CN112596443A - Control system and method for multi-satellite deployer - Google Patents
Control system and method for multi-satellite deployer Download PDFInfo
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- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
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Abstract
The invention discloses a control system and a control method of a multi-satellite deployer, which comprise a power supply module, an upper computer module and an A/D signal acquisition module, wherein the A/D signal acquisition module is electrically connected with a CPU module, the A/D signal acquisition module comprises a temperature sensor and a pressure sensor, the CPU module is electrically connected with a plurality of paths of deployment modules, the number of the paths of the plurality of paths of deployment modules is 1-100, and the power supply module comprises a battery and power supply management. The control system and the method of the multi-satellite deployer can be matched with the multi-satellite separators, and the combination of the multi-satellite deployers can deploy a plurality of cuboids of different models at the same time, so that compared with the mode that one cuboid corresponds to one deployer, the control system saves power consumption, has the advantages of good universality, low power consumption, small volume, light weight and low cost, and is beneficial to modularization and large-scale production.
Description
Technical Field
The invention relates to the technical field of control of spacecraft deployers, in particular to a control system and a control method of a multi-satellite deployer.
Background
With the development of microelectronics, micromachines, nanotechnology, etc., satellites are becoming smaller and smaller, with cuboids being divided by "U", 1U referring to a standard unit (volume 10cm x 10 cm). The cubic star is an integral multiple of 1U satellite, and has the greatest advantage of unified design and manufacture standards and convenience for international cooperation; low cost, high functional density, short development period, fast track entering and other features. The device can realize detection on oceans, atmospheric environments, ships and aviation aircrafts, and can also be used in the fields of communication, biological research and the like.
However, the existing control method of the multi-satellite deployer is that one cube corresponds to one deployer, the deployment mode is heavy in weight and large in volume, and meanwhile, continuous large-current continuous work is required, so that the power consumption is large, the function is single, the adaptability is low, only one cube can be used, the customization is high, the research and development cost is high, modularization and large-scale production are not facilitated, and the weight and the space of a launch vehicle are seriously wasted; the cubic star has very high carrying cost, and is generally charged according to weight, so that the weight and the space of the deployer are reduced, and the emission cost is particularly important to be reduced.
Therefore, the invention develops a control system and a control method of a multi-satellite deployer.
Disclosure of Invention
Technical problem to be solved
Aiming at the defects of the prior art, the invention provides a control system and a control method of a multi-satellite deployer, which have the advantages of high performance, strong flexibility, short period, relatively simple development, low power consumption, small volume, light weight and the like, and solve the problems of large weight, large volume, large power consumption, single function, low adaptability and high research and development cost in the prior art.
(II) technical scheme
In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a control system of many satellites deployer, includes power module and host computer module, still includes AD signal acquisition module, AD signal acquisition module and CPU module electric connection, AD signal acquisition module includes temperature sensor and baroceptor, CPU module electric connection has the multichannel and deploys the module, the way number of multichannel deployment module is 1 ~ 100, power module includes battery and power management.
Preferably, the multi-path deployment module comprises an output part and a state monitoring part.
Preferably, the battery is 18650 single-cell storage battery.
Preferably, the CPU module has a multi-output interface, and adopts a dual redundancy design, in which one part is used for normal output and the other part is used for standby output.
Preferably, the system communicates with an upper computer in an RS422 optical coupling isolation bus mode and a CAN optical coupling isolation bus mode.
Another technical problem to be solved by the present invention is to provide a method for controlling a multi-satellite deployer, comprising two steps a and b:
after a target enters a track, a CPU module can carry out signal acquisition and storage on the temperature of a circuit board and the air pressure of the position of the circuit board through an A/D signal acquisition module;
then the received upper computer command is distinguished,
if the command is a release command, the CPU module collects analog quantity of the current PCB temperature and the air pressure of the position, and then judges the quantity of released electric quantity and whether the air pressure is close to vacuum according to the current temperature;
finally, whether the optimal separation state is reached is judged,
after the voltage pulse is applied, the CPU module applies the voltage pulse with the width of 200ms, the voltage pulse is applied again at the interval of 2000ms, and the output of the deployer is finished;
by parity of reasoning, the deployment and release work of other paths of satellites is completed;
b, separating by a multi-satellite separator, wherein an unlocking device of the multi-satellite separator adopts memory alloy as drive and is completed by a memory alloy pin puller;
under the non-electrified state, the closing of the cabins is completed through a positioning pin in the memory alloy device,
after the power is switched on, the memory alloy device unlocks the door plate, opens the cabin door under the action of the pressure of the main spring and pushes the satellite out of the deployer box.
