CN115877894A - High-reliability liquid floating gyroscope starting control system and method for aerospace - Google Patents
High-reliability liquid floating gyroscope starting control system and method for aerospace Download PDFInfo
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- CN115877894A CN115877894A CN202310101936.2A CN202310101936A CN115877894A CN 115877894 A CN115877894 A CN 115877894A CN 202310101936 A CN202310101936 A CN 202310101936A CN 115877894 A CN115877894 A CN 115877894A
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Abstract
The invention relates to a liquid floating gyro starting control system and method, in particular to a high-reliability liquid floating gyro starting control system and method for aerospace, and mainly solves the problem that an existing liquid floating gyro is easy to damage when being started under the working condition of low environmental temperature. The starting control system comprises N input power sources Vin and N starting control circuits, wherein N is more than or equal to 1; the input ends of the N starting control circuits are respectively connected with the N input power sources Vin, and the output ends of the N starting control circuits are respectively used for being connected with the N liquid floating gyros to be started; when N =1, starting the control circuit to control the liquid floating gyro to be heated firstly, then closing the liquid floating gyro after preset closing time, and starting the liquid floating gyro after preset starting time; when N is larger than 1, N starting control circuits simultaneously control N liquid floating gyros to be heated at the same time, then the liquid floating gyros are closed in sequence after respective preset closing time, and finally the liquid floating gyros are started in sequence after respective preset starting time.
Description
Technical Field
The invention relates to a liquid floating gyro starting control system and method, in particular to a high-reliability liquid floating gyro starting control system and method for aerospace.
Background
The liquid floating gyroscope is a sensitive instrument which does not depend on external information and autonomously measures the attitude of a carrier, and is widely applied to the fields of satellites, spaceships, space stations and the like due to the advantages of mature technology, high precision and the like of the liquid floating gyroscope; the existing liquid floating gyroscope is divided into three types, namely a classic liquid floating gyroscope, a two-floating gyroscope and a three-floating gyroscope, wherein the two-floating gyroscope is most widely applied due to higher comprehensive precision, service life and reliability.
As shown in fig. 1-3, which are typical structure diagrams of a conventional two-floating gyroscope, the two-floating gyroscope includes a dynamic pressure motor 1, a frame 2, a floater 3, a housing 4, an end cover assembly 5, a jewel bearing assembly 6, and a combined sensor 7; spherical shaft points 8 are respectively arranged at two ends of the shell 4, suspension liquid is filled between the floater 3 and the shell 4 of the two-floating gyroscope, the suspension liquid is used for supporting the weight of the whole floater 3, and the spherical shaft points 8 at two ends of the shell 4 only play a positioning role; as shown in fig. 2 and 3, since the gap between the spherical shaft tip 8 and the jewel bearing assembly 6 is small, at normal ambient temperature, the suspension density is high, the viscous drag is high, the buoyancy force on the float 3 is greater than the gravity force, the float 3 is upward relative to the zero position, if the gyroscope is closed at this time, the loop action is intensified at the moment of closing the loop, the float 3 will move to the vicinity of the zero position, and there is a risk that the spherical shaft tip 8 impacts the jewel bearing assembly 6, which is easy to cause damage to the gyroscope, thereby generating abnormal disturbance torque or generating excess, and causing performance reduction or function loss of the gyroscope. Since the density and viscosity of the suspension are inversely proportional to the temperature, i.e., the lower the temperature, the higher the density and viscosity of the suspension, the lower the temperature at startup, and the higher the risk of damage to the spinning top, it is necessary to warm the spinning top at startup.
As shown in fig. 4, it is a circuit diagram of a synchronous start control circuit of a prior art liquid floating gyroscope; when the liquid floating gyroscope begins to be heated, the power supply module supplies power to the servo circuit, and applies current to the torquer through the servo circuit to realize the closed circuit of the gyroscope; meanwhile, the power supply of the motor works to apply current to the gyro motor to realize the start of the gyro; however, the starting control mode is to start heating at the same time of the starting of the spinning top, the temperature of the suspension liquid is still low when the spinning top is started, and the risk of damage to the spinning top in the starting process still exists.
