CN211253084U - Drive control circuit of space active sun wing spreading mechanism - Google Patents
Drive control circuit of space active sun wing spreading mechanism Download PDFInfo
- Publication number
- CN211253084U CN211253084U CN201921832863.XU CN201921832863U CN211253084U CN 211253084 U CN211253084 U CN 211253084U CN 201921832863 U CN201921832863 U CN 201921832863U CN 211253084 U CN211253084 U CN 211253084U
- Authority
- CN
- China
- Prior art keywords
- circuit
- dual
- control circuit
- drive control
- position detection
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 44
- 230000007480 spreading Effects 0.000 title claims description 15
- 238000001514 detection method Methods 0.000 claims abstract description 37
- 239000000758 substrate Substances 0.000 claims abstract description 18
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 13
- 230000003993 interaction Effects 0.000 claims abstract description 7
- 230000009467 reduction Effects 0.000 claims abstract description 5
- 230000006870 function Effects 0.000 claims description 28
- 238000004891 communication Methods 0.000 claims description 9
- 230000004044 response Effects 0.000 claims description 8
- 230000009977 dual effect Effects 0.000 claims description 5
- 238000006243 chemical reaction Methods 0.000 claims description 4
- 230000008901 benefit Effects 0.000 abstract description 6
- 238000013461 design Methods 0.000 description 11
- 238000000034 method Methods 0.000 description 10
- 230000008569 process Effects 0.000 description 9
- 230000002159 abnormal effect Effects 0.000 description 5
- 230000007547 defect Effects 0.000 description 5
- 239000002131 composite material Substances 0.000 description 4
- 238000011217 control strategy Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000005381 potential energy Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000003471 anti-radiation Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 230000011218 segmentation Effects 0.000 description 1
- 229910001285 shape-memory alloy Inorganic materials 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Images
Landscapes
- Control Of Position Or Direction (AREA)
Abstract
The present disclosure relates to a drive control circuit for a space active sun wing opening mechanism, the control circuit comprising: the main control chip DSP, main control chip DSP connects double-circuit H bridge pulse width modulation amplifier power drive chip, dual-redundancy CAN bus interface circuit and binary channels position detection circuit, dual-redundancy CAN bus interface circuit carries out the information interaction with the integrated electronic system on the planet, position sensor is connected to binary channels position detection circuit's every passageway position detection circuit, position sensor connects the output shaft, the output shaft connects the reduction gear, reduction gear connection step motor is according to the PWM signal of resolving the corresponding duty cycle of gained control quantity size output. The stepping motor controls the output shaft after being decelerated by the speed reducer, and stops PWM output after the solar wing substrate is unfolded in place. The utility model has the advantages that: the detection precision is high, the mechanism can be repeatedly unfolded, the control precision is high, the operation is stable, and the reliability is high.
Description
Technical Field
The utility model relates to a drive control circuit of space active sun wing spreading mechanism.
Background
With the vigorous development of aerospace industries such as manned aerospace, space station, deep space exploration and the like in China, the spacecraft technology is rapidly developed, the structure of the spacecraft is increasingly complex, the functions are continuously increased, and due to the characteristics of long on-orbit running time and difficulty in replacement, a solar wing unfolding mechanism serving as a power source becomes an important component of the spacecraft. Whether the solar wing can be smoothly unfolded after being in orbit is one of important indexes for measuring success or failure of launching tasks of the spacecraft, so that the guarantee of reliable work of the solar wing is the primary requirement of an unfolding mechanism.
The driving part of the sun wing unfolding mechanism provides a main moment for the movement of the mechanism, and is the core part of the mechanism, and whether the work of the sun wing is reliable or not depends on the selection of a driving control mode to a great extent. The currently common driving method of the sun wing spreading mechanism comprises the following steps: spring actuation, micro-electromechanical actuation, pneumatic actuation and self-extending actuation. At present, the spring is commonly used as a main power source for the engineered solar wing unfolding mechanism to provide unfolding driving energy. When the spacecraft launches or other non-working states, the solar wing base plate is folded in the effective load cabin, and the spring is prestressed to store elastic potential energy; when the spacecraft works, the spring releases elastic potential energy to enable the solar wing substrate to be unfolded.
