Data rescue system applied to extraterrestrial celestial body detector
阅读说明：本技术 应用于地外天体探测器的数据拯救系统 (Data rescue system applied to extraterrestrial celestial body detector ) 是由 张松涛 彭玉明 王云财 王伟 刘辉 韩柠 衣样 杨伟光 董炀 李敬一 李伟楠 于 2020-07-31 设计创作，主要内容包括：本发明属于深空探测技术领域,旨在解决地外天体探测器着陆故障时的数据丢失问题,具体涉及一种应用于地外天体探测器的数据拯救系统,包括设置在第一装置内的第一数据无线回传模块、数据采集控制模块、总控模块,以及设置在第二装置的第二数据无线回传模块；第一装置与第二装置可分离式连接；第二数据无线回传模块用于实时备份第一数据无线回传模块中存储的过程检测数据；总控模块基于数据采集控制模块采集的数据,对着陆过程状态进行在线分析,判断是否能成功着陆,以执行是否分离第二装置进行数据回传。通过本发明可实现着陆过程关键数据的拯救,从而为后续工程设计提供数据参考和支撑。(The invention belongs to the technical field of deep space exploration, aims to solve the problem of data loss when an extraterrestrial celestial body detector is in a landing fault, and particularly relates to a data rescue system applied to the extraterrestrial celestial body detector, which comprises a first data wireless backhaul module, a data acquisition control module and a master control module, wherein the first data wireless backhaul module is arranged in a first device; the first device and the second device are connected in a separable way; the second data wireless backhaul module is used for backing up the process detection data stored in the first data wireless backhaul module in real time; the main control module analyzes the landing process state on line based on the data acquired by the data acquisition control module, and judges whether the landing can be successfully performed so as to execute whether the second device is separated for data return. The method and the device can save the critical data in the landing process, thereby providing data reference and support for subsequent engineering design.)
1. A data rescue system applied to a extraterrestrial celestial body detector is characterized by comprising a protection buffering module, a data wireless return module, a data acquisition control module, a power supply module and a master control module, wherein the data acquisition control module and the master control module are arranged in the protection buffering module and are in communication connection with the master control module; the protection buffer module comprises a first device and a second device, and the second device is arranged at the tail of the first device and is connected with the first device through a separating device; the data acquisition control module and the master control module are arranged in the first device; the data wireless return module comprises a first data wireless return module and a second data wireless return module, and the first data wireless return module is arranged in the first device and used for storing data detected by the detector in flight; the second wireless data backhaul module is arranged in the second device, is in communication connection with the first wireless data backhaul module, and is used for backing up data stored in the first wireless data backhaul module in real time; the data acquisition control module is used for detecting the descent speed of the detector in the landing process and the distance parameter of the area to be landed in real time and transmitting the parameters to the master control module; the master control module carries out online analysis on the landing process state of the detector based on the data acquired by the data acquisition control module, and judges whether the detector can land successfully or not so as to formulate related measures; the related measures comprise sending a control instruction for starting the separation of the first device and the second device to the protection buffering module, and sending a control instruction for triggering the second data wireless backhaul module to execute data backhaul.
2. The data rescue system applied to the extraterrestrial celestial body detector of claim 1, wherein buffer structures are arranged on the peripheral sides of the data acquisition control module, the master control module, the first wireless data return module and the second wireless data return module, and are used for ensuring buffer protection and limit fixation between adjacent modules; the buffer structure comprises a first buffer structure and a second buffer structure, a plurality of first contact surface creases are formed on the contact surface of the first buffer structure and the corresponding module, and the surface of the first buffer structure, which is far away from the corresponding module, is a first buffer surface; the contact surface of the second buffer structure and the corresponding module is provided with a plurality of second contact surface creases, and the surface of the second buffer structure, which is far away from the corresponding module, is a second buffer surface; the first contact surface crease and the second contact surface crease are provided with a plurality of folds; the first buffering surface and the second buffering surface are sequentially arranged in the circumferential direction of the buffering structure.
3. The data rescue system applied to the extraterrestrial celestial detector of claim 1, wherein the second wireless data backhaul module comprises one or more second antenna devices; when the second antenna devices are multiple, the second antenna device arrays are arranged on the periphery of the axis of the second device to form an omnidirectional antenna array.