In conclusion, when the existing liquid floating gyroscope is started under the working condition of lower environmental temperature, damage is easy to occur.
Disclosure of Invention
The invention aims to solve the technical problem that the existing liquid floating gyroscope is easy to damage when being started under the working condition of lower environmental temperature, and provides a high-reliability liquid floating gyroscope starting control system and method for aerospace.
In order to realize the purpose, the technical scheme adopted by the invention is as follows:
a high-reliability liquid floating gyro starting control system for aerospace is characterized in that: the power supply comprises N input power sources Vin and N starting control circuits, wherein N is more than or equal to 1;
the input ends of the N starting control circuits are respectively connected with N input power sources Vin, and the output ends of the N starting control circuits are respectively used for being connected with N liquid floating gyros to be started;
when N =1, starting the control circuit to control the liquid floating gyro to be heated firstly, then closing the liquid floating gyro after the preset closing time, and starting the liquid floating gyro after the preset starting time;
when N is more than 1, N starting control circuits simultaneously control N liquid floating gyros to be heated at the same time, the N liquid floating gyros are sequentially closed after respective preset closed time, and the N liquid floating gyros are sequentially started after respective preset starting time; the preset closed-circuit time and the preset starting time of the N liquid floating gyros are sequentially increased, and the preset closed-circuit time of the liquid floating gyros is smaller than the preset starting time;
the starting control circuit comprises a temperature control circuit, a power supply module, a servo circuit and a motor power supply;
the input ends of the temperature control circuit, the power supply module and the motor power supply are respectively connected with a corresponding input power Vin, and the output end of the temperature control circuit is used for being connected with a heating plate in a corresponding liquid floating gyro to control the liquid floating gyro to be heated;
a first signal output end S1 of the control circuit is connected with a signal end of a power supply module, an output end of the power supply module is connected with an input end of a servo circuit, and an output end of the servo circuit is used for being connected with a torquer in a corresponding liquid floating gyroscope to control the closed circuit of the liquid floating gyroscope;
and a second signal output end S2 of the control circuit is connected with a signal end of a motor power supply, and an output end of the motor power supply is used for being connected with a gyro motor in the corresponding liquid-floated gyro to control the liquid-floated gyro to be started.
Further, the control circuit comprises an auxiliary power supply circuit and a delay circuit;
the auxiliary power supply circuit is used for supplying power to the delay circuit;
the first signal output end S1 of the delay circuit is connected with the signal end of the power supply module and used for sending a signal to the power supply module after the preset closed-circuit time; the second signal output end S2 is connected with a signal end of the motor power supply and used for sending a signal to the motor power supply after the preset starting time.
Further, the auxiliary power supply circuit comprises a resistor R7, a resistor R8, a triode D11 and a zener diode D10;
one end of each of the resistor R7 and the resistor R8 is connected with a corresponding input power Vin, the other end of the resistor R7 is connected with the cathode of the voltage stabilizing diode D10 and the base of the triode D11 respectively, the other end of the resistor R8 is connected with the collector of the triode D11, the anode of the voltage stabilizing diode D10 is grounded, and the emitter of the triode D11 is connected with the delay circuit.
