aircraft test mode and working mode, and satisfies the requirements of reliable and safe unlocking of the aircraft servo.

[0008] The technical solution of the present invention is: an aircraft steering gear rudder lock unlocking control circuit, including a rudder lock voltage acquisition circuit, an external command receiving circuit, a logic operation circuit, an isolated DC / DC and its control end circuit, and a multi-energy automatic identification circuit; wherein,

[0009] The steering lock voltage acquisition circuit is connected in parallel with the steering lock, and its acquisition signal is output to the logic operation unit for acquiring the voltage across the steering lock or the voltage across the resistor R1, and converting it into a digital signal through an analog-to-digital converter and transmitting it to the logic operation circuit. This circuit needs to achieve isolation between the steering lock and the steering lock voltage acquisition circuit;

[0010] The external instruction receiving circuit is used to receive external test instructions, adopts a universal RS422 serial communication interface, one end of which is connected to the logic operation circuit;

[0011] The logic operation circuit reads the voltage signal collected by the rudder lock voltage acquisition circuit and the external command signal, and performs logic operation to determine in real time whether the isolated DC / DC control terminal has given an opening control signal; the logic operation circuit is used to logically calculate whether the rudder lock needs the control power supply to participate in the control;

[0012] The isolated DC / DC and its control end circuit are connected to the external control power supply, and are controlled by the control end circuit and output voltage U1; the isolated DC / DC is connected to the control end circuit; the isolated DC / DC and its control end circuit realize isolation and power supply between the control power supply and the rudder lock drive circuit;

[0013] The multi-energy automatic identification circuit is connected to the aircraft's power supply via diodes V1 and V2, and to the aircraft's control power supply via diodes V3 and V4. The multi-energy automatic identification circuit includes a circuit R1 for discharging static electricity in the circuit; the multi-energy automatic identification circuit includes a diode V5 for releasing stored electrical energy in the circuit; the multi-energy automatic identification circuit automatically selects a power supply energy source according to the rudder lock;

[0014] The control power supply and control power supply return line are the control power supply provided by the energy system on the aircraft; the power power supply and power supply return line are the power power provided by the energy system on the aircraft; both power supplies provide the aircraft with the rudder lock unlocking control circuit.

[0015] Preferably, based on the energy characteristics of existing aircraft, taking into account the different needs of aircraft test mode and working mode, the working mode is automatically determined first, and in the working mode, the power supply energy on the aircraft is automatically used to unlock the rudder lock circuit and maintain the unlocked state, thereby ensuring the safety and reliability of the aircraft's mission execution; in the test mode, it can decide whether to open the rudder lock as needed, and use the control power supply to achieve controllable unlocking and maintain the unlocked state of the aircraft's servo rudder lock, thereby reducing the high requirements for test equipment and personnel during aircraft testing.

[0016] Preferably, the rudder lock voltage acquisition circuit includes a voltage divider circuit composed of R10 and R11, which realizes proportional adjustment of the higher rudder lock voltage to a lower voltage. The divided voltage is connected to pin 2 of the linear isolation circuit N10 device through R12; the linear isolation circuit N10 converts the collected rudder lock voltage into a differential voltage of the same proportion through linear isolation transformation, and then obtains the collected voltage analog quantity through proportional operation through the N11 operational amplifier circuit, which is given to the AD converter through the RC aluminum foil network composed of R17 and C13. The analog voltage signal collected by the rudder lock voltage acquisition circuit is converted into a digital signal through the AD converter.