4. The data rescue system applied to the extraterrestrial celestial detector of claim 1, wherein the first wireless data backhaul module comprises one or more first antenna devices for storing data detected during the detector flight; when the number of the first antenna devices is multiple, the multiple first antenna device arrays are arranged on the periphery side of the axis of the first device.
5. The data rescue system applied to the extraterrestrial celestial body detector according to claim 4, wherein the first device comprises at least two layers of shells, and the adjacent shells are connected through a buffer device and used for protecting the data acquisition control module and the master control module which are arranged in the shells; the buffer device is formed by combining and superposing at least two buffer materials.
6. The data rescue system applied to the extraterrestrial celestial body detector of claim 5, wherein the first device comprises an impact portion and a fixed portion, the impact portion is arranged at the front end of the fixed portion, and the impact portion is bullet-shaped; an overload sensor is arranged between the impact part and the fixing part and is in communication connection with the master control module; the data acquisition control module and the master control module are sequentially and fixedly arranged on the fixing part; the rear end of the fixing part is connected with the second device.
7. The data rescue system applied to the extraterrestrial celestial body detector of claim 1, wherein the separation device is an explosive bolt or a connector with an annular explosive cable.
8. The data rescue system for extraterrestrial celestial detector of claim 1, wherein the separation device is a hydraulically driven mechanically separated hydraulic catapult.
9. The data rescue system for extraterrestrial celestial detector of claim 1, wherein the separation device is an autonomous safety separation device; the autonomous safety separation device comprises an outer mounting ring, an inner cutting ring, a powder charging ring groove and an ignition device, wherein the inner cutting ring is arranged on the inner side of the outer mounting ring and forms an annular cavity with the outer mounting ring; the charge ring groove is wound in the cavity; the ignition device is arranged on the inner wall of the inner cutting ring and communicated with the powder charging ring groove.
10. The data rescue system applied to the extraterrestrial celestial body detector of any one of claims 1-9, wherein a plurality of third antenna devices are arranged on the periphery side of the second device, and a plurality of third antenna devices are arranged on the outer side of the second device and connected with the second device through an ejection device; the ejection device is in signal connection with the master control module; the third antenna device is of a spherical structure.
Technical Field
The invention belongs to the technical field of deep space exploration, and particularly relates to a data rescue system applied to an extraterrestrial celestial body detector.
Background
The characteristics of severe environment, unknown uncertainty, long distance, large communication delay and the like of the extraterrestrial celestial body determine extraterrestrial celestial body detection, and particularly, the extraterrestrial celestial body detection has high difficulty and risk. Another characteristic of extraterrestrial celestial body landing detection is that if a landing fault occurs, any landing data cannot be taken, and even the true cause of landing failure cannot be determined, so that reference is difficult to provide for next task design, and subsequent tasks may fail again due to the same cause, thereby causing huge loss of manpower, material resources, financial resources and the like.
Disclosure of Invention
In order to solve the problems in the prior art, namely solving the problem of data loss when the extraterrestrial celestial body detector is in landing fault, the invention provides a data rescue system applied to the extraterrestrial celestial body detector, which comprises a protection buffer module, a data wireless backhaul module, a data acquisition control module, a power supply module and a general control module, wherein the data acquisition control module and the general control module are arranged in the protection buffer module and are in communication connection with the general control module; the protection buffer module comprises a first device and a second device, and the second device is arranged at the tail of the first device and is connected with the first device through a separating device; the data acquisition control module and the master control module are arranged in the first device; the data wireless return module comprises a first data wireless return module and a second data wireless return module, and the first data wireless return module is arranged in the first device and used for storing data detected by the detector in flight; the second wireless data backhaul module is arranged in the second device, is in communication connection with the first wireless data backhaul module, and is used for backing up data stored in the first wireless data backhaul module in real time; the data acquisition control module is used for detecting the descent speed of the detector in the landing process and the distance parameter of the area to be landed in real time and transmitting the parameters to the master control module; the master control module carries out online analysis on the landing process state of the detector based on the data acquired by the data acquisition control module, and judges whether the detector can land successfully or not so as to formulate related measures; the related measures comprise sending a control instruction for starting the separation of the first device and the second device to the protection buffering module, and sending a control instruction for triggering the second data wireless backhaul module to execute data backhaul.