Further, the delay circuit includes a counter D1, a diode D2, a transistor D3, a diode D4, a transistor D5, a diode D6, a diode D7, a diode D8, a transistor D9, a resistor R1, a resistor R2, a resistor R3, a resistor R4, a resistor R5, a resistor R6, a capacitor C1, and a capacitor C2;
the model of the counter D1 is 4060;
one end of the capacitor C1 is connected to an emitter of a transistor D11, and is connected to one end of a resistor R5 and a pin 16 of the counter D1, the other end of the capacitor C1 is connected to one end of a resistor R1 and a pin 12 of the counter D1, the other end of the resistor R1 is grounded, one end of the resistor R2 is connected to a pin 11 of the counter D1 and a pin 9 of the counter D1, the other end of the resistor R2 is connected to one end of a resistor R3 and one end of the capacitor C2, the other end of the resistor R3 is connected to a pin 10 of the counter D1, the other end of the capacitor C2 is connected to a pin 9 of the counter D1, an anode of the diode D2 is connected to one end of a resistor R4, a pin 3 of the counter D1, and an anode of a diode D6, the other end of the resistor R4 is connected to a base of the transistor D3, an emitter of the counter D3 is grounded, the emitter of the transistor D5 is connected to an anode of the transistor D3, the transistor D5 is connected to an emitter of the transistor D5, a collector of the transistor D5 is used as a second signal output terminal S2, and is connected to a power supply terminal of the counter D7, the cathode of the counter D6 is connected to a pin 9D 8 of the diode D1, the ground, the resistor R1 is connected to a signal output terminal of the diode D8, the ground, the resistor R1, the diode D6 is connected to a cathode of the resistor R1, and a cathode of the ground, the diode D6 is connected to a signal output terminal of the resistor R1, the ground, the diode D8 is connected to a signal output terminal of the resistor R1, and a cathode of the ground, the diode D6 of the ground, the resistor R1, the resistor R8 is connected to a cathode of the ground, the resistor R1, the resistor R8 is connected to a signal output terminal of the ground, and a cathode of the ground, the resistor R1, the ground, the diode D6 of the ground, the cathode of the ground, the resistor R1, the cathode of the resistor R1, the resistor R8 of the ground, the resistor R1 is connected to the ground, the resistor R1, the resistor R8 is connected to the cathode of the ground, and a diode D6 of the ground, and a signal output terminal of the ground, the resistor R8 of the ground, the ground of the resistor R1, the resistor R8 of the ground, the resistor R1 is connected to the ground terminal of the resistor R1.
Furthermore, the number of the input power Vin and the number of the starting control lines are both 3, and the starting control of the 3 liquid floating gyros are realized.
Meanwhile, the invention also provides a high-reliability aerospace liquid floating gyroscope starting control method, and the high-reliability aerospace liquid floating gyroscope starting control system comprises the following steps:
and 4, finishing the starting control of the liquid floating gyroscope.
Compared with the prior art, the invention has the beneficial effects that:
1. the liquid floating gyroscope is controlled to be heated firstly by directly applying current to the heating sheet under the action of the input power supply through the arranged temperature control circuit, the arranged control circuit can control the power supply module to apply current to the torquer through the servo circuit after the preset closed-circuit time, the closed circuit of the liquid floating gyroscope is controlled, the arranged control circuit can control the motor power supply to apply current to the gyroscope motor after the preset starting time, the liquid floating gyroscope is controlled to be started, and the aims of heating, then closing and finally starting the liquid floating gyroscope are fulfilled, so that the damage caused by starting the liquid floating gyroscope in a low-temperature environment is avoided; meanwhile, the invention designs an independent starting control circuit and an input power Vin for each liquid floating gyro, so that each liquid floating gyro is independent, N liquid floating gyros are set to be closed circuits at different times and started at different times, and the N liquid floating gyros are ensured to have no influence on each other in the starting process.
2. The invention can realize that the current is applied to the gyro motor through the servo circuit after the liquid floating gyro starts to be heated through the preset closed-circuit time control power supply module and the current is applied to the gyro motor through the preset starting time through the arranged auxiliary power supply circuit and the delay circuit, thereby realizing simple and reliable starting control of the liquid floating gyro and reducing the occupied volume of the starting control circuit.