At present, most of the solar wing unfolding mechanisms applied in domestic engineering adopt passive control, and the solar wings are driven to unfold under the action of springs in hinges. The driving force of the spring is not easy to control, strong collision is easy to generate at the moment of the unfolding ending, the stability of the locking and releasing process is poor, the control precision is low, and the stability control of the flight attitude of the spacecraft is not facilitated. In addition, the mechanism which finishes the unfolding work by releasing potential energy does not always have the folding function, only can realize the functions of unfolding and fixing the angle and locking at a single time, and cannot adjust the angle of the solar wing substrate in real time along with the operation of the spacecraft, thereby ensuring the energy supply of the long-time on-orbit operation of the spacecraft.
The driving defects of the existing solar wing spreading mechanism are mainly shown in the following aspects:
(1) the spring driving mode belongs to passive driving, and because the driving torque of the spring linearly decreases along with the increase of the unfolding angle, in order to ensure that the necessary torque margin is met in the whole unfolding process, the initial torque of the spring must be increased, so that the excessive locking impact load is caused by the residual kinetic energy when the unfolding is finished. The driving mode has the defects of uncontrollable unfolding process, poor stability, incapability of realizing repeated unfolding and the like;
(2) the micro-motor driving mode belongs to active driving, the unfolding and folding of the mechanism are realized by adopting direct current or alternating current motor driving, the driving process is controllable, the operation is stable, the control precision is high, and the movement process is reversible. The driving mode has the defects of consuming satellite limited power resources, causing abnormal work due to volatile effect of components of a circuit system and the like;
(3) the pneumatic driving mode generally adopts flexible film material to manufacture the inflatable unfolding mechanism, adopts the combined action of the driving inflation tube and the inflation guide tube, and has simple structure, strong bearing capacity and high reliability. The driving mode has the defects of unstable unfolding work, slow unfolding process, high air tightness requirement and the like;
(4) the whole structure of the solar wing unfolding mechanism in a self-stretching driving mode is made of special elements or materials such as memory alloy and self-adaptive intelligent elements, can be automatically released and unfolded according to design requirements in a specific environment, and has the defects that the driving mode is only suitable for one-time unfolding, the technology is not mature and the like.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that a space active sun wing spreading mechanism drive control circuit is provided, it can guarantee repeated expansion, improves the reliability effectively.
In order to solve the technical problem, the utility model discloses a technical scheme is: a space active sun wing opening mechanism drive control circuit, comprising: the system comprises a main control chip DSP, a dual-path H-bridge pulse width modulation amplifier power driving chip, a dual-redundancy CAN bus interface circuit and a dual-path position detection circuit, wherein the dual-redundancy CAN bus interface circuit is in information interaction with an onboard integrated electronic system, each path position detection circuit of the dual-path position detection circuit is connected with a position sensor, the position sensor is connected with an output shaft, the output shaft is connected with a speed reducer, and the speed reducer is connected with a stepping motor; the main control chip DSP realizes instruction receiving and response data sending through the dual-redundancy CAN bus interface circuit, and realizes a solar wing substrate position feedback acquisition function and a PWM closed-loop control quantity output function through the dual-channel position detection circuit; and the main control chip DSP realizes the function of driving the stepping motor to rotate by a certain angle in the appointed direction according to the PWM closed-loop control quantity output by the main control chip DSP through the power driving chip of the double-path H-bridge pulse width modulation amplifier.