In some preferred embodiments, the data acquisition control module, the master control module, the first wireless data backhaul module, and the second wireless data backhaul module are all provided with a buffer structure on the periphery for ensuring buffer protection and limiting fixation between adjacent modules.
The buffer structure comprises a first buffer structure and a second buffer structure, a plurality of first contact surface creases are formed on the contact surface of the first buffer structure and the corresponding module, and the surface of the first buffer structure, which is far away from the corresponding module, is a first buffer surface; the contact surface of the second buffer structure and the corresponding module is provided with a plurality of second contact surface creases, and the surface of the second buffer structure, which is far away from the corresponding module, is a second buffer surface; the first contact surface crease and the second contact surface crease are provided with a plurality of folds; the first buffer surface and the second buffer surface are sequentially arranged in the radial direction of the buffer structure; the adjacent first buffer surfaces and the second buffer surfaces are alternately arranged in a small-to-large mode in the circumferential direction of the buffer structure.
In some preferred examples, the second wireless backhaul module comprises one or more second antenna devices; when the second antenna devices are multiple, the second antenna device arrays are arranged on the periphery of the axis of the second device to form an omnidirectional antenna array.
In some preferred examples, the first data wireless backhaul module includes one or more first antenna devices for storing data detected in flight by the probe; when the number of the first antenna devices is multiple, the multiple first antenna device arrays are arranged on the periphery side of the axis of the first device.
In some preferred examples, the first device comprises at least two layers of shells, and adjacent shells are connected through a buffer device and used for protecting the data acquisition control module and the master control module arranged in the shells; the buffer device is formed by combining and superposing at least two buffer materials.
In some preferred examples, the first device comprises a striking part and a fixed part, the striking part is arranged at the front end of the fixed part, and the striking part is bullet-shaped; an overload sensor is arranged between the impact part and the fixing part and is in communication connection with the master control module; the data acquisition control module and the master control module are sequentially and fixedly arranged on the fixing part; the rear end of the fixing part is connected with the second device.
In some preferred examples, the separation device is an explosive bolt or a connector with an annular explosive cord.
In some preferred examples, the separation device is a hydraulically driven mechanically separated hydraulic catapult.
In some preferred embodiments, the separation device is an autonomous safety separation device; the autonomous safety separation device comprises an outer mounting ring, an inner cutting ring, a powder charging ring groove and an ignition device, wherein the inner cutting ring is arranged on the inner side of the outer mounting ring and forms an annular cavity with the outer mounting ring; the charge ring groove is wound in the cavity; the ignition device is arranged on the inner wall of the inner cutting ring and communicated with the powder charging ring groove.
In some preferred embodiments, a plurality of third antenna devices are arranged on the peripheral side of the second device, and a plurality of arrays of the third antenna devices are arranged outside the second device and connected with the second device through an ejection device; the ejection device is in signal connection with the master control device; the third antenna device is of a spherical structure.
The invention has the beneficial effects that: 1) the data rescue system provided by the invention can carry the detector or the impactor to perform real-time control on corresponding landing, and return rescue of flight process data is performed in time before a landing fault or the impactor is to be crashed, so that detailed parameters are provided for subsequent deep space detection, and effective propulsion of the deep space detection is performed.
2) The protective buffering module is separately arranged into a first device and a second device, and a first data wireless back-transmission module and a second data wireless back-transmission module which are independent from each other and back up in real time are simultaneously arranged, so that the time for starting separation is judged by a master control module based on the speed and/or the distance parameter of an area to be landed in the descending process of a detector or an impactor, which is acquired by a data acquisition control module, and a second data wireless back-transmission module in the second device is triggered to back up the back-up data; the following can be achieved by the split arrangement of the invention: firstly, when the data rescue system carries a detector or serves as the detector to execute a detection landing task, the general control module controls the separation device to start the separation of the second device and the first device when the general control module pre-judges a landing fault or failure based on the height parameter acquired by the data acquisition control module and the speed parameter of the detector, and simultaneously triggers the second data wireless return module to return data; secondly, when the data rescue system carries a detector or serves as the detector to execute a detection landing task, the separation device is controlled to start separation of the second device and the first device through a preset height arranged in the master control module, and meanwhile, the second data wireless return module is triggered to return data so as to store the data; thirdly, when the data rescue system carries a striker and the height far away from the impact influence range is ensured, the main control module controls the separation device to start the separation of the second device and the first device, and simultaneously triggers the second data wireless return module to return data for storing the data, so that the task of impacting a celestial body can be realized, and detailed data in the descending process of the striker can be obtained; fourth, when this data rescue system carries on the detector, perhaps when surveying the landing task as the detector execution, through the predetermined height that sets up in the total control module, controlling means's separation, trigger the wireless passback module of second data simultaneously and carry out the data passback in order to carry out the save of data, when first device landed to the celestial body surface success, through the wireless passback module of first data with the wireless passback module disconnect-type independent setting of second data, carry out the transmission of celestial body surface information and with the information interaction of encircleing ware or ground, can further carry out the detection instruction.
3) According to the invention, through the arrangement of the buffer structure, the protection design and the limit of the data acquisition control module and the master control module in the first device are realized, and the buffer structure is different from the fixed arrangement in the prior art, so that the weight of the whole structure is reduced, and the protection of the data acquisition control module and the master control module is further improved; through buffer structure's fold formula design, effectively fill the space between module and the device lateral wall, simultaneously through the setting of specific different buffer faces, make this buffer structure have characteristics such as elasticity, compressibility, flexibility, lightweight, further protect the module that corresponds, when first device successfully landed to the celestial body surface, guarantee that the landing impact reduces to the minimum to the influence of module. In addition, the second data wireless return module in the second device is wrapped and limited through the buffer structure arranged on the peripheral side, rigid connecting pieces inside the device are reduced, the weight of the device is reduced, and the second data wireless return module has great significance for the light weight in the deep space detection field.
4) The device provided by the invention has the advantages of scientific design, simple structure, light weight and high equipment integration level, and can realize data rescue under various detection scenes.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings.
FIG. 1 is a block diagram of an embodiment of a data rescue system applied to a extraterrestrial celestial object detector in accordance with the present invention.
Fig. 2 is a schematic sectional structure diagram of a first embodiment of a buffer structure applied to a data rescue system of a extraterrestrial celestial body detector in the invention.
Fig. 3 is a schematic sectional view of a second embodiment of a buffer structure applied to a data rescue system of a extraterrestrial celestial body detector in the invention.
The reference numbers are in sequence: 1. a data acquisition control module; 2. a master control module; 3. a navigation module; 4. a power supply module; 5. a first data wireless backhaul module; 6. a second data wireless backhaul module; 71. a first buffer structure, 72, a second buffer structure.
Detailed Description
The preferred embodiments of the present invention will be described below with reference to the accompanying drawings, and it will be understood by those skilled in the art that these embodiments are merely illustrative of the technical principles of the present invention and are not intended to limit the scope of the present invention.
The invention provides a data rescue system applied to the landing fault of a extraterrestrial celestial body detector, which comprises a protection buffer module, a data wireless return module, a data acquisition control module, a power supply module and a master control module, wherein the data acquisition control module and the master control module are arranged in the protection buffer module and are in communication connection with the master control module; the data acquisition control module is the core of the miniaturized data saving system, realizes power supply, charging and communication through an interconnection cable, can realize acquisition, processing and storage of key data and send the key data to the data wireless return module, has a power management function, reduces the power consumption of the miniaturized data saving system to realize complete and effective return of the data, and simultaneously accesses a large capacitor to store energy at the voltage input end of a power conversion chip, so that the instantaneous power failure problem of a battery during high overload impact under the condition of landing fault of a lander can be effectively solved; the power supply management module divides power supply into analog circuit power supply, single chip microcomputer power supply and antenna emission power supply, the single chip microcomputer power supply conversion chip starts to work after the miniaturized data saving system is started to work, the single chip microcomputer starts the analog circuit power supply conversion chip to work when data collection is started, and the single chip microcomputer closes the analog circuit power supply conversion chip after the collection is finished; the singlechip starts the power conversion chip of the data wireless return module to work during the working period of the data wireless return module, and the power chip is closed after the data transmission is finished; the power module has a power supply electric quantity protection function, so that the power supply reliability of the miniaturized data saving system is improved.
Furthermore, the protection buffer module comprises a first device and a second device, wherein the second device is arranged at the tail of the first device and is connected with the first device through a separating device; the data acquisition control module and the master control module are arranged in the first device; the data wireless return module comprises a first data wireless return module and a second data wireless return module, and the first data wireless return module is arranged in the first device and used for storing data detected by the detector in flight; the second wireless data backhaul module is arranged in the second device, is in communication connection with the first wireless data backhaul module, and is used for backing up data stored in the first wireless data backhaul module in real time; the data acquisition control module is used for detecting the descent speed of the detector in the landing process and the distance parameter of the area to be landed in real time and transmitting the parameters to the master control module; the main control module carries out online analysis on the landing process state of the detector based on the data acquired by the data acquisition control module, and judges whether the detector can land successfully or not so as to formulate related measures; the related measures comprise that a control instruction for starting the separation of the first device and the second device is sent to the protection buffer module, and a control instruction for triggering the second data wireless backhaul module to execute data backhaul is sent to the second data wireless backhaul module.
The invention is further described with reference to the following detailed description of embodiments with reference to the accompanying drawings.
Referring to fig. 1, the diagram is a schematic frame diagram of an embodiment of a data rescue system applied to a extraterrestrial celestial body detector in the present invention, and the data rescue system includes a data acquisition control module 1, a master control module 2, a navigation module 3, a power module 4, a first data wireless backhaul module 5, and a second data wireless backhaul module 6, where the data acquisition control module 1, the master control module 2, the navigation module 3, the power module 4, and the first data wireless backhaul module 5 are disposed in a first device of a protection buffer module, and the second data wireless backhaul module 6 is disposed in a second device of the protection buffer module. The data acquisition control module 1 is the core of a miniaturized data rescue system and is used for acquiring key data in the descending process of the detector, the data acquisition control module is in communication connection with the navigation module, or the data acquisition control module comprises the navigation module, the speed of the detector or the impactor carried by the data rescue system relative to the surface of the celestial body at the speed measurement moment can be calculated in real time through the navigation module, and the speed of the speed measurement wave beam direction can be determined; the data acquisition control module also comprises a laser ranging module which is used for detecting the height of a detector or an impactor carried by the data rescue system relative to the surface of the celestial body in real time; and the data acquisition control module transmits the detected descent speed of the detector in the landing process and/or the distance parameter of the area to be landed to the master control module.
Furthermore, the second device is arranged at the tail part of the first device and is connected with the first device through a separating device; the first data wireless return module is arranged in the first device and used for storing data detected in the flying process of the detector; the second wireless data backhaul module is arranged in the second device, is in communication connection with the first wireless data backhaul module, and is used for backing up data stored in the first wireless data backhaul module in real time; the second device is also provided with a power module for supplying power. The main control module carries out on-line analysis on the landing process state of the detector based on the data acquired by the data acquisition control module, and judges whether the detector can land successfully or not so as to formulate related measures, wherein the related measures comprise sending a control instruction for starting the separation of the first device and the second device to the protection buffer module and sending a control instruction for triggering the second data wireless return module to execute data return, namely when the main control system judges that the speed at different heights in the descending process of the detector has a problem and the landing fault occurs at a high probability, the main control module sends an instruction for controlling the separation of the first device and the second device to separate the second device from the first device, and simultaneously triggers the second data wireless return module in the second device to carry out return rescue on backup data; in addition, the first data wireless return module arranged in the first device can also carry out return rescue of process data, the explosion probability is probably knocked down when the actual landing fault occurs, synchronous data return of the first data wireless return module and the second data wireless return module can be carried out simultaneously, and the success of data rescue transmission is ensured.
Furthermore, buffer structures are arranged on the periphery sides of the data acquisition control module, the master control module, the first data wireless backhaul module and the second data wireless backhaul module in the first device, and are used for ensuring buffer protection and limiting fixation between adjacent modules; in the embodiment, each module is fixed on the first device by adopting the traditional side wall inside the first device or through a connecting device, but is wrapped on the periphery of each module by adopting the buffer structure, the limit fixation inside the first device is achieved through each buffer structure, the use of the connecting piece is reduced, the weight of the whole device is reduced, and the device has great significance for deep space exploration.
Further, referring to fig. 2, there is shown a schematic cross-sectional view of a first embodiment of a buffering structure applied to a data rescue system of a extraterrestrial celestial body detector in the present invention; the buffer structure comprises a
Furthermore, the joint of the first buffering surface and the second buffering surface is provided with a plurality of creases which are used for filling the gap between the first buffering structure and the second buffering structure and improving the buffering structure
Structural strength of (2).
Furthermore, the corners of the buffer structure wrapping module can be arranged in a regular cube manner or in a circular arc transition manner; in this embodiment, the preferred circular arc transition sets up, increases spacing and the close laminating to parcel module corner.
Further, the first buffer structure and the second buffer structure are both made of high-density and high-elasticity buffer materials.
Furthermore, the buffer device of the invention can also be arranged by combining the buffer structure with the existing buffer pad.
When receiving external impact force in the twinkling of an eye at first device landing to the celestial body surface, the surface of impact force to buffer structure is transmitted through the casing of first device, at first closely laminates through first buffer structure and corresponding module, compresses to shorten under the impact force effect, and then the outside contact laminating of rethread second buffer structure and corresponding module, and first buffer structure among the buffer structure, second buffer structure carry out the buffer protection of different levels according to the size of impact force.
It should be noted that, besides the two-layer buffer structure provided in an embodiment of the present invention, a multi-layer buffer structure may be flexibly provided according to the type of the detector or the type of the impactor carried by the data rescue system; in addition, besides the buffer structures arranged on the periphery of the corresponding modules in the first device, a plurality of gap-filled buffer structures are also arranged, and the limit fixation and the buffer effect enhancement of each module are carried out.
Furthermore, the number of the buffer structures arranged on the outer side of each module can be one or more, and when the number of the buffer structures arranged on the outer side of each module is multiple, the multiple buffer structures are sequentially wrapped from inside to outside; in addition, the buffer structure arranged at the outermost side can only keep the buffer structure main body consisting of the first buffer structure and the second buffer structure, and the first buffer surface and the second buffer surface of the first buffer structure and the second buffer structure are attached to the inner part of the first device, so that rigid collision cannot occur between the modules arranged in the first device and between the modules and the inner wall of the first device.
Further, referring to fig. 3, a schematic cross-sectional view of a second embodiment of the buffering structure applied in the data rescue system of the extraterrestrial celestial body detector in the present invention is shown; the buffer structure comprises a first buffer structure and a second buffer structure, the contact surface of the
Further, the buffering structure disposed inside the second device is the same as the buffering structure disposed in the first device, and therefore, the description thereof is omitted.
When the data rescue system carries a detector to carry out soft landing, taking Mars landing as an example, when the first device successfully touches the surface of the Mars, the impact load is absorbed by the buffer device, and the soft landing is realized; under the condition, in the descending process, the main control module does not detect and judge that the landing fault is likely to occur, so the second device and the first device form a data rescue system to integrally land, the successful landing backshell carries out the return of key data in the descending process through the first data wireless return module arranged in the first device, at the moment, the second data wireless return module arranged in the second device is used as the standby transmission of a detector, and the power supply module arranged in the second device is used as a standby power supply.
When the data rescue system carries the detector, or the data rescue system is used as the detector to execute a detection landing task, when the total control module pre-judges a landing fault or failure based on the height parameter acquired by the data acquisition control module and/or the speed parameter of the detector, or based on the preset height and/or the preset time, the total control module controls the separation device to start the separation of the second device and the first device, and simultaneously triggers the second data wireless return module to carry out data return.
Further, in the present invention, the separation means may be an explosive bolt or a connector with an annular explosive cord; the function of the explosive cable and the explosive bolt is to burst the connecting piece between the first device and the second device to realize separation.
Further, the separating device is a hydraulic drive mechanical separation type hydraulic catapult.
Furthermore, the separation device is an autonomous safe self-destruction device; the autonomous safety self-destruction device comprises an outer mounting ring, an inner cutting ring, a powder charging ring groove and an ignition device, wherein the inner cutting ring is arranged on the inner side of the outer mounting ring and forms an annular cavity together with the outer mounting ring; the charge ring groove is wound in the cavity; ignition sets up in the inner wall of interior cutting ring to communicate with the powder charge annular, wherein, ignition and total control module communication connection, and can ignite in order to realize the separation based on the instruction of total control module.
Further, the first device comprises at least two layers of shells, adjacent shells are connected through a buffer device, when the lander is in failure and suffers from high overload and strong impact, stress wave transmission is reduced through the buffer layer, and the buffer stroke is increased, so that instantaneous overload and average overload of the inner shell are reduced, and a control circuit, a power supply, a data acquisition control module, a master control module, a first data wireless return module and the like are protected; the buffer device is formed by combining and superposing at least two buffer materials.
Further, the outer shell of the first device mainly has the function of ensuring that the shell is not broken when a detector or other landers are in a landing fault, so that the inner shell, the data acquisition control module, the antenna transmission module and the like are protected. When the data saving system is used by carrying a detector, the outer shell can adopt a structure similar to a funnel, and the weight of the shell is reduced as much as possible on the premise of ensuring that the overload resistance meets the requirement; the inner shell can adopt a cylindrical structural design, so that a sufficient space is ensured for installing a data acquisition control module, a power supply module and the like, and a buffer material is used for filling the residual cavity of the shell for protecting all modules in the shell; the upper cover of the inner shell adopts a U-shaped structure and is in threaded connection with the inner shell, so that sufficient threaded connection is ensured, and the structural weight is reduced.
Further, in this embodiment, the antenna board in the first wireless data backhaul module is installed in a steel cup and fixed by potting adhesive, and buffer layers are added between the steel cup and the outer shell to reduce stress wave transmission and increase buffer stroke, thereby reducing instantaneous overload and average overload.
Further, the first device comprises an impact part and a fixed part, the impact part is arranged at the front end of the fixed part, and the impact part is bullet-shaped; an overload sensor is arranged between the impact part and the fixed part and is in communication connection with the master control module; the data acquisition control module and the master control module are sequentially and fixedly arranged on the fixing part; the rear end of the fixing part is connected with the second device.
Further, the first data wireless backhaul module comprises one or more first antenna devices for storing data detected by the probe in flight; when the number of the first antenna emitting devices is plural, the plural first antenna emitting device arrays are disposed on the axial line peripheral side of the first device.
Further, a second wireless backhaul module disposed in the second device includes one or more second antenna devices; when the number of the second antenna devices is multiple, the multiple second antenna device arrays are arranged on the periphery of the axis of the second device to form the omnidirectional antenna array.
Furthermore, a plurality of third antenna devices are arranged on the periphery of the second device, and a plurality of third antenna devices are arranged outside the second device in an array manner and are connected with the second device through an ejection device; the ejection device is in signal connection with the master control device; the third antenna device is of a spherical structure; in this embodiment, the signal is transmitted by the third antenna device that is shot, and when the plurality of third antenna devices are scattered on the surface of the celestial body according to the free fall, the plurality of third antenna devices can be fitted into a fitting circle centered on the first device landing point or the impact point.
In the invention, when the first antenna device, the second antenna device and the third antenna device transmit signals, the antenna transmission signals can be exposed through the control of the corresponding connecting device, and can be sealed in the corresponding devices when the signal transmission is not required, thereby reducing the damage to the antenna transmission device in the flying or descending process.
Furthermore, the first data wireless backhaul module and the second data wireless backhaul module both adopt technologies such as data compression, anti-interference, coherent reception, and the like, thereby ensuring effective transmission of signals.
Furthermore, the data wireless return module mainly realizes the return of key data acquired in the landing process after landing faults of the lander, a high-performance and professional narrow-band wireless communication chip is selected as the module, and an amplifier is adopted at the sending end to expand the communication distance so as to meet the requirement of the communication distance.
Further, the module adopts the MCU of high performance low-power consumption as main control unit, and main control MCU adopts SPI interface connection with UHF narrowband communication chip, directly controls the operation to UHF narrowband wireless communication chip, and main control module has serial ports half-duplex communication function simultaneously, and the user can directly send data for main control unit through the serial ports, and main control unit operation control UHF narrowband wireless communication chip sends user data with wireless form again.
