Large spacecraft temperature quantity wireless acquisition and transmission device

Abstract

The utility model relates to the field of spacecraft cableless data transmission, in particular to a large spacecraft temperature quantity wireless acquisition and transmission device, which comprises an in-cabin temperature acquisition and transmission end and a control cabin receiving and processing end, wherein the in-cabin temperature acquisition transmitting end comprises N temperature acquisition circuits, a multi-path parallel A / D conversion circuit, a transmitting end microcontroller, a UWB communication transmitting module and a UWB transmitting antenna; the control cabin receiving processing end comprises a UWB receiving antenna, a UWB communication receiving module, a receiving end microcontroller and a serial port communication module. The large-scale spacecraft temperature quantity wireless acquisition and transmission device provided by the utility model performs single-machine temperature quantity acquisition on spacecraft sub-cabins, and uses a UWB wireless channel to replace a traditional low-frequency cable to realize wireless transmission of the temperature quantity between each cabin and a control cabin, so that the use of the low-frequency cable is reduced; and the convenience of collecting the temperature quantity of the large spacecraft is greatly improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of spacecraft cableless data transmission, concretely relates to a large spacecraft temperature quantity wireless acquisition and transmission device. BACKGROUND

[0002] Temperature quantity is a very important telemetry parameter in spacecraft single machine equipment, when temperature is too high or too low, it can cause serious harm to single machine, even can destroy single machine and make it lose function, therefore, the monitoring of spacecraft cabin single machine temperature is very important. With the high-speed development of space technology, the on-board load is more and more, the large size of spacecraft makes its corresponding function cabin more, the number of supporting single machine equipment increases, the distance between single machines becomes far, and because the temperature quantity of each single machine needs to be monitored, the number of cables for temperature quantity telemetry acquisition between cabins increases, the length of cable network increases, which not only causes the increase of cable layout and laying difficulty and cable overweight problem, but also makes it inconvenient to separate and dock between cabins because of too many cable connections, and is not conducive to the development of large spacecraft to modularization and integration. SUMMARY

[0003] The utility model solves the problem of the increase of cable network design, layout and laying difficulty and cable overweight between cabins in the process of collecting and transmitting the temperature quantity of each cabin single machine of large spacecraft due to the large size of large spacecraft and the large number of cabin bodies, proposes a large spacecraft temperature quantity wireless acquisition and transmission device, adopts single machine temperature quantity acquisition for large spacecraft cabin division, and uses wireless carrier communication technology ultra wide band (UWB) wireless channel to replace traditional low-frequency cable to realize the wireless transmission of temperature quantity between each cabin and control cabin, which not only simplifies the cable network design difficulty and effectively reduces the weight of spacecraft, but also greatly increases the convenience of large spacecraft temperature quantity acquisition.

[0004] The specific technical scheme of the utility model is as follows:

[0005] A large spacecraft temperature quantity wireless acquisition and transmission device, the device comprises a cabin temperature acquisition sending end and a control cabin receiving processing end, wherein the cabin temperature acquisition sending end has n, each cabin temperature acquisition sending end comprises a multi-channel parallel A / D conversion circuit, a transmitting end microcontroller, a UWB communication transmitting module, a UWB transmitting antenna and N temperature acquisition circuits, and the control cabin receiving processing end comprises a UWB receiving antenna, a UWB communication receiving module, a receiving end microcontroller and a serial communication module.

[0006] The multi-channel parallel A / D conversion circuit is used for acquiring multi-channel voltage analog quantity, and converting the voltage analog quantity into corresponding digital signals and sending to the transmitting end microcontroller for processing.

[0007] The transmitting end microcontroller is configured to frame the digital signals transmitted by the multi-channel parallel A / D conversion circuit according to a transmission format, and is configured to parameter configuration, control and state acquisition of the UWB communication transmitting module;

[0008] The UWB communication transmitting module is configured to encode and modulate the communication frames sent by the transmitting end microcontroller into UWB pulse signals, and radiate the UWB pulse signals to space through a UWB antenna.