Preferably, the memory alloy pin puller is a facility specially used for pulling out the positioning pin, and after the power is supplied, the memory alloy pin puller receives a command for separating the satellite to release and open the separator through calculation of current and power-on time, and judges whether the satellite is released or not.
Preferably, the multi-satellite separator can release a plurality of cuboids with different sizes on the track, and the box door of the ejection mechanism is closed after the cuboids are installed inside the box.
(III) advantageous effects
Compared with the prior art, the invention provides a control system and a control method of a multi-satellite deployer, which have the following beneficial effects:
the multi-path deployment output is controlled by the CPU module, at most 100 paths of satellite deployers can be opened for separation and release, each path of satellite deployer independently deploys the control output, each path of output is provided with a standby output interface, and then the multi-path satellite deployers can be matched, the combination of the multi-path satellite deployers can simultaneously deploy a plurality of cubic stars in different models, compared with the mode that one cubic star corresponds to one deployer, the power consumption is saved, and the multi-path satellite deployer has the advantages of good universality, low power consumption, small size, light weight and low cost, and is beneficial to modularization and large-scale production.
Drawings
FIG. 1 is a schematic diagram of the overall framework of the control system of the present invention;
FIG. 2 is a schematic circuit diagram of a power module according to the present invention;
FIG. 3 is a schematic diagram of a single-pass deployment output circuit of the present invention;
FIG. 4 is a schematic view showing a flow of the memory alloy pin puller according to the present invention;
FIG. 5 is a schematic diagram of a deployer deployment timing of the invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-5, a control system of a multi-satellite deployer includes a power module and an upper computer module, and further includes an a/D signal acquisition module, the a/D signal acquisition module is electrically connected to a CPU module, the CPU chip selects MSP430, which is a 16-bit ultra-low power consumption mixed signal processor with RISC reduced instruction set, the a/D signal acquisition module includes a temperature sensor and a pressure sensor, wherein the temperature sensor selects 5-pin SOT23 to package a TMP36GRTZ chip, the accuracy is ± 3 ℃, the voltage interface surface is mounted, and the sensing temperature range is: -40 ℃ to +125 ℃; MS5611-01BA03 chip is selected for the baroceptor collection, it adopts QFN encapsulation size, integrated 24 bit ADC, and measurement, working range are: 10-1200 mbar, -40 ℃ to +85 ℃, the system is provided with two bus interfaces of SPI and I2C, the resolution ratio reaches 10cm, no external component exists, the stability in long-term operation is good, the CPU module is electrically connected with a multi-path deployment module, the path number of the multi-path deployment module is 1-100, the power supply module comprises a battery and a power supply management part, and the power supply management part comprises the functions of boosting, stabilizing voltage, filtering, constant current, protection and the like.
Preferably, the multi-path deployment module comprises an output part and a state monitoring part.
Preferably, the battery is 18650 single-cell storage battery.
Preferably, the CPU module has a multi-output interface, and adopts a dual redundancy design, in which one part is used for normal output and the other part is used for standby output.
Preferably, the system communicates with an upper computer in an RS422 optical coupling isolation bus mode and a CAN optical coupling isolation bus mode, and an RS422 communication transceiver selects an MAX490 chip, so that the system has high stability, high static protection and excellent EMI performance; the CAN communication transceiver selects an SN65HVD230QD chip, has high communication rate, good anti-interference capability and high reliability, and ensures that the communication with an upper computer is reliably completed.