Industrial or military grade high-performance devices are selected for the UHF narrow-band module in design, military grade anti-impact silicon crystal oscillators are selected for crystal oscillator selection, a master controller is selected as a high-performance low-power consumption MCU in the industry, and the wireless communication chip is selected from the most excellent industrial narrow-band wireless communication chip in the industry, so that the design requirement of low power consumption is met while the performance is met.
The power supply interface of the UHF narrow-band wireless communication module adopts a direct-current 5V power supply design, and then a power supply part on the module performs voltage reduction and voltage stabilization treatment to respectively provide a stable power supply for each functional part of the module. 1) A 1W power amplifier part of the UHF narrow-band wireless communication module adopts 5V power supply; 2) the UHF narrow-band wireless communication chip and the single chip microcomputer part adopt 3.3V voltage stabilization power supply.
Furthermore, the first antenna device, the second antenna device and the third antenna device can be high-gain directional antennas, and the parabolic antennas can rotate, so that the antennas can be ensured to point to a signal receiving target during flying and detecting, and the signal transmission effect is further improved.
Further, the data acquisition control module has the following principle: after passing through a conditioning circuit, a sensor signal enters a single chip microcomputer to be subjected to ADC (analog to digital converter) acquisition, encoded data are stored, and the data are output through a first serial interface under an appointed condition and are sent to an antenna transmitting module; the power management module is controlled by the single chip microcomputer; the main controller can start the miniaturized data rescue system through charging and starting the interface, and sends an instruction to the miniaturized data rescue system through the second serial interface.
Further, the power supply module is configured as follows: 1) a single chip microcomputer: 3.3V; 2) an analog circuit: A3.3V, A6.5V; 3) emission module, antenna module: D5V; the power supply module divides the power supply into an analog circuit power supply, a singlechip power supply and an antenna emission module power supply, and the singlechip power conversion chip starts to work after the data rescue system is started to work; when data acquisition is started, the single chip microcomputer starts the analog circuit power conversion chip to work, and after the data acquisition is finished, the single chip microcomputer closes the analog circuit power conversion chip; and the singlechip starts the power supply conversion chip of the antenna emission module to work during the working period of the antenna emission module, and the power supply chip is closed after the data emission is finished.
When the data rescue system carries the detector or is used as the detector to execute a detection landing task, the total control module is used for carrying out the prediction of the landing fault or failure condition based on the speed parameters and the height parameters of the detector acquired by the navigation module and the laser ranging module in the data acquisition control module, the total control module controls the separation device to start the separation of the second device and the first device, and simultaneously triggers the second data wireless return module to carry out data return, one or more second antenna devices arranged on the periphery side of the axis of the second device can be flexibly started to carry out data transmission according to the transmission distance and other parameters, and the energy is saved.
When this data rescue system carries on the detector in the invention, perhaps when surveying the landing task as the detector execution, through the preset height that sets up in the total control module, control separator starts the separation of second device and first device, trigger the wireless passback module of second data simultaneously and carry out the data passback in order to carry out the save of data, in this embodiment, mainly through the detection data of total control system and the contrast feedback of settlement data, continue the rescue passback of data, the false judgement condition of supplementary system to the probability landing fault of minimums, further perfect this data rescue system.
When the data rescue system carries the impactor, the main control module controls the separating device to start the separation of the second device and the first device when the height far away from the impact influence range is ensured, and simultaneously the second data wireless return module is triggered to return data to store the data, so that the task of impacting a celestial body can be realized, and detailed data of the impactor in the descending process can be obtained.
While the invention has been described with reference to a preferred embodiment, various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention, especially if structural conflict does not exist and the technical features mentioned in the various embodiments may be combined in any way; it is intended that the invention not be limited to the particular embodiments disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.
In the description of the present invention, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like, which indicate directions or positional relationships, are based on the directions or positional relationships shown in the drawings, which are for convenience of description only, and do not indicate or imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The terms "comprises," "comprising," or any other similar term are intended to cover a non-exclusive inclusion, such that a process, 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, article, or apparatus.
So far, the technical solutions of the present invention have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present invention is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the invention, and the technical scheme after the changes or substitutions can fall into the protection scope of the invention.