[0009] The UWB transmitting antenna is configured to transmit the UWB pulse signals modulated by the UWB communication transmitting module to the control cabin.

[0010] The temperature acquisition circuit comprises a thermistor and a constant resistor, the thermistor and the constant resistor are connected in series, and the temperature of the single machine is determined by acquiring the voltage change between the thermistor, and the temperature quantity is converted into a corresponding voltage analog quantity.

[0011] The UWB receiving antenna is configured to receive the signals radiated by the UWB communication transmitting module of other cabins, the UWB communication receiving module is configured to demodulate and decode the received UWB pulse signals, convert the UWB pulse signals into digital signals and send the digital signals to the receiving end microcontroller, the receiving end microcontroller is configured to parameter configuration, control and state acquisition of the UWB communication receiving module, and send the temperature digital quantity to the serial communication module, and the serial communication module is configured to transmit the temperature digital quantity collected by each cabin to the spacecraft computer through serial communication.

[0012] The transmitting end microcontroller comprises a processor module, a control module, a storage module, a clock module, an interface communication module and a power module, wherein: the processor module is configured to configure the parameters of the UWB communication transmitting module, detect and control the state of the UWB communication transmitting module, and frame the temperature digital quantity; the control module is configured to receive the control instructions of the spacecraft and forward the control instructions to the processor module to direct corresponding operations, and feed back the state information of the processor module to the spacecraft; the storage module is configured to store related program codes, data and operation numbers, and match the data transmission rate between the multi-channel parallel A / D conversion circuit and the microcontroller, so as to avoid data loss caused by transmission data rate fluctuation; the clock module provides original and stable clock frequency and clock signal to each module; the interface communication module is configured to realize interface communication between the modules in the microcontroller and external communication between the microcontroller and the multi-channel parallel A / D conversion circuit; and the power module converts primary power into secondary power, provides various working power required by each module unit, and realizes monitoring and control of power voltage.

[0013] The receiving end microcontroller includes a processor module, a control module, a storage module, a clock module, an interface communication module and a power module, wherein: the processor module is configured to configure parameters of the UWB communication receiving module, detect and control the state of the UWB communication receiving module; the control module is configured to receive control instructions of the spacecraft and forward the control instructions to the processor module to direct corresponding operations, and feed back state information of the processor module to the spacecraft; the storage module is configured to store relevant program codes, data and operation numbers, and match data transmission rates between the serial communication module and the microcontroller, so as to avoid data loss caused by transmission data rate fluctuation; the clock module provides original and stable clock frequency and clock signals for each module; the interface communication module is configured to realize interface communication between modules in the microcontroller and external communication between the microcontroller and the serial communication module; and the power module converts primary power into secondary power, provides various working power required by each module unit, and realizes monitoring and control of power voltage.

[0014] The interface communication module of the transmitting end microcontroller includes an internal interface communication submodule and an external interface communication submodule, wherein the internal interface communication submodule is configured to process data communication between the processor module and the control module, the storage module and the clock module, and the external interface communication submodule is configured to realize external data communication between the transmitting end microcontroller and the multi-channel parallel A / D conversion circuit and between the transmitting end microcontroller and the UWB communication transmitting module.

[0015] The communication frame transmitted by the transmitting end microcontroller to the UWB communication transmitting module includes a cabin identifier and a single machine identifier, the cabin identifier is configured to distinguish different cabins, and the single machine identifier is configured to distinguish different single machines; the single machine identifier and the temperature of the single machine form a small data packet; and finally, the cabin identifier and a plurality of single machine data packets are sequentially spliced to form a communication frame.

[0016] The interface communication module of the receiving end microcontroller includes an internal interface communication submodule and an external interface communication submodule, wherein the internal interface communication submodule is configured to process data communication between the processor module and the control module, the storage module and the clock module, and the external interface communication submodule is configured to realize external data communication between the receiving end microcontroller and the serial communication module and between the receiving end microcontroller and the UWB communication receiving module.