Compared with the prior art, the utility model discloses following profitable technological effect has:
simple structure includes: the system comprises a main control chip DSP, a dual-path H-bridge pulse width modulation amplifier power driving chip, a dual-redundancy CAN bus interface circuit and a dual-path position detection circuit, wherein the dual-redundancy CAN bus interface circuit is in information interaction with an onboard integrated electronic system, each path position detection circuit of the dual-path position detection circuit is connected with a position sensor, the position sensor is connected with an output shaft, the output shaft is connected with a speed reducer, and the speed reducer is connected with a stepping motor; the main control chip DSP realizes instruction receiving and response data sending through the dual-redundancy CAN bus interface circuit, and realizes a solar wing substrate position feedback acquisition function and a PWM closed-loop control quantity output function through the dual-channel position detection circuit; and the main control chip DSP realizes the function of driving the stepping motor to rotate by a certain angle in the appointed direction according to the PWM closed-loop control quantity output by the main control chip DSP through the power driving chip of the double-path H-bridge pulse width modulation amplifier. Compared with the traditional passive sun wing unfolding mechanism, the two-phase hybrid stepping motor is used as a power source, can realize the function of repeatedly and stably unfolding or folding to any angle in the stroke and locking according to the actual operation requirement of the spacecraft, and has the advantages of high precision, high reliability and the like. When the selected components are all strictly subjected to derating design, the communication and closed loop are both subjected to dual-redundancy control design, and even if part of circuits are in failure, the system can still work normally. In addition, the thermal design and the anti-radiation design of the controller shell further guarantee the working environment of components and parts, and the reliability of the system is improved. The driving control circuit effectively ensures the advantages of repeatable expansion of the mechanism, high control precision, stable operation, high reliability and the like.
Drawings
Fig. 1 is an electrical schematic diagram of a drive control circuit of the space active sun wing spreading mechanism of the present invention;
fig. 2 is a circuit diagram of a two-way H-bridge pwm amplifier power driver chip according to the present invention;
fig. 3 is a flowchart of the driving control circuit of the space active sun wing spreading mechanism of the present invention.
Detailed Description
The present invention will be described in further detail with reference to specific embodiments, but these examples are only illustrative and do not limit the scope of the present invention.
Referring to fig. 1 to 2, the present invention provides a driving control circuit for a space active sun wing spreading mechanism, including: the system comprises a main control chip DSP, a dual-path H-bridge pulse width modulation amplifier power driving chip, a dual-redundancy CAN bus interface circuit and a dual-path position detection circuit, wherein the dual-redundancy CAN bus interface circuit is in information interaction with an onboard integrated electronic system, each path position detection circuit of the dual-path position detection circuit is connected with a position sensor, the position sensor is connected with an output shaft, the output shaft is connected with a speed reducer, and the speed reducer is connected with a stepping motor; the main control chip DSP realizes instruction receiving and response data sending through the dual-redundancy CAN bus interface circuit, and realizes a solar wing substrate position feedback acquisition function and a PWM closed-loop control quantity output function through the dual-channel position detection circuit; and the main control chip DSP realizes the function of driving the stepping motor to rotate by a certain angle in the appointed direction according to the PWM closed-loop control quantity output by the main control chip DSP through the power driving chip of the double-path H-bridge pulse width modulation amplifier.
In one embodiment, the main control chip DSP is further connected to a microswitch control and analog quantity acquisition circuit, and the microswitch control and analog quantity acquisition circuit realizes limit position microswitch control and open/close state information detection.
In one embodiment, the main control chip DSP adopts a domestic digital signal processor with model JDSP 28335.
In one embodiment, the position sensor employs a rotary transformer.
In one embodiment, the dual channel position detection circuit employs a detection circuit with the shaft angle conversion chip FX2S1210 as the core.
In one embodiment, the two-way H-bridge pulse width modulation amplifier power driver chip is of the model number LHKF2703dD 02.
In one embodiment, the stepper motor is a two-phase hybrid stepper motor, and the full step angle is 1.8 °.
In one embodiment, the decelerator employs a deceleration ratio of 90.
In one embodiment, the two-way H-bridge pulse width modulation amplifier power driving chip comprises a dual FET power driving circuit, which is connected with three opto-coupler isolators.