A control method of a multi-satellite deployer comprises two steps of a and b:
after a target enters a track, a CPU module can carry out signal acquisition and storage on the temperature of a circuit board and the air pressure of the position of the circuit board through an A/D signal acquisition module;
then the received upper computer command is distinguished,
if the command is a release command, the CPU module collects analog quantity of the current PCB temperature and the air pressure of the position, and then judges the quantity of released electric quantity and whether the air pressure is close to vacuum according to the current temperature;
finally, whether the optimal separation state is reached is judged,
after the voltage pulse is applied, the CPU module applies the voltage pulse with the width of 200ms, the voltage pulse is applied again at the interval of 2000ms, and the output of the deployer is finished;
by parity of reasoning, the deployment and release work of other paths of satellites is completed;
b, separating by a multi-satellite separator, wherein an unlocking device of the multi-satellite separator adopts memory alloy as drive and is completed by a memory alloy pin extractor, the memory alloy pin extractor is a facility special for pulling out a positioning pin, one end of the memory alloy pin extractor is connected with a pin, the other end of the memory alloy pin extractor is provided with a movable heavy hammer, and the pin is pulled out by utilizing the impact generated by the movable heavy hammer;
under the non-electrified state, the closing of the cabins is completed through a positioning pin in the memory alloy device,
after the power is switched on, the memory alloy device unlocks the door plate, opens the cabin door under the action of the pressure of the main spring and pushes the satellite out of the deployer box.
Preferably, the memory alloy pin puller is a facility specially used for pulling out the positioning pin, after the power is on, the memory alloy pin puller receives a command for separating the satellite through calculation of current and power-on time to release the separator, and judges whether the satellite is released or not, so that the purpose of being universal is achieved.
Preferably, the multi-satellite separator can release a plurality of cuboids with different sizes on the track, and the box door of the ejection mechanism is closed after the cuboids are installed inside the box.
The implementation mode is as follows:
the CPU is the core part of the controller of the whole multi-satellite deployer, firstly, the CPU adopts an internal 12-bit ADC to acquire and store signals of the temperature of a circuit board and the air pressure of the position of the circuit board, then judges the received upper computer command, if the satellite release command of the upper computer is received, the CPU acquires analog quantity of the current PCB temperature and the air pressure of the position of the circuit board, then judges the quantity of electric quantity to be released according to the current temperature and whether the current air pressure is close to vacuum or not, and finally judges whether the optimal separation state is achieved or not through a CPU core processor;
if the optimal separation state is reached, the CPU core processor gives a voltage pulse with the width of 200ms, and the voltage pulse with the width of 200ms is applied again at the interval of 2000ms, and the output of the deployer is completed.
In order to ensure that the satellite is deployed smoothly, the release state of the satellite is detected at the same time: when the satellite is successfully released, a port of the deployment completion indication plus port can apply a voltage pulse and the deployment completion indication still becomes a low level, which indicates that the satellite in the path is successfully deployed, otherwise, the deployment is not successfully deployed, under the condition, the CPU core processor 1 gives a voltage pulse with the width of 200ms to the standby output interface in the path, applies a voltage pulse with the width of 200ms again at an interval of 2000ms, completes the output of the deployer, similarly, the corresponding state detection is carried out again on the satellite deployment output released this time, after the satellite is successfully released, the port of the deployment completion indication plus port can apply a voltage pulse and the deployment completion indication still becomes a low level, which indicates that the satellite in the path is successfully deployed, otherwise, the deployment is not successfully deployed.
If the satellite release output state of the path is still not successful, the dual redundancy function of the system is enabled, and the core processor 2 carries out the same work flow.
Multi-path deployment:
deployment output and output state detection functions released by multiple paths of satellites at least meet the requirement that deployment state detection of a 100-path deployer is used for acquiring telemetering engineering parameters, wherein the telemetering engineering parameters appear in the forms of switching value signals '0' and '1';
the multi-path deployment output of the deployer is controlled by an MSP430 core processor CPU, at most 100 paths of satellite deployers can be opened for separation and release, each path of deployer independently deploys control output, and each path of output is provided with a standby output interface;
the timing relationship between the individual deployment output and the standby deployment output of each way is: after the core processor receives a deployment command of the upper computer, a deployment signal with pulse of 200ms is directly output, after the interval of 2000ms, a deployment signal with pulse of 200ms is output by the standby output port, the deployment success of the satellite in the path is ensured to be reliably released, the deployment and release work of other satellites is finished by analogy, and 100 identical single-path deployment outputs form the controller output of the satellite deployer with 100 paths.