Drawings
FIG. 1 is a schematic structural diagram of a conventional two-floating gyroscope;
FIG. 2 is a schematic view of the mounting of a spherical tip and jewel bearing assembly in a prior art two-floating gyroscope;
FIG. 3 is an enlarged schematic view at A in FIG. 2;
FIG. 4 is a circuit diagram of a synchronous start control of a prior art liquid-floated gyroscope;
FIG. 5 is a circuit diagram of a starting control system of a high-reliability liquid-floating gyroscope for aerospace according to the invention;
FIG. 6 is a timing diagram of the starting control of N floating gyros in the starting control system of the high-reliability aerospace floating gyro;
FIG. 7 is a circuit diagram of a control circuit in an embodiment of a high-reliability liquid-floating gyroscope starting control system for aerospace according to the invention.
In the figure:
the sensor comprises a dynamic pressure motor 1, a frame 2, a floater 3, a shell 4, an end cover 5, a jewel bearing assembly 6, a combined sensor 7 and a spherical shaft tip 8.
Detailed Description
In order to make the objects, advantages and features of the present invention clearer, a high-reliability liquid-floated gyroscope start control system and method for aerospace according to the present invention will be described in detail with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will be more apparent from the following detailed description. It should be noted that: the drawings are in simplified form and are not to precise scale, the intention being solely for the convenience and clarity of illustrating embodiments of the invention; second, the structures shown in the drawings are often part of actual structures.
As shown in FIGS. 5-7, the starting control system for a high-reliability aerospace liquid floating gyroscope of the present invention comprises N input power sources Vin and N starting control circuits, wherein N is greater than or equal to 1; the specific number N of the starting control lines and the input power Vin can be specifically set according to the number of the liquid floating gyros in the corresponding product.
The N starting control circuits and the N input power sources Vin are arranged in a one-to-one correspondence mode, the input ends of the N starting control circuits are respectively connected with the N input power sources Vin, power is supplied to the corresponding starting control circuits through the input power sources Vin, the N starting control circuits and the N liquid floating gyros to be started are arranged in a one-to-one correspondence mode, and the output ends of the N starting control circuits are respectively used for being connected with the N liquid floating gyros to be started; as shown in fig. 6, when N =1, the control circuit is started to control the liquid floating gyro to be heated first, and then to be closed after the preset closing time, and then to be started after the preset starting time; when N is more than 1, N starting control circuits simultaneously control N liquid floating gyros to be heated at the same time, the N liquid floating gyros are sequentially closed after respective preset closed-loop time, and the N liquid floating gyros are sequentially started after respective preset starting time; the preset closed-circuit time of the N liquid floating gyros is increased in sequence, the preset starting time of the N liquid floating gyros is increased in sequence, and the preset closed-circuit time of the liquid floating gyros is smaller than the preset starting time, so that each liquid floating gyro can be started through an independent circuit, and the starting processes are not influenced by each other.
The starting control circuit comprises a temperature control circuit, a power supply module, a servo circuit and a motor power supply; the input ends of the temperature control circuit, the power supply module and the motor power supply are respectively connected with a corresponding input power Vin, the output end of the temperature control circuit is used for being connected with a heating sheet in a corresponding liquid floating gyro to apply current to the heating sheet to control the liquid floating gyro to be heated, suspension in the liquid floating gyro can be heated to a preset temperature, and the phenomenon that the gyro is damaged due to the fact that the temperature of the suspension is too low, the density and the viscosity are too high, and the shaft tip of the gyro is impacted with a jewel bearing assembly when the gyro is started is avoided; a first signal output end S1 of the control circuit is connected with a signal end of the power supply module, an output end of the power supply module is connected with an input end of the servo circuit, an output end of the servo circuit is used for being connected with a torquer in the corresponding liquid floating gyroscope, and after the control circuit passes the preset closed-circuit time, the control circuit applies current to the torquer through the power supply module and the servo circuit to control the closed circuit of the liquid floating gyroscope; the second signal output end S2 of the control circuit is connected with a signal end of the motor power supply, the output end of the motor power supply is used for being connected with a gyro motor in the corresponding liquid floating gyro, after the control circuit is started for a preset time, the control motor power supply applies current to the gyro motor, and the liquid floating gyro is controlled to be started after the suspension is heated to a preset temperature, so that the liquid floating gyro is prevented from being damaged in the starting process.