The utility model discloses a control process, include: the control circuit completes initialization after being electrified, starts PWM interruption, and executes position feedback acquisition processing, microswitch control and state acquisition, system instruction information inquiry and closed-loop or open-loop control operation in an interruption function; inquiring command data of CANA and CANB communication interfaces at regular time in PWM interruption, and controlling to finish receiving and judging command data frames when a command arrives; when the instruction is normal, updating the instruction to return response information and executing corresponding operation; when the instruction is abnormal, returning the abnormal information of the instruction and not executing the corresponding operation; when a correct solar wing substrate unfolding angle control instruction is received, the instruction identifier is set, if the position sensor works normally, a bipolar constant-current double-four-beat and subdivision drive control algorithm composite control strategy is adopted to realize system closed loop, the instruction pulse quantity and the solar wing substrate feedback pulse quantity are compared, corrected and processed by a subdivision drive control algorithm, and PWM signals with corresponding duty ratios are output according to the calculated control quantity; if the position sensor works abnormally, open-loop control is carried out according to the opening and closing state of the microswitch and the working characteristics of the stepping motor, and a PWM signal is output; the PWM signal controls the stepping motor to rotate through a power driving chip of a double-path H-bridge pulse width modulation amplifier, the stepping motor realizes the control of an output shaft after being decelerated by a speed reducer, and the PWM output is stopped when the solar wing substrate is unfolded in place; if the instruction is not received, circularly acquiring the information of the position sensor, judging the working state of the position sensor, acquiring the state information of the microswitch and inquiring the receiving instruction;
as specific example, the utility model discloses a: the system comprises a domestic JDSP28335 type digital signal processor, a two-way H-bridge pulse width modulation amplifier power driving chip, a dual-redundancy CAN bus interface circuit, a two-way position detection circuit, a microswitch control and analog quantity acquisition circuit and the like. The main control chip DSP realizes instruction receiving and response data sending through a dual-redundancy CAN bus interface circuit, and realizes a solar wing substrate position feedback acquisition function and a PWM closed-loop control quantity output function according to a dual-channel position detection circuit; the power driving chip realizes the function of driving the stepping motor to rotate by a certain angle in the appointed direction according to the PWM closed-loop control quantity output by the main control chip; the microswitch control and analog quantity acquisition circuit realizes limit position microswitch control and open-close state information detection. The driving control circuit of the present invention is shown in fig. 1. The double-path H-bridge pulse width modulation amplifier has high circuit integration level and a function of prohibiting PWM output, and can effectively reduce the volume of a control circuit and the power consumption of components.
As specific embodiment, the utility model discloses a domestic digital signal processor that the model is JDSP28335 adopts dual-redundancy CAN communication interface circuit and the star to synthesize electronic system and carry out the information interaction.
As specific embodiment, the utility model discloses regard as position sensor with domestic resolver to domestic high accuracy shaft angle conversion chip FX2S1210 detects sun wing base plate position information in real time as the binary channels position detection circuit of core.
As specific embodiment, the utility model discloses carry out the comparison correction according to feedback position pulse volume and instruction pulse volume, through the two four compound control strategy output PWM closed-loop control volume of clapping of bipolar constant current and subdivision control algorithm.
As specific embodiment, the utility model discloses PWM closed-loop control volume drives step motor according to the rotatory certain angle of appointed orientation through double-circuit H bridge pulse width modulation amplifier power drive chip LHKF2703dD02, and step motor drives the output shaft rotation through reduction gears to reach the function of control sun wing base plate angular adjustment.
As specific embodiment, the utility model discloses at two extreme position installation micro-gap switches, when the binary channels position detection circuit trouble, can carry out open loop control according to micro-gap switch's switching state and step motor's operating characteristics, guarantee the normal work of sun wing opening mechanism.
