CN113241586B - Output stable optical power control method for spacecraft optical transceiver module - Google Patents
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- CN113241586B CN113241586B CN202110425165.3A CN202110425165A CN113241586B CN 113241586 B CN113241586 B CN 113241586B CN 202110425165 A CN202110425165 A CN 202110425165A CN 113241586 B CN113241586 B CN 113241586B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01S—DEVICES USING THE PROCESS OF LIGHT AMPLIFICATION BY STIMULATED EMISSION OF RADIATION [LASER] TO AMPLIFY OR GENERATE LIGHT; DEVICES USING STIMULATED EMISSION OF ELECTROMAGNETIC RADIATION IN WAVE RANGES OTHER THAN OPTICAL
- H01S5/00—Semiconductor lasers
- H01S5/06—Arrangements for controlling the laser output parameters, e.g. by operating on the active medium
- H01S5/068—Stabilisation of laser output parameters
- H01S5/0683—Stabilisation of laser output parameters by monitoring the optical output parameters
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01S—DEVICES USING THE PROCESS OF LIGHT AMPLIFICATION BY STIMULATED EMISSION OF RADIATION [LASER] TO AMPLIFY OR GENERATE LIGHT; DEVICES USING STIMULATED EMISSION OF ELECTROMAGNETIC RADIATION IN WAVE RANGES OTHER THAN OPTICAL
- H01S5/00—Semiconductor lasers
- H01S5/06—Arrangements for controlling the laser output parameters, e.g. by operating on the active medium
- H01S5/068—Stabilisation of laser output parameters
- H01S5/06804—Stabilisation of laser output parameters by monitoring an external parameter, e.g. temperature
Abstract
The invention discloses an output stable optical power control method for an optical transceiver component of a spacecraft, which comprises the following steps: the method comprises the following steps: reading the working state information of the optical assembly under the preset APC working mode; step two: judging whether the working state information of the optical assembly is normal working state information or abnormal working state information; step three: for the normal working state information, keeping the current preset APC working mode, and reading the working state information of the optical assembly; preferentially sending a complete machine reset instruction for the abnormal working state information, if the abnormal working state is removed, keeping the current preset APC working mode, and reading the working state information of the optical assembly; and if the abnormal state is not released, switching to an open loop power compensation working mode. The invention improves the reliability and service life of the optical assembly during the on-track operation.
Description
Technical Field
The invention belongs to the technical field of spacecraft optical transceiver components, and particularly relates to an output stable optical power control method for a spacecraft optical transceiver component.
Background
The optical transceiver module is a high-speed communication carrier designed based on photoelectric and electro-optical conversion principles. The method has the advantages of high communication speed, long transmission distance, good stability and the like, and is widely applied to the fields of enterprise networking, operator networks, cloud computing local area networks and the like at present.
With the continuous popularization and application of optical components in the aerospace field, the reliability and the service life of the optical components are greatly concerned by the industry. Whether the stable output light power can be obtained is an important index for measuring the service life and the reliability of the optical component.
Currently, the optical module (or called as optical module) used in the industrial field generally adopts a single control mode in the aspect of output optical power control, i.e. an APC (automatic power control) mode or an open-loop control mode. The two operation modes are both to maintain the stability of the output optical power by controlling the laser operation current, but are different in control mechanism. In the APC working mode, a closed-loop control system is formed among a laser (TOSA), a drive circuit and a feedback circuit, and the bias current of the laser is feedback-controlled by setting the working current of a backlight diode under the condition of preset parameters, so that stable optical power output is obtained. As shown in fig. 1. Under a long-time working state, in addition to the change of the environmental temperature, the self parameters of the backlight PD diode drift, and further the feedback circuit works abnormally (such as oscillation and overshoot), even fails. This directly affects the stability of the optical power delivered by the laser. Aiming at the fault phenomenon, the method of directly replacing the optical assembly is adopted in the industrial field for remedying, and in the aerospace field, particularly in an unmanned spacecraft, the optical assembly cannot be manually replaced, the replacement is limited by the influence of space environment and the convenience of replacement, and the replacement cost and the cost are difficult to bear. In addition, in the open-loop operation mode, the light emitting efficiency of the Laser Diode (LD) may decrease gradually with time and temperature, which in turn may cause the optical power output by the optical module to decrease. In order to compensate for this "aging" tendency, a temperature compensation method is usually adopted, i.e. a relationship between temperature and preset optical power is fitted in a full temperature working range, and an open-loop temperature compensation function is realized inside a microprocessor (or an upper computer). The problem that the fitting precision is different from the actual working condition is that how to accurately realize stable optical power output and the fitting precision control is required to be higher.