The technical scheme of the invention can realize the starting control sequence of heating, closing and starting at first in the application of the liquid floating gyroscope in certain aerospace products, meet the requirements of normal starting and reliable work of the gyroscope under the condition that the environmental temperature is only 2-4 ℃ higher than the solidifying point of the suspension liquid of the liquid floating gyroscope, and ensure that the gyroscope is not damaged in the starting process.
In a preferred embodiment of the invention, as shown in fig. 7, the control circuit comprises a delay circuit and an auxiliary power supply circuit for supplying power to the delay circuit.
The auxiliary power supply circuit comprises a resistor R7, a resistor R8, a triode D11 and a voltage stabilizing diode D10; one end of each of the resistor R7 and the resistor R8 is connected with the corresponding input power Vin, the other end of the resistor R7 is connected with the cathode of the voltage stabilizing diode D10 and the base of the triode D11 respectively, the other end of the resistor R8 is connected with the collector of the triode D11, the anode of the voltage stabilizing diode D10 is grounded, and the emitter of the triode D11 is connected with the delay circuit; the first signal output end S1 of the delay circuit is connected with the signal end of the power supply module, so that a signal can be sent to the power supply module after the preset closed-circuit time; the second signal output end S2 is connected with a signal end of the motor power supply, and can send signals to the motor power supply after preset starting time.
The time delay circuit comprises a counter D1, a diode D2, a triode D3, a diode D4, a triode D5, a diode D6, a diode D7, a diode D8, a triode D9, a resistor R1, a resistor R2, a resistor R3, a resistor R4, a resistor R5, a resistor R6, a capacitor C1 and a capacitor C2; in this embodiment, a counter with a model 4060 is used for illustration, and in other embodiments of the present invention, counters with other models may also be selected according to actual needs, and the circuit may be adaptively adjusted according to different pins of the counter; an emitting electrode of a triode D11 is respectively connected with one end of a capacitor C1, one end of a resistor R5 and a pin 16 of a counter D1, the other end of the capacitor C1 is respectively connected with one end of a resistor R1 and a pin 12 of the counter D1, the other end of the resistor R1 is grounded, one end of a resistor R2 is respectively connected with a pin 11 of the counter D1 and a cathode of a diode D2, the other end of the resistor R2 is respectively connected with one end of a resistor R3 and one end of a capacitor C2, the other end of the resistor R3 is connected with a pin 10 of the counter D1, the other end of the capacitor C2 is connected with a pin 9 of the counter D1, an anode of the diode D2 is connected with one end of a resistor R4, a pin 3 of the counter D1 and an anode of a diode D6, the other end of the resistor R4 is connected with a base electrode of the triode D3, and an emitting electrode of the triode D3 is grounded, the other end of the resistor R5 is connected with a collector of a triode D3 and an anode of a diode D4, a cathode of the diode D4 is connected with a base of the triode D5, an emitting electrode of the triode D5 is grounded, the collector of the triode D5 is used as a second signal output end S2, the collector of the triode D5 is connected with a signal end of a motor power supply, a cathode of a diode D6 is connected with a cathode of a diode D7, a cathode of a diode D8 and one end of a resistor R6, an anode of the diode D7 is connected with a pin 2 of a counter D1, an anode of the diode D8 is connected with a pin 1 of the counter D1, the other end of the resistor R6 is connected with a base of a triode D9, an emitting electrode of a triode D9 is grounded, a collector of a triode D9 is used as a first signal output end S1, a collector of a triode D9 is connected with a signal end of a power supply module, and a pin 8 of the counter D1 is grounded; by arranging the delay circuit, the control power supply module can apply current to the torquer through the servo circuit after the preset closed-circuit time, and the control motor power supply can apply current to the gyro motor after the preset starting time, so that the complexity of the starting control circuit is reduced, the reliability of the starting control circuit is improved, and the high-reliability starting control of the liquid-floated gyro is realized.