The method comprises the following operation steps:
after the cube satellite reaches a preset orbit, the satellite can be successfully released only by giving an unlocking new number by a carrying upper computer;
the controller of the multi-satellite deployer provides power current signals for satellite deployment;
release indicator function test: before the satellite is released, voltage pulse is applied to the port of 'deployment completion indication +', and at the moment, voltage pulse can simultaneously appear at the port of 'deployment completion indication', which indicates that the indicator has normal function and the satellite is not released;
and (3) satellite orbit deployment: after 500ms, applying a voltage pulse with the width of 200ms to the port of the main unlocking signal plus, and applying a voltage pulse with the width of 200ms again at the interval of 2000ms to ensure that the satellite is deployed smoothly;
detecting a satellite release state: when the satellite is successfully released, a voltage pulse is applied to the port of the deployment completion indication + and the port of the deployment completion indication-is still changed to be low level, so that the satellite is successfully deployed.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, the use of the verb "comprise a" to define an element does not exclude the presence of another, same element in a process, method, article, or apparatus that comprises the element.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The utility model provides a control system of many satellite deployers, includes power module and host computer module, its characterized in that: still include AD signal acquisition module, AD signal acquisition module and CPU module electric connection, AD signal acquisition module includes temperature sensor and baroceptor, CPU module electric connection has the multichannel and deploys the module, the way number of multichannel deployment module is 1 ~ 100, power module includes battery and power management.
2. The control system of a multi-satellite deployer of claim 1, wherein: the multi-path deployment module comprises an output part and a state monitoring part.
3. The control system of a multi-satellite deployer of claim 1, wherein: the battery is preferably a 18650 cell battery.
4. The control system of a multi-satellite deployer of claim 1, wherein: the CPU module is provided with a multi-path output interface and adopts a dual redundancy design, wherein one part of the multi-path output interface is used for normal output, and the other part of the multi-path output interface is used for standby output.
5. The control system of a multi-satellite deployer of claim 1, wherein: the system adopts an RS422 optical coupling isolation bus mode and a CAN optical coupling isolation bus mode to communicate with an upper computer.
6. A control method of a multi-satellite deployer is characterized by comprising two steps of a and b:
after a target enters a track, a CPU module can carry out signal acquisition and storage on the temperature of a circuit board and the air pressure of the position of the circuit board through an A/D signal acquisition module;
then the received upper computer command is distinguished,
if the command is a release command, the CPU module collects analog quantity of the current PCB temperature and the air pressure of the position, and then judges the quantity of released electric quantity and whether the air pressure is close to vacuum according to the current temperature;
finally, whether the optimal separation state is reached is judged,
after the voltage pulse is applied, the CPU module applies the voltage pulse with the width of 200ms, the voltage pulse is applied again at the interval of 2000ms, and the output of the deployer is finished;
by parity of reasoning, the deployment and release work of other paths of satellites is completed;
b, separating by a multi-satellite separator, wherein an unlocking device of the multi-satellite separator adopts memory alloy as drive and is completed by a memory alloy pin puller;
under the non-electrified state, the closing of the cabins is completed through a positioning pin in the memory alloy device,
after the power is switched on, the memory alloy device unlocks the door plate, opens the cabin door under the action of the pressure of the main spring and pushes the satellite out of the deployer box.
7. The method of claim 6, wherein: the memory alloy pin puller is a facility specially used for pulling out a positioning pin, and after the power is on, the memory alloy pin puller receives a command for separating a satellite through calculation of current and power-on time to release and open the separator and judges whether the satellite is released or not.
8. The method of claim 6, wherein: the multi-satellite separator can release a plurality of cuboids with different sizes on the track, and after the cuboids are arranged inside the ejection mechanism box body, the box body cabin door is closed.
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| CN114572425A (en) * | 2022-04-12 | 2022-06-03 | 星众空间(西安)科技有限公司 | Multi-satellite separation controller |
| CN115498431A (en) * | 2022-07-15 | 2022-12-20 | 大连理工大学 | Separation control box suitable for long-time on-orbit operation satellite deployer |
| CN116395148A (en) * | 2023-03-20 | 2023-07-07 | 银河航天(北京)网络技术有限公司 | Satellite and rocket separation control system and control method |
| CN116534279A (en) * | 2023-07-05 | 2023-08-04 | 北京未来宇航空间科技研究院有限公司 | Satellite orbit deployment device and assembly thereof |
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