[0017] Preferably, the circuit includes a logic operation circuit to determine the state of the steering lock control terminal, thereby determining whether the control power supply needs to participate in unlocking the steering lock; its basic process is: the logic operation circuit receives the external command function mode description, and at the same time reads the voltage at both ends of the steering lock. When the voltage at both ends of the steering lock is higher than U1+ΔU, where U1 is the rated output voltage of the N1 module and ΔU is the set error, in order to prevent circuit misjudgment and no external command test function description is received, it is determined that the steering lock needs to be in working mode. In this mode, in order to reduce the steering lock's demand for control power energy, it is necessary to turn off the isolated DC / DC N1 through the control end; when the voltage at both ends of the steering lock is higher than U1+ΔU and the external command test function description is received, it is determined that the steering lock needs to be in test mode. In this mode, it is necessary to turn on the isolated DC / DC N1 through the control end; when the voltage at both ends of the steering lock is not higher than U1+ΔU and the external command test function description is received, it is determined that the steering lock needs to be in test mode. In this mode, it is necessary to turn on the isolated DC / DC N1; when the voltage across the rudder lock is not higher than U1+ΔU and no external command test function description is received, it is determined that the rudder lock needs to be in test mode. In this mode, in order to reduce the rudder lock's demand for control power energy, it is necessary to turn off the isolated DC / DC N1 through the control end.

[0018] Preferably, in the test mode, it is capable of determining whether the output voltage of the rudder lock unlocking circuit is successful, and in the working mode, it is capable of monitoring the voltage across the rudder lock in real time.

[0019] Preferably, the isolated DC / DC and its control end circuit, its control end is controlled by a logic operation circuit, and determines whether the isolated DC / DC is turned on or off; the control end circuit is a circuit composed of a photoelectric coupler, and the N2 input end is a current drive signal. When the logic operation circuit outputs a high level, the current passes through the internal light-emitting diode of N2, resulting in a low level at the N1 control end. At this time, N1 is in a closed state, and the control power supply does not output energy to the steering lock; when the logic operation circuit outputs a low level, no current passes through the internal light-emitting diode of N2, resulting in a high level at the N1 control end. At this time, N1 is in an open state, and the control power supply has the conditions to output energy to the steering lock.

[0020] Preferably, the logic operation circuit is a circuit composed of a single chip microcomputer, DSP, FPGA or ARM operation chip.

[0021] Compared with the prior art, the present invention has the following advantages:

[0022] (1) Make full use of the characteristics of the existing energy system of the aircraft and use a power supply as the main control power supply for unlocking the rudder lock to ensure the safety and reliability of the rudder lock unlocking control when the aircraft is in working mode.

[0023] (2) Make full use of the characteristics of the existing energy system of the aircraft and use the control power supply as the auxiliary power supply for unlocking the rudder lock, so that when the rudder lock is in the test mode, the servo has the unlocking control function to meet the needs of aircraft function testing or self-inspection.

[0024] (3) Reduce the risk of aircraft safety hazards caused by test personnel's misoperation during aircraft testing and maintenance. At the same time, by reducing the requirements for test equipment, safety hazards caused by test equipment are avoided, bringing convenience to user testing.

[0025] (4) The working mode has a higher priority level. The circuit has the function of automatically identifying the working mode and gives priority to maintaining the safety and reliability of unlocking the rudder lock.

[0026] (5) The test mode has a lower priority. Under test mode, the aircraft usually only performs functional tests and inspections, reducing the energy demand for test equipment. At the same time, the rudder lock is in a controlled state in test mode, which is conducive to the rational use of limited energy under restricted test conditions.

[0027] (6) The present invention fully utilizes the characteristics of the existing energy system of the aircraft, has a simple circuit design, is easy to implement, occupies a small volume, and is easy to install inside the aircraft or integrate into other circuits for use. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a schematic diagram of the aircraft servo lock unlocking control principle according to an embodiment of the present invention;

[0029] Figure 2 The rudder lock unlocking decision logic of the embodiment of the present invention;

[0030] Figure 3 The control end circuit design of the embodiment of the present invention;

[0031] Figure 4 This is a rudder lock voltage acquisition circuit according to an embodiment of the present invention. DETAILED DESCRIPTION