In a specific embodiment of the present invention, the input power Vin and the start control circuit are set to be 3, which are used to realize the start control of 3 floating gyros, the preset closed-loop time of the 3 floating gyros is sequentially 7 minutes, 10 seconds, and 7 minutes, 20 seconds, and the preset start time is sequentially 28 minutes, 40 seconds, and 29 minutes, 20 seconds.
The invention discloses a high-reliability aerospace liquid floating gyroscope starting control method, which is based on a high-reliability aerospace liquid floating gyroscope starting control system and comprises the following steps:
and 4, finishing the starting control of the liquid floating gyroscope.
Claims (6)
1. The utility model provides a high reliable aerospace is with liquid floating top start control system which characterized in that: the power supply comprises N input power sources Vin and N starting control circuits, wherein N is more than or equal to 1;
the input ends of the N starting control circuits are respectively connected with N input power sources Vin, and the output ends of the N starting control circuits are respectively used for being connected with N liquid floating gyros to be started;
when N =1, starting the control circuit to control the liquid floating gyro to be heated firstly, then closing the liquid floating gyro after the preset closing time, and starting the liquid floating gyro after the preset starting time;
when N is more than 1, N starting control circuits simultaneously control N liquid floating gyros to be heated at the same time, the N liquid floating gyros are sequentially closed after respective preset closed-loop time, and the N liquid floating gyros are sequentially started after respective preset starting time; the preset closed-circuit time and the preset starting time of the N liquid floating gyros are sequentially increased, and the preset closed-circuit time of the liquid floating gyros is smaller than the preset starting time;
the starting control circuit comprises a temperature control circuit, a power supply module, a servo circuit and a motor power supply;
the input ends of the temperature control circuit, the power supply module and the motor power supply are respectively connected with a corresponding input power Vin, and the output end of the temperature control circuit is used for being connected with a heating plate in a corresponding liquid floating gyro to control the liquid floating gyro to be heated;
the first signal output end S1 of the control circuit is connected with the signal end of the power supply module, the output end of the power supply module is connected with the input end of the servo circuit, and the output end of the servo circuit is used for being connected with a torquer in the corresponding liquid floating gyro to control the closed circuit of the liquid floating gyro;
and a second signal output end S2 of the control circuit is connected with a signal end of a motor power supply, and an output end of the motor power supply is used for being connected with a gyro motor in the corresponding liquid-floated gyro to control the liquid-floated gyro to be started.
2. The starting control system of the high-reliability liquid-floated gyroscope for aerospace according to claim 1, is characterized in that: the control circuit comprises an auxiliary power supply circuit and a delay circuit;
the auxiliary power supply circuit is used for supplying power to the delay circuit;
the first signal output end S1 of the delay circuit is connected with the signal end of the power supply module and used for sending a signal to the power supply module after the preset closed-circuit time; the second signal output end S2 is connected with a signal end of the motor power supply and used for sending a signal to the motor power supply after the preset starting time.
3. The starting control system of the high-reliability liquid-floated gyroscope for aerospace according to claim 2, characterized in that:
the auxiliary power supply circuit comprises a resistor R7, a resistor R8, a triode D11 and a voltage stabilizing diode D10;
one end of each of the resistor R7 and the resistor R8 is connected with the corresponding input power Vin, the other end of the resistor R7 is connected with the cathode of the voltage stabilizing diode D10 and the base of the triode D11, the other end of the resistor R8 is connected with the collector of the triode D11, the anode of the voltage stabilizing diode D10 is grounded, and the emitter of the triode D11 is connected with the delay circuit.