[0017] The thermistor in the temperature acquisition circuit is a thermistor with a temperature measurement accuracy better than 0.1℃.

[0018] The large spacecraft temperature quantity wireless acquisition and transmission device acquires the temperature quantities of all single machines in each cabin, uses a UWB wireless channel to replace a traditional low-frequency cable, and transmits the temperature quantities in each cabin to a star computer in a control cabin.

[0019] The utility model discloses the following beneficial effects are obtained:

[0020] (1) the utility model discloses based on UWB technology realizes the cabin temperature of large spacecraft to gather, and this wireless communication technology has low power consumption, high reliability, high security and so on, and its multipath resolution is extremely high, can penetrate various obstacles, and the transmission rate is higher than the current commonly used bluetooth, zigbee, WiFi and so on wireless communication technology, and the performance is more stable.

[0021] (2) the utility model discloses a kind of large spacecraft temperature quantity wireless acquisition and transmission device, first cabin temperature collection is integrated wireless transmission to control cabin again, can effectively increase the integration level and convenience of temperature quantity acquisition system, reduce the use of low-frequency cable.

[0022] (3) the utility model discloses a kind of large spacecraft temperature quantity wireless acquisition and transmission device, cabin identifier and single machine identifier are added in communication frame design, the temperature quantity of cabin and single machine is identified by mark, can obtain all temperature quantities of spacecraft.

[0023] (4) the utility model discloses a kind of large spacecraft temperature quantity wireless acquisition and transmission device, the temperature precision that thermistor in its temperature acquisition circuit can measure is superior to 0.1 ℃, can satisfy spacecraft temperature quantity high-precision measurement demand.

[0024] (5) the utility model discloses a kind of large spacecraft temperature quantity wireless acquisition and transmission device, can be applicable to in-orbit space station, future expansion segmented cabin and mars exploration spacecraft, with good forward-looking and adaptability. BRIEF DESCRIPTION OF DRAWINGS

[0025] In order to more clearly illustrate the technical scheme of the embodiments of the utility model, the following will be briefly introduced to the drawings needed to be used in embodiment description, for the ordinary skilled person in the art, without paying the creative labor, can also obtain other drawings according to these drawings.

[0026] Figure 1 For the structure diagram of large spacecraft temperature quantity wireless acquisition and transmission device proposed in the utility model,

[0027] Figure 2 For the structure diagram of transmitting end and receiving end microcontroller proposed in the utility model. DETAILED DESCRIPTION

[0028] The specific embodiments of the utility model will be further described in combination with the drawings.

[0029] As Figure 1As shown in the utility model discloses large -scale spacecraft temperature quantity wireless acquisition and transmission device includes n cabin temperature acquisition sending end and a control cabin receiving processing end, wherein, the cabin temperature acquisition sending end includes multichannel parallel A / D conversion circuit, transmitting end microcontroller, UWB communication transmitting module, UWB transmitting antenna and n temperature acquisition circuit, the control cabin receiving processing end includes UWB receiving antenna, UWB communication receiving module, receiving end microcontroller and serial communication module.

[0030] The multichannel parallel A / D conversion circuit is used to collect multichannel voltage analog quantity, and the voltage analog quantity is converted into corresponding digital signal and sent to the transmitting end microcontroller for processing, the transmitting end microcontroller is used to frame the digital signal sent by the multichannel parallel A / D conversion circuit according to the transmission format, and is used for parameter configuration, control and state acquisition of the UWB communication transmitting module, the UWB communication transmitting module is used to encode and modulate the communication frame sent by the transmitting end microcontroller, converts into UWB pulse signal and radiates to space through the UWB antenna, the UWB transmitting antenna transmits the UWB pulse signal modulated by the UWB communication transmitting module to the control cabin, the temperature acquisition circuit includes a thermistor and a fixed resistor, the thermistor and the fixed resistor are connected in series, and the temperature of the single machine is determined by collecting the voltage change of the thermistor, and the temperature quantity is converted into corresponding voltage analog quantity.