Referring to fig. 3, the working process of the present invention is: the system completes initialization after being electrified, starts PWM interruption, and executes operations of position feedback acquisition processing, microswitch control and state acquisition, system instruction information inquiry, closed-loop or open-loop control and the like in an interruption function. And the software regularly inquires the instruction data of the CANA and CANB communication interfaces in the PWM interruption process, and when an instruction arrives, the control software finishes receiving and judging the instruction data frame. When the instruction is normal, updating the instruction to return response information and executing corresponding operation; and when the instruction is abnormal, returning the abnormal information of the instruction and not executing the corresponding operation. When a correct solar wing substrate unfolding angle control instruction is received, the instruction identifier is set, if the position sensor works normally, a bipolar constant-current double-four-beat and subdivision drive control algorithm composite control strategy is adopted to realize system closed loop, the instruction pulse quantity and the solar wing substrate feedback pulse quantity are compared, corrected and processed by a subdivision drive control algorithm, and PWM signals with corresponding duty ratios are output according to the calculated control quantity; if the position sensor works abnormally, open-loop control is carried out according to the opening and closing state of the microswitch and the working characteristics of the stepping motor, and a PWM signal is output. The PWM signal controls the motor to rotate through the driving chip, the motor controls the output shaft after being decelerated through the deceleration mechanism, and the PWM output is stopped when the solar wing substrate is unfolded in place. If the instruction is not received, the control software circularly collects the information of the position sensor, judges the working state of the position sensor, collects the state information of the microswitch and inquires the receiving instruction.
The utility model adopts a two-phase hybrid stepping motor as a power source, and has certain self-locking capacity when the stepping motor stops rotating, and effectively ensures the running stability and control precision of the system and the locking reliability of the solar wing substrate after the solar wing substrate is in place by matching with a bipolar constant-current double-four-beat and subdivision control algorithm composite control strategy;
the utility model adopts the dual-redundancy CAN bus communication with good real-time performance, high reliability and strong anti-interference capability, takes two eCAN modules integrated by domestic JDSP28335 as communication controllers, has simple circuit and convenient operation, and ensures the reliability of the communication between the solar wing spreading mechanism and the satellite integrated electronic system;
the utility model adopts a domestic rotary transformer which can adapt to the severe environment of the space as a position sensor, a double-channel position detection circuit based on a domestic high-precision shaft angle conversion chip detects the position of the solar wing substrate in real time, the resolution can reach 16bit, the precision is superior to 0.02 degree, and the device has the advantages of high resolution, accurate position information and the like;
the utility model discloses install micro-gap switch at extreme position, when the binary channels position detection circuit is unusual, can carry out system open-loop control according to the micro-gap switch switching state, further guarantee the reliability of system's operation;
the utility model discloses the core chip of circuit all is domestic metal-packaged product, and product quality and reliability are higher, and is better to space environment adaptability, can effectively reduce the failure rate of electronic components under adverse space environment.
The utility model discloses can realize through experimental proof that solar wing opens the function that the mechanism can repeatedly expand arbitrary angle in the stroke, through bipolar constant current two four claps and segmentation drive control algorithm composite control tactics can improve step motor's operation stationarity and control accuracy effectively, guarantee solar wing opens the high accuracy and the high reliability operation of mechanism. All domestic metal package components and parts of selecting for use of this active solar wing spreading mechanism drive control circuit in space, the two-phase hybrid step motor whole step distance angle that spreading mechanism used is 1.8, and structural design has adopted 90 reduction ratio, adopts 4 subdivision drive control on the software, and step motor rotates 1 microstep, and the rotatory 1.8 of solar wing base plate/4/90 become 0.005, can reach 0.005 precision on the solar wing base plate angle control theory promptly. The test result shows, the utility model discloses control accuracy is high, operational reliability is high, maneuverability is strong, transportability is good.