[0032] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0033] refer to Figure 1 The aircraft steering gear rudder lock unlocking control circuit of the present invention comprises a rudder lock voltage acquisition circuit, an external command receiving circuit, a logic operation circuit, an isolated DC / DC and its control end circuit, and a multi-energy automatic identification circuit; wherein:

[0034] The steering lock voltage acquisition circuit receives the voltage across the steering lock as input and converts the collected analog signal into a digital signal. The output is connected to the logic operation circuit. The logic operation circuit receives the input from the external command receiving circuit and the voltage across the steering lock collected by the steering lock voltage acquisition circuit. After performing a logic operation, the output is sent to the isolated DC / DC and its control circuit, determining whether the isolated DC / DC is on or off. The control circuit receives the isolated DC / DC on / off signal output from the logic operation circuit. After optical isolation, the output determines whether the isolated DC / DC is on or off. The isolated DC / DC input is connected to the control power supply. When the isolated DC / DC is on, the control power supply is able to supply power to the steering lock. When the isolated DC / DC is off, the control power supply is isolated from the steering lock circuit, and no power is supplied to the steering lock. The multi-energy automatic identification circuit actively identifies the isolated DC / DC voltage and power supply status and supplies power to the steering lock, determining whether the steering lock is on or off.

[0035] The rudder lock voltage acquisition circuit collects the voltage at both ends of the rudder lock in real time ( Figure 1 The voltage collected by the rudder lock is fed back to the logic operation circuit. The rudder lock voltage collection circuit includes a resistor divider circuit ( Figure 4 ), the voltage divider circuit consists of R10 and R11. One end of R10 is connected to the high voltage end of the rudder lock (DS-U), one end of R10 is directly connected to R11, and the other end of R11 is connected to the low voltage end of the rudder lock (DS-UH). This circuit adjusts the high voltage at both ends of the rudder lock to a low voltage suitable for circuit processing according to a certain ratio. The rudder lock voltage acquisition circuit includes a linear isolation circuit ( Figure 4N10, C10, C11) in the middle) isolates the rudder lock voltage from the rudder lock voltage collection to avoid crosstalk between circuits. At the same time, the circuit collects the rudder lock voltage (R12 outputs DS-US) and converts it into a differential voltage signal ( Figure 4 The rudder lock voltage acquisition circuit includes a proportional circuit composed of an operational amplifier ( Figure 4 In the circuit, N11, R13, R14, R15, and R16 form the power circuit, which converts the differential output signal from the preceding linear isolation device into a single-ended signal of the same proportion. This signal is then passed through the RC filter circuit formed by R17 and C13 and fed to the analog-to-digital converter (ADC). The ADC converts the resulting rudder lock voltage from analog to digital and outputs it to the logic operation circuit.

[0036] The external command receiving circuit receives the servo working mode and test mode instructions through the communication circuit (serial RS422 is used in this circuit).

[0037] Logic operation circuit ( Figure 1 (middle) The working mode description of receiving the rudder lock voltage collected by the rudder lock voltage collection circuit and the external command receiving circuit input, and through logical operation, it is determined whether the isolated DC / DC is turned on. The specific judgment logic is (reference Figure 2 ): When the voltage at both ends of the rudder lock is higher than U1+ΔU (U1 is the rated output voltage of the N1 module, ΔU is the set error, to prevent circuit misjudgment) and no external command test function description is received, it is determined that the rudder lock needs to be in working mode. In this mode, in order to reduce the rudder lock's demand for control power energy, it is necessary to turn off the isolated DC / DC N1 through the control end; when the voltage at both ends of the rudder lock is higher than U1+ΔU and an external command test function description is received, it is determined that the rudder lock needs to be in test mode. In this mode, it is necessary to turn on the isolated DC / DC N1 through the control end; when the voltage at both ends of the rudder lock is not higher than U1+ΔU and an external command test function description is received, it is determined that the rudder lock needs to be in test mode. In this mode, it is necessary to turn on the isolated DC / DC N1 through the control end; when the voltage at both ends of the rudder lock is not higher than U1+ΔU and no external command test function description is received, it is determined that the rudder lock needs to be in test mode. In this mode, it is necessary to turn on the isolated DC / DC N1 through the control end.

[0038] The isolated DC / DC and its control terminal circuit consists of an isolated DC / DC N1 and its control terminal circuit. The on and off of this circuit is controlled by the logic operation circuit. When the logic operation circuit outputs a high level, the current flows through N2 ( Figure 3) causes the N1 control terminal to appear low, at which point N1 is in the off state, and the control power supply does not output energy to the rudder lock. When the logic operation circuit outputs a low level, no current flows through the N2 internal LED, causing the N1 control terminal to appear high, at which point N1 is in the on state, and the control power supply is able to output energy to the rudder lock.

[0039] The multi-energy automatic identification circuit consists of multiple diodes and resistors. Diodes V1 and V2 connect to the aircraft's power supply, allowing it to output power to the rudder lock. Diodes V3 and V4 connect to the isolated DC / DC output, allowing it to output power from the control power supply to the rudder lock. A logic circuit ultimately determines which power source the rudder lock receives. The circuit includes circuit R1, which discharges static electricity, and diode V5, which releases stored energy from the rudder lock.

[0040] Obviously, those skilled in the art may make various changes and modifications to the invention without departing from the spirit and scope of the invention. Thus, if such changes and modifications fall within the scope of the claims and their equivalents, the present invention is intended to include such changes and modifications.

Claims

1. An aircraft steering gear rudder lock unlocking control circuit, characterized in that: It includes rudder lock voltage acquisition circuit, external command receiving circuit, logic operation circuit, isolated DC / DC and its control end circuit, multi-energy automatic identification circuit; Among them, The steering lock voltage acquisition circuit is connected in parallel with the steering lock, and its acquisition signal is output to the logic operation circuit for acquiring the voltage across the steering lock or the voltage across the resistor R1, and converting it into a digital signal through an analog-to-digital converter and transmitting it to the logic operation circuit. This circuit needs to achieve isolation between the steering lock and the steering lock voltage acquisition circuit; The external instruction receiving circuit is used to receive external test instructions, adopts a universal RS422 serial communication interface, one end of which is connected to the logic operation circuit; The logic operation circuit reads the voltage signal collected by the rudder lock voltage acquisition circuit and the external command signal, and performs logic operation to determine in real time whether the isolated DC / DC control terminal has given an opening control signal; the logic operation circuit is used to logically calculate whether the rudder lock needs the control power supply to participate in the control; The isolated DC / DC and its control end circuit are connected to the external control power supply, and are controlled by the control end circuit and output voltage U1; the isolated DC / DC is connected to the control end circuit; the isolated DC / DC and its control end circuit realize isolation and power supply between the control power supply and the rudder lock drive circuit; The multi-energy automatic identification circuit is connected to the aircraft's power supply via diodes V1 and V2, and to the aircraft's control power supply via diodes V3 and V4. The multi-energy automatic identification circuit includes a circuit R1 for discharging static electricity in the circuit; the multi-energy automatic identification circuit includes a diode V5 for releasing stored electrical energy in the circuit; the multi-energy automatic identification circuit automatically selects a power supply energy source according to the rudder lock; The control power supply and control power supply return line are the control power supply provided by the energy system on the aircraft; the power power supply and power supply return line are the power power provided by the energy system on the aircraft; both power supplies provide the aircraft with the rudder lock unlocking control circuit.

2. The aircraft steering gear rudder lock unlocking control circuit according to claim 1, characterized in that: Based on the energy characteristics of existing aircraft, taking into account the different needs of aircraft test mode and working mode, the system automatically determines the working mode first. In the working mode, it automatically uses the power supply energy on the aircraft to unlock the rudder lock circuit and maintain the unlocked state, ensuring the safety and reliability of the aircraft in executing missions. In test mode, it can decide whether to open the rudder lock as needed, and use the control power supply to achieve controllable unlocking and maintain the unlocked state of the aircraft servo rudder lock, reducing the high requirements for test equipment and personnel during aircraft testing.

3. The aircraft steering gear rudder lock unlocking control circuit according to claim 1, characterized in that: The rudder lock voltage acquisition circuit includes a voltage divider circuit composed of R10 and R11, which adjusts the higher voltage of the rudder lock to a lower voltage in proportion. The divided voltage is connected to pin 2 of the linear isolation circuit N10 device through R12; The linear isolation circuit N10 converts the collected rudder lock voltage into a differential voltage of the same proportion through linear isolation transformation, and then obtains the collected voltage analog quantity through proportional operation through the N11 operational amplifier circuit. The analog quantity is fed to the AD converter through the RC aluminum foil network composed of R17 and C13, and the analog voltage signal collected by the rudder lock voltage collection circuit is converted into a digital signal through the AD converter.

4. The aircraft steering gear rudder lock unlocking control circuit according to claim 1, characterized in that: This circuit includes a logic operation circuit to determine the state of the rudder lock control terminal, thereby determining whether the control power supply needs to participate in unlocking the rudder lock; The basic process is as follows: the logic operation circuit receives the external command function mode description and reads the voltage at both ends of the rudder lock at the same time. When the voltage at both ends of the rudder lock is higher than U1+ΔU, where U1 is the rated output voltage of the N1 module and ΔU is the set error, to prevent circuit misjudgment and no external command test function description is received, it is determined that the rudder lock needs to be in working mode. In this mode, in order to reduce the rudder lock's demand for control power energy, it is necessary to turn off the isolated DC / DC N1 through the control end; when the voltage at both ends of the rudder lock is higher than U1+ΔU and the external command test function description is received, it is determined that the rudder lock needs to be in test mode. In this mode, it is necessary to turn on the isolated DC / DC N1 through the control end; when the voltage at both ends of the rudder lock is not higher than U1+ΔU and the external command test function description is received, it is determined that the rudder lock needs to be in test mode. In this mode, it is necessary to turn on the isolated DC / DC N1 through the control end; when the voltage at both ends of the rudder lock is not higher than U1+ΔU and the external command test function description is received, it is determined that the rudder lock needs to be in test mode. In this mode, it is necessary to turn on the isolated DC / DC N1 through the control end; when the voltage at both ends of the rudder lock is not higher than U1+ΔU and no external command test function description is received, it is determined that the rudder lock needs to be in test mode. In this mode, in order to reduce the rudder lock's demand for control power energy, it is necessary to turn off the isolated DC / DC N1 through the control end.

5. The aircraft steering gear rudder lock unlocking control circuit according to claim 4, characterized in that: In the test mode, it can determine whether the output voltage of the rudder lock unlocking circuit is successful. In the working mode, it can monitor the voltage at both ends of the rudder lock in real time.

6. The aircraft steering gear rudder lock unlocking control circuit according to claim 1, characterized in that: The isolated DC / DC and its control end circuit, the control end of which is controlled by a logic operation circuit and determines whether the isolated DC / DC is turned on or off; the control end circuit is a circuit composed of a photoelectric coupler, and the N2 input end is a current drive signal. When the logic operation circuit outputs a high level, the current passes through the internal light-emitting diode of N2, causing a low level to appear at the control end of N1. At this time, N1 is in a closed state, and the control power supply does not output energy to the steering lock; when the logic operation circuit outputs a low level, no current passes through the internal light-emitting diode of N2, causing a high level to appear at the control end of N1. At this time, N1 is in an open state, and the control power supply is able to output energy to the steering lock.

7. The aircraft steering gear rudder lock unlocking control circuit according to claim 1, characterized in that: The logic operation circuit is a circuit composed of a single chip microcomputer, DSP, FPGA or ARM operation chip.

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