4. The starting control system of the high-reliability liquid-floated gyroscope for aerospace according to claim 3, wherein: the time delay circuit comprises a counter D1, a diode D2, a triode D3, a diode D4, a triode D5, a diode D6, a diode D7, a diode D8, a triode D9, a resistor R1, a resistor R2, a resistor R3, a resistor R4, a resistor R5, a resistor R6, a capacitor C1 and a capacitor C2;
the model of the counter D1 is 4060;
one end of the capacitor C1 is connected with an emitting electrode of a triode D11 and is connected with one end of a resistor R5 and a pin 16 of the counter D1, the other end of the capacitor C1 is respectively connected with one end of a resistor R1 and a pin 12 of the counter D1, the other end of the resistor R1 is grounded, one end of the resistor R2 is respectively connected with a pin 11 of the counter D1 and a cathode of a diode D2, the other end of the resistor R2 is respectively connected with one end of a resistor R3 and one end of the capacitor C2, the other end of the resistor R3 is connected with a pin 10 of the counter D1, the other end of the capacitor C2 is connected with a pin 9 of the counter D1, an anode of the diode D2 is connected with one end of a resistor R4, a pin 3 of the counter D1 and an anode of a diode D6, the other end of the resistor R4 is connected with a base electrode of a triode D3, and an emitting electrode of the triode D3 is grounded, the other end of the resistor R5 is connected with a triode D3 collector and a diode D4 anode, a diode D4 cathode is connected with a triode D5 base, a triode D5 emitting electrode is grounded, the triode D5 collector is used as a second signal output end S2 and is connected with a signal end of a motor power supply, a diode D6 cathode is connected with a diode D7 cathode, a diode D8 cathode and one end of a resistor R6, a diode D7 anode is connected with a pin 2 of the counter D1, a diode D8 anode is connected with a pin 1 of the counter D1, the other end of the resistor R6 is connected with a triode D9 base, a triode D9 emitting electrode is grounded, a triode D9 collector is used as a first signal output end S1 and is connected with a signal end of a power module, and a pin 8 of the counter D1 is grounded.
5. The starting control system of the high-reliability liquid-floated gyroscope for aerospace according to any one of claims 1-4, wherein:
the number of the input power Vin and the number of the starting control circuits are 3, and the starting control of the 3 liquid floating gyros are realized.
6. A high-reliability aerospace liquid floating gyroscope starting control method is based on any one of claims 1-5, and is characterized by comprising the following steps:
step 1, applying current to a starting control circuit through an input power Vin, and when N =1, applying current to a heating sheet in a liquid floating gyro by a temperature control circuit in the starting control circuit to control the liquid floating gyro to start heating; when N is larger than 1, the temperature control circuits in the N starting control circuits simultaneously apply current to the heating sheets of the corresponding liquid floating gyros to control the N liquid floating gyros to start heating simultaneously;
step 2, a first signal output end S1 of the control circuit sends a signal to a power supply module after a preset closed-circuit time, and when N =1, the power supply module applies current to a torquer in the liquid floating gyro through a servo circuit to control the liquid floating gyro to be closed-circuit; when N is larger than 1, the preset closed-circuit time of the N liquid floating gyros is increased in sequence, and the power supply modules in the N starting control circuits apply current to the torquers in the corresponding liquid floating gyros in sequence through the corresponding servo circuits to control the N liquid floating gyros to be closed in sequence;
step 3, a second signal output end S2 of the control circuit sends a signal to a motor power supply after preset starting time, and when N =1, the motor power supply applies current to a gyro motor in the liquid floating gyro to control the liquid floating gyro to start; when N is larger than 1, the preset starting time of the N liquid floating gyros is increased in sequence, and the motor power supplies in the N starting control circuits apply current to the gyro motors in the corresponding liquid floating gyros in sequence to control the N liquid floating gyros to start in sequence;
and 4, finishing the starting control of the liquid floating gyroscope.
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| CN202310101936.2A CN115877894B (en) | 2023-02-13 | 2023-02-13 | System and method for controlling starting of liquid floating gyroscope for aerospace |
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| CN202310101936.2A CN115877894B (en) | 2023-02-13 | 2023-02-13 | System and method for controlling starting of liquid floating gyroscope for aerospace |
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| CN115877894B CN115877894B (en) | 2023-06-27 |
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Citations (13)
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