The utility model discloses a following profitable technological effect:
the realization is simple, include: the system comprises a main control chip DSP, a dual-path H-bridge pulse width modulation amplifier power driving chip, a dual-redundancy CAN bus interface circuit and a dual-path position detection circuit, wherein the dual-redundancy CAN bus interface circuit is in information interaction with an onboard integrated electronic system, each path position detection circuit of the dual-path position detection circuit is connected with a position sensor, the position sensor is connected with an output shaft, the output shaft is connected with a speed reducer, and the speed reducer is connected with a stepping motor; the main control chip DSP realizes instruction receiving and response data sending through the dual-redundancy CAN bus interface circuit, and realizes a solar wing substrate position feedback acquisition function and a PWM closed-loop control quantity output function through the dual-channel position detection circuit; and the main control chip DSP realizes the function of driving the stepping motor to rotate by a certain angle in the appointed direction according to the PWM closed-loop control quantity output by the main control chip DSP through the power driving chip of the double-path H-bridge pulse width modulation amplifier. Compared with the traditional passive sun wing unfolding mechanism, the two-phase hybrid stepping motor is used as a power source, can realize the function of repeatedly and stably unfolding or folding to any angle in the stroke and locking according to the actual operation requirement of the spacecraft, and has the advantages of high precision, high reliability and the like. When the selected components are all strictly subjected to derating design, the communication and closed loop are both subjected to dual-redundancy control design, and even if part of circuits are in failure, the system can still work normally. In addition, the thermal design and the anti-radiation design of the controller shell further guarantee the working environment of components and parts, and the reliability of the system is improved. The driving control circuit effectively ensures the advantages of repeatable expansion of the mechanism, high control precision, stable operation, high reliability and the like.
Although the preferred embodiments of the present invention have been disclosed above, the present invention is not limited thereto. It is obvious that not all embodiments need be, nor cannot be exhaustive here. Any person skilled in the art can change and modify the research scheme of the present invention by adopting the design and content of the above disclosed embodiments without departing from the spirit and scope of the present invention, and therefore, any simple modification, parameter change and modification of the above embodiments by the research entity of the present invention all belong to the protection scope of the scheme of the present invention.
Claims (10)
1. A space active sun wing opening mechanism drive control circuit, comprising: the system comprises a main control chip DSP, a dual-path H-bridge pulse width modulation amplifier power driving chip, a dual-redundancy CAN bus interface circuit and a dual-path position detection circuit, wherein the dual-redundancy CAN bus interface circuit is in information interaction with an onboard integrated electronic system, each path position detection circuit of the dual-path position detection circuit is connected with a position sensor, the position sensor is connected with an output shaft, the output shaft is connected with a speed reducer, and the speed reducer is connected with a stepping motor; the main control chip DSP realizes instruction receiving and response data sending through the dual-redundancy CAN bus interface circuit, and realizes a solar wing substrate position feedback acquisition function and a PWM closed-loop control quantity output function through the dual-channel position detection circuit; and the main control chip DSP realizes the function of driving the stepping motor to rotate by a certain angle in the appointed direction according to the PWM closed-loop control quantity output by the main control chip DSP through the power driving chip of the double-path H-bridge pulse width modulation amplifier.
2. The drive control circuit of the space active solar wing spreading mechanism according to claim 1, wherein the main control chip DSP is further connected with a micro switch control and analog quantity acquisition circuit, and the micro switch control and analog quantity acquisition circuit realizes limit position micro switch control and open/close state information detection.
3. The space active solar wing spreading mechanism driving control circuit according to claim 2, wherein the main control chip DSP adopts a domestic digital signal processor of model JDSP 28335.
4. The space active solar span opening mechanism drive control circuit of claim 1 wherein the position sensor employs a rotary transformer.
5. The drive control circuit for a space active solar span opening mechanism according to claim 2, wherein the dual channel position detection circuit employs a detection circuit with an axis angle conversion chip FX2S1210 as a core.
6. The space active solar span opening mechanism drive control circuit of claim 2 wherein the two-way H-bridge pulse width modulated amplifier power driver chip is of the model number LHKF2703dD 02.
7. The space active solar wing spreading mechanism drive control circuit of claim 4 wherein the stepper motor is a two phase hybrid stepper motor with a full step angle of 1.8 °.
8. The space active solar span opening mechanism drive control circuit of claim 3 wherein the speed reducer employs a reduction ratio of 90.