Disclosure of Invention
The invention solves the technical problems that: the method can automatically switch to the open-loop power compensation working mode after the closed-loop control mode fails, so that the reliability and the service life of the optical assembly during the in-orbit working period are improved.
The purpose of the invention is realized by the following technical scheme: an output stabilized optical power control method for an optical transceiver component of a spacecraft, the method comprising the steps of: the method comprises the following steps: reading the working state information of the optical assembly under the preset APC working mode; step two: judging whether the working state information of the optical assembly is normal working state information or abnormal working state information; step three: for the normal working state information, keeping the current preset APC working mode, and reading the working state information of the optical assembly; preferentially sending a complete machine reset instruction for the abnormal working state information, if the abnormal working state is removed, keeping the current preset APC working mode, and reading the working state information of the optical assembly; and if the abnormal state is not released, switching to an open loop power compensation working mode.
In the above method for controlling output stabilized optical power of an optical transceiver module of a spacecraft, in the first step, the optical module includes a microprocessor, a laser driving circuit, a capacitor C1, a capacitor C2 and a laser TOSA; the microprocessor is connected with the laser driving circuit; the OUT + end of the laser driving circuit is connected with the TOSA through a capacitor C1; the OUT-end of the laser driving circuit is connected with the TOSA through a capacitor C2; the IBIAS end of the laser driving circuit is connected with the TOSA; the IMON end of the laser driving circuit is connected with the TOSA.
In the method for controlling the output stable optical power of the optical transceiver module of the spacecraft, the laser TOSA comprises an LD diode and a PD diode; the anode of the LD diode is respectively connected with the cathode of the PD diode and a capacitor C1;
the cathode of the LD diode is connected with the capacitor C2;
the cathode of the LD diode is connected with the IBIAS end of the laser driving circuit;
and the anode of the PD diode is connected with the IMON end of the laser driving circuit.
In the method for controlling the output stable optical power of the optical transceiver module of the spacecraft, in the first step, the operating state information of the optical module includes a bias current, a feedback current and an operating temperature.
In the method for controlling the output stable optical power of the spacecraft optical transceiver module, in the second step, when the bias current is 10 mA-120 mA, the information is in a normal working state.
In the method for controlling the output stable optical power of the spacecraft optical transceiver module, in the second step, when the feedback current is 0 mA-1 mA, the feedback current is normal working state information.
In the method for controlling the output stable optical power of the optical transceiver component of the spacecraft, in the second step, when the working temperature is-40 ℃ to 85 ℃, the information is the normal working state information.
In the method for controlling the output stable optical power of the optical transceiver component of the spacecraft, the laser driving circuit comprises a temperature sensor, the temperature sensor can measure the working temperature of the optical component, and the microprocessor reads the working temperature of the optical component.
In the method for controlling the output stable optical power of the optical transceiver module of the spacecraft, in the third step, in an open loop power compensation working mode, the linear relation between the temperature and the output optical power is fitted by a least square method in advance, and the optical power compensation is performed according to a preset temperature lookup table, so that the effect of stable output of the optical power is achieved.
Compared with the prior art, the invention has the following beneficial effects:
The invention adopts a control mode of combining closed-loop Automatic Power Control (APC) and open-loop power compensation for the output light power of the light assembly, thereby avoiding the risk of single-point failure of the spacecraft.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic diagram of an electrical circuit of an optical assembly provided by an embodiment of the present invention;
FIG. 2 is a flow chart of an optical power output control scheme provided by an embodiment of the present invention;
fig. 3 is a graph illustrating a variation curve between optical power and aging duration according to an embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 2 is a flowchart of an optical power output control method according to an embodiment of the present invention. As shown in fig. 2, the method comprises the steps of:
the method comprises the following steps: reading the working state information of the optical assembly under the preset APC working mode;
step two: judging whether the working state information of the optical assembly is normal working state information or abnormal working state information;
step three: for the normal working state information, keeping the current preset APC working mode, and reading the working state information of the optical assembly; preferentially sending a complete machine reset instruction for the abnormal working state information, if the abnormal working state is removed, keeping the current preset APC working mode, and reading the working state information of the optical assembly; and if the abnormal state is not released, switching to an open loop power compensation working mode.
In step one, as shown in fig. 1, the optical assembly includes a microprocessor, a laser driving circuit, a capacitor C1, a capacitor C2, and a laser TOSA; the microprocessor is connected with the laser driving circuit; the OUT + end of the laser driving circuit is connected with the TOSA through a capacitor C1; the OUT-end of the laser driving circuit is connected with the TOSA through a capacitor C2; the IBIAS end of the laser driving circuit is connected with the TOSA; the IMON end of the laser driving circuit is connected with the TOSA.
The microprocessor is used for realizing parameter configuration and related control algorithm of the laser driving circuit; the laser driving circuit is mainly used for providing working current (bias current and modulation current) required by the laser; the feedback unit is used for realizing closed-loop Automatic Power Control (APC) of the laser; and a laser (TOSA) is used as a light-emitting element and used for outputting optical signals to complete the electro-optical conversion function.
The control method of the invention has a flow chart as shown in fig. 2, and comprises the following main steps:
(1) presetting an initial operating mode to a closed loop Automatic Power Control (APC) mode
After the optical assembly is powered on and reset, the microprocessor sets initialization parameters of a laser driving circuit through a bus interface (such as I2C, SPI, UART), wherein the working mode of the driving circuit is set as closed-loop Automatic Power Control (APC), and sets a working current threshold of the laser (bias current in FIG. 1) and a working current threshold of a backlight detection diode (PD diode in FIG. 1).
(2) The microprocessor initiates the monitoring of the operational status of the optical assembly transmission link. Including the threshold current, operating temperature, and other status information of step (1). Classifying according to the monitoring state information, wherein the state information comprises normal working state information and abnormal working state information, and the abnormal working state information comprises: and the laser bias current abnormity warning and the backlight detection circuit current abnormity warning are carried out.
(3) Optical module working mode switching mechanism
According to the state information monitored by the microprocessor, keeping the current preset APC working mode for the normal working state information, and regularly reading the working state information of the optical assembly; for abnormal working state information, preferably sending a complete machine reset instruction, if the abnormal working state is relieved, keeping the current preset APC working mode, and regularly reading the working state information of the optical assembly; and if the abnormal state is not released, switching to an open loop power compensation working mode. Under the open-loop mode, the linear relation between the temperature and the output optical power is fitted by a least square method in advance, and the optical power compensation is carried out by means of a temperature lookup table, so that the effect of stable output of the optical power is achieved.
Examples
In order to verify the on-orbit working effect of the invention, the service life of the product is estimated by carrying out a high-temperature (80 ℃) accelerated aging test on the optical assembly. The number of the test samples is 3, and the working modes are respectively as follows:
sample 1: APC working mode;
sample 2: open loop operating mode (no power compensation mechanism);
sample 3: the APC working mode and the open loop power compensation are combined to control;
in the test process, the output light power index test is carried out on 3 samples every 120 hours, and the current value is recorded. Statistically, the variation curve between the output light power and the aging period is shown in fig. 3. It is clear from the graph that the output light power of the sample 3 has a gentle trend, and the light power is attenuated less in the aging period.
According to the mathematical model of the Bellcore standard about the aging test of the semiconductor light emitting device, the aging time variation law of the output light power of the optical assembly can be represented by the following formula:
p＝p 0 +βt (1)
in the formula P 0 The output optical power of the optical component before aging, P the output optical power after aging, t the aging time, and beta the degradation rate. The degradation rate can be approximated by the formula:
β＝β 0 exp[(-E a /KT)] (2)
in the formula beta 0 Is a constant, E a K is the boltzmann constant and T is the junction temperature for the activation energy of the optical component degradation.
According to the data analysis of figure 1, the aging rate beta of the optical component under high temperature stress is calculated by fitting the formula (1), and the service life t of the optical component under high temperature is extrapolated h At T 1 And T 2 Aging rate of two high-temperature stress conditions in obtaining two high-temperature stressesβ 1 And beta 2 Obtaining the activation energy E of the optical component according to the formula (2) a ：
Finally, according to the obtained activation energy E a And high temperature life t h To estimate the normal working condition (T) of the light-emitting component 0 298K, 25 deg.C) working life t 0 ：
Through calculation, under the working condition of normal temperature (25 ℃) and normal pressure, the estimated service life of 3 samples is as follows:
TABLE 1 life estimation table for sample of optical assembly
| Sample1 | Sample2 | Sample3 | |
| Service life (h) | ≈19342.22h | ≈59240.69h | ≈142403.08 |
As can be seen from Table 1, sample 3 has the longest service life, about 142403.08h ≈ 16.256 years; the service life of sample 1 is the shortest, about 19342.22h ≈ 2.207 years; second, the life of sample 1 is about 59240.69h h ≈ 6.76 years. Therefore, the invention is an effective means for stabilizing the optical power control by using the output of the optical transceiver component of the spacecraft.
The invention adopts a control mode of combining closed-loop Automatic Power Control (APC) and open-loop power compensation for the output light power of the light assembly, thereby avoiding the risk of single-point failure of the spacecraft.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (8)
1. An output stabilized optical power control method for an optical transceiver component of a spacecraft, the method comprising the steps of:
the method comprises the following steps: reading the working state information of the optical assembly under the preset APC working mode;
step two: judging whether the working state information of the optical assembly is normal working state information or abnormal working state information; wherein, the abnormal working state information includes: the laser bias current abnormity warning and the backlight detection circuit current abnormity warning;
Step three: for the normal working state information, keeping the current preset APC working mode, and reading the working state information of the optical assembly; preferentially sending a complete machine reset instruction for the abnormal working state information, if the abnormal working state is removed, keeping the current preset APC working mode, and reading the working state information of the optical assembly; if the abnormal state is not released, switching to an open loop power compensation working mode; wherein, the first and the second end of the pipe are connected with each other,
in the third step, in the open loop power compensation working mode, the linear relation between the temperature and the output optical power is fitted by a least square method in advance, and the optical power compensation is carried out according to a preset temperature lookup table, so that the effect of stable output of the optical power is achieved.
2. The output stabilizing optical power control method for an optical transceiver component of a spacecraft of claim 1, wherein: in step one, the optical assembly comprises a microprocessor, a laser driving circuit, a capacitor C1, a capacitor C2 and a laser TOSA; wherein the content of the first and second substances,
the microprocessor is connected with the laser driving circuit;
the OUT + end of the laser driving circuit is connected with the TOSA through a capacitor C1;
the OUT-end of the laser driving circuit is connected with the TOSA through a capacitor C2;
The IBIAS end of the laser driving circuit is connected with the TOSA;
the IMON end of the laser driving circuit is connected with the TOSA.
3. The output stabilizing optical power control method for an optical transceiver component of a spacecraft of claim 2, wherein: the laser TOSA comprises an LD diode and a PD diode; wherein, the first and the second end of the pipe are connected with each other,
the anode of the LD diode is respectively connected with the cathode of the PD diode and the capacitor C1;
the cathode of the LD diode is connected with the capacitor C2;
the cathode of the LD diode is connected with the IBIAS end of the laser driving circuit;
and the anode of the PD diode is connected with the IMON end of the laser driving circuit.
4. The output stabilizing optical power control method for an optical transceiver component of a spacecraft of claim 2, wherein: in step one, the optical component operating state information comprises a bias current, a feedback current and an operating temperature.
5. The method of claim 4 for output stabilizing optical power control of an optical transceiver component of a spacecraft, wherein: in the second step, when the bias current is 10 mA-120 mA, the information is the normal working state information.
6. The method of claim 4 for output stabilizing optical power control of an optical transceiver component of a spacecraft, wherein: in the second step, when the feedback current is 0 mA-1 mA, the information is normal working state information.
7. The method of claim 4 for output stabilizing optical power control of an optical transceiver component of a spacecraft, wherein: in the second step, when the working temperature is-40 ℃ to 85 ℃, the information is the normal working state information.
8. The output stabilizing optical power control method for an optical transceiver component of a spacecraft of claim 2, wherein: the laser driving circuit comprises a temperature sensor, the temperature sensor can measure the working temperature of the optical assembly, and the microprocessor reads the working temperature of the optical assembly.
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