[0031] The UWB receiving antenna is used to receive the signal radiated by the UWB communication transmitting module of other cabins, the UWB communication receiving module is used to demodulate and decode the received UWB pulse signal, converts into digital signal and sends to the receiving end microcontroller, the receiving end microcontroller is used for parameter configuration, control and state acquisition of the UWB communication receiving module, and sends the temperature digital quantity to the serial communication module, and the serial communication module is used for transmitting the temperature digital quantity collected by each cabin to the star computer through serial communication.

[0032] As Figure 2 As shown in the utility model discloses transmitting end, receiving end microcontroller structure diagram, from the drawing, the microcontroller of the utility model bears the data processing and interaction between multichannel parallel A / D conversion circuit, serial communication module and UWB communication module, and is responsible for the control and state acquisition of UWB communication module, the microcontroller includes processor module, control module, storage module, clock module, interface communication module and power module, and each module realizes information exchange with bus.

[0033] The processor module is used for configuring parameters of the UWB communication module, detecting and controlling the state of the UWB communication module, and framing data groups of the temperature digital quantity; the control module is used for receiving control instructions of the spacecraft and forwarding the control instructions to the processor module to direct corresponding operations, and feeding back state information of the processor module to the spacecraft; the storage module is used for storing relevant program codes, data and operation numbers, and matching data transmission rates between the multi-path parallel A / D conversion circuit, the serial communication module and the microcontroller, so as to avoid data loss caused by transmission data rate fluctuation and the like; the clock module provides original and stable clock frequencies and clock signals for each module; the interface communication module is used for realizing interface communication between modules in the microcontroller and external communication of the microcontroller; and the power module converts primary power into secondary power, provides various working power required by each module unit, and realizes monitoring and control of power supply voltage.

[0034] In the embodiment, the temperature quantity of all single machines in each cabin is collected, and then a UWB wireless channel is used to replace a traditional low-frequency cable to transmit the temperature quantity in each cabin to a star computer in a control cabin.

[0035] The above specific embodiments are used to explain and illustrate the present application, and any modification and change made to the present application within the spirit and protection scope of the claims of the present application all fall into the protection scope of the present application.

Claims

1. A large spacecraft temperature wireless collection and transmission device, characterized in that: The device includes a cabin temperature collection and transmission end and a control cabin receiving and processing end, wherein: There are n cabin temperature collection and transmission terminals, each of which includes a multi-channel parallel A / D conversion circuit, a transmitting end microcontroller, a UWB communication transmission module, a UWB transmitting antenna and N temperature collection circuits; The control cabin receiving and processing end includes a UWB receiving antenna, a UWB communication receiving module, a receiving end microcontroller and a serial communication module.

2. The large spacecraft temperature wireless acquisition and transmission device according to claim 1 is characterized in that: The multi-channel parallel A / D conversion circuit is used to collect multi-channel voltage analog quantities, and convert the voltage analog quantities into corresponding digital signals and send them to the transmitting end microcontroller for processing; The transmitting end microcontroller is used to frame the digital signals sent by the multi-channel parallel A / D conversion circuit according to the transmission format, and is used for parameter configuration, control and status acquisition of the UWB communication transmitting module; The UWB communication transmitting module is used to encode and modulate the communication frame sent by the transmitting end microcontroller, convert it into a UWB pulse signal and radiate it into space via the UWB antenna; The UWB transmitting antenna transmits a UWB pulse signal modulated by the UWB communication transmitting module to the control cabin. The UWB receiving antenna is used to receive signals radiated by the UWB communication transmitting modules of other cabins. The temperature acquisition circuit includes a thermistor and a fixed-value resistor, which are connected in series. The temperature of the single machine is determined by acquiring the voltage change at both ends of the thermistor, and the temperature is converted into a corresponding voltage analog value.