9. The space active solar span opening mechanism drive control circuit of claim 2 wherein the two-way H-bridge pulse width modulated amplifier power drive chip comprises a dual FET power drive circuit connected to three opto-coupled isolators.
10. The space active sun wing opening mechanism drive control circuit according to claim 1, characterized in that the dual redundant CAN bus interface circuit integrates two eCAN modules as communication controller with a domestic JDSP 28335.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921832863.XU CN211253084U (en) | 2019-10-29 | 2019-10-29 | Drive control circuit of space active sun wing spreading mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921832863.XU CN211253084U (en) | 2019-10-29 | 2019-10-29 | Drive control circuit of space active sun wing spreading mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211253084U true CN211253084U (en) | 2020-08-14 |
Family
ID=71982005
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921832863.XU Withdrawn - After Issue CN211253084U (en) | 2019-10-29 | 2019-10-29 | Drive control circuit of space active sun wing spreading mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211253084U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110789737A (en) * | 2019-10-29 | 2020-02-14 | 贵州航天控制技术有限公司 | Drive control circuit and method for space active sun wing spreading mechanism |
-
2019
- 2019-10-29 CN CN201921832863.XU patent/CN211253084U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110789737A (en) * | 2019-10-29 | 2020-02-14 | 贵州航天控制技术有限公司 | Drive control circuit and method for space active sun wing spreading mechanism |
| CN110789737B (en) * | 2019-10-29 | 2024-03-29 | 贵州航天控制技术有限公司 | Space active solar wingspan opening mechanism driving control circuit and method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105159309B (en) | It is a kind of to utilize the spacecraft Attitude stable control method for biasing tether | |
| US11359579B2 (en) | Multi-redundancy electromechanical servo system for regulating liquid rocket engine and implementation method therefor | |
| CN103753535B (en) | Robot single-bus modular digital steering engine control device and control method | |
| CN211253084U (en) | Drive control circuit of space active sun wing spreading mechanism | |
| Peng et al. | Compliant motion control of kinematically redundant manipulators | |
| US20040211200A1 (en) | Current control loop for actuator and method | |
| WO2007044385B1 (en) | Self-powered systems and methods using auxiliary solar cells | |
| CN103072142A (en) | Space rope catching and locking device | |
| CN110789737B (en) | Space active solar wingspan opening mechanism driving control circuit and method thereof | |
| CN109352661A (en) | A kind of control method of joint of robot, servo drive and can storage medium | |
| CN109194213A (en) | A kind of warm back-up control circuit of spaceborne stepper motor driving circuit | |
| CN109120167B (en) | Sector buffer-based two-level PWM rectifier fault-tolerant control method | |
| CN102289217B (en) | Modular reconfigurable motion control system with axle as unit | |
| CN108748157B (en) | Control device and method for driving space manipulator joint | |
| Baheti et al. | Design of self-calibrating controllers for heliostats in a solar power plant | |
| CN110703588B (en) | Space station solar wing reliable redundancy control system and method based on multi-instruction input | |
| CN110963077B (en) | Space station solar wing capable of correcting speed and speed correction method thereof | |
| CN209514360U (en) | A kind of solar battery array driving control system and drive dynamic control device | |
| CN110963087B (en) | Multi-mode complex-process control method for space station solar wing | |
| Carroll et al. | Robust tracking control of rigid-link electrically-driven robots actuated by switched reluctance motors. | |
| CN114846738A (en) | Pool architecture for controlling an electromechanical actuator | |
| CN220820478U (en) | Real-time motion control system of mobile robot | |
| Bailey et al. | Resolved rate and torque control schemes for large scale space based kinematically redundant manipulators | |
| CN219392504U (en) | High-reliability satellite-borne electric pushing mechanical arm servo controller | |
| Hui et al. | High-cohesion and low-coupling integrative joint for space manipulator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20200814 Effective date of abandoning: 20240329 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20200814 Effective date of abandoning: 20240329 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |