CN111174821A - Temperature and humidity sensor and monitoring system for carrier rocket - Google Patents
Temperature and humidity sensor and monitoring system for carrier rocket Download PDFInfo
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- CN111174821A CN111174821A CN201911193614.5A CN201911193614A CN111174821A CN 111174821 A CN111174821 A CN 111174821A CN 201911193614 A CN201911193614 A CN 201911193614A CN 111174821 A CN111174821 A CN 111174821A
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- 238000012544 monitoring process Methods 0.000 title claims description 36
- 230000001681 protective effect Effects 0.000 claims abstract description 40
- 239000000523 sample Substances 0.000 claims abstract description 31
- 238000005259 measurement Methods 0.000 claims abstract description 26
- 238000005245 sintering Methods 0.000 claims abstract description 16
- 230000007613 environmental effect Effects 0.000 claims abstract description 6
- 238000004891 communication Methods 0.000 claims description 6
- 239000002245 particle Substances 0.000 claims description 5
- 229920006351 engineering plastic Polymers 0.000 claims description 4
- 235000008694 Humulus lupulus Nutrition 0.000 claims description 3
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- 229920006362 Teflon® Polymers 0.000 claims 1
- -1 polytetrafluoroethylene Polymers 0.000 description 9
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 9
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- 238000012360 testing method Methods 0.000 description 7
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- G—PHYSICS
- G08—SIGNALLING
- G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
- G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
- G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
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Abstract
一种用于运载火箭的温湿度传感器，属于测量技术领域，包括温湿度敏感头、电路板、电池、电池腔、法兰、天线；温湿度敏感头用于敏感环境温度和湿度；电路板用于采集温湿度敏感头的测量数据，并通过天线发送测量数据；电池舱作与法兰连接后形成中空腔体，电池、电路板、天线均安装在腔体内；电池用于对电路板供电；温湿度敏感头包括ABS防护罩、整体烧结防护罩、湿敏元件、温度敏感元件、探杆；湿敏元件和温度敏感元件安装在探杆的端部，整体烧结防护罩套装在探杆上；ABS防护罩套装在整体烧结防护罩上；ABS防护罩在湿敏元件和温度敏感元件的所在区域设有镂空槽；探杆和ABS防护罩均与法兰连接。
A temperature and humidity sensor for a launch vehicle belongs to