3. The large spacecraft temperature wireless acquisition and transmission device according to claim 1 is characterized in that: The transmitting end microcontroller includes a processor module, a control module, a storage module, a clock module, an interface communication module and a power supply module, wherein: The processor module is used to configure the parameters of the UWB communication transmission module, detect and control the status of the UWB communication transmission module, and frame the temperature digital quantity; The control module is used to receive control instructions from the spacecraft and forward them to the processor module to instruct corresponding operations, and feed back status information of the processor module to the spacecraft; The storage module is used to store relevant program codes, data and operands, and to match the data transmission rate between the multi-channel parallel A / D conversion circuit and the microcontroller to avoid data loss caused by fluctuations in the transmission data rate; The clock module provides original, stable clock frequency and clock signal to each module; The interface communication module is used to realize the interface communication between the modules inside the microcontroller and the external communication between the microcontroller and the multi-channel parallel A / D conversion circuit; The power supply module converts the primary power supply into the secondary power supply, provides the required various working power supplies for each module unit, and realizes the monitoring and control of the power supply voltage.

4. The large spacecraft temperature wireless acquisition and transmission device according to claim 1 is characterized in that: The UWB communication receiving module is used to demodulate and decode the received UWB pulse signal, convert it into a digital signal and send it to the receiving end microcontroller; The receiving end microcontroller is used for parameter configuration, control and status acquisition of the UWB communication receiving module, and sends the temperature digital value to the serial communication module; The serial communication module is used to transmit the temperature digital quantity collected by each cabin to the satellite service computer through serial communication.

5. The large spacecraft temperature wireless acquisition and transmission device according to claim 1 is characterized in that: The receiving end microcontroller includes a processor module, a control module, a storage module, a clock module, an interface communication module and a power supply module, wherein: The processor module is used to configure the UWB communication receiving module parameters and detect and control the status of the UWB communication receiving module; The control module is used to receive control instructions from the spacecraft and forward them to the processor module to instruct corresponding operations, and feed back status information of the processor module to the spacecraft; The storage module is used to store relevant program codes, data and operands, and to match the data transmission rate between the serial communication module and the microcontroller to avoid data loss caused by fluctuations in the transmission data rate; The clock module provides original, stable clock frequency and clock signal to each module; The interface communication module is used to realize the interface communication between the modules inside the microcontroller and the external communication between the microcontroller and the serial communication module; The power supply module converts the primary power supply into the secondary power supply, provides the required various working power supplies for each module unit, and realizes the monitoring and control of the power supply voltage.

6. The large spacecraft temperature wireless acquisition and transmission device according to claim 1 or 3, characterized in that: The communication frame transmitted by the transmitting end microcontroller to the UWB communication transmitting module includes a cabin identifier and a single-machine identifier. The cabin identifier is used to distinguish different cabins, and the single-machine identifier is used to distinguish different single machines. The single-machine identifier and the temperature of the single machine itself constitute a small data packet. Finally, the cabin identifier and multiple single-machine data packets are spliced ​​in sequence to form a communication frame.

7. The large spacecraft temperature wireless acquisition and transmission device according to claim 3 is characterized by: The interface communication module includes an internal interface communication submodule and an external interface communication submodule, wherein the internal interface communication submodule is used for data communication between the processor module and the control module, storage module, and clock module; the external interface communication module is used for external data communication between the transmitting end microcontroller and the multi-channel parallel A / D conversion circuit, and between the transmitting end microcontroller and the UWB communication transmitting module; the external interface communication module is also used for external data communication between the receiving end microcontroller and the serial port communication module, and between the receiving end microcontroller and the UWB communication receiving module.

8. The large spacecraft temperature wireless acquisition and transmission device according to claim 1 is characterized by: The large spacecraft temperature wireless collection and transmission device collects the temperature of all units in each cabin on a cabin-by-cabin basis, and then uses UWB wireless channels to replace traditional low-frequency cables to transmit the temperature in each cabin to the space service computer in the control cabin.

9. The large spacecraft temperature wireless acquisition and transmission device according to claim 2, characterized in that: The thermistor is a thermistor that can measure temperature with an accuracy better than 0.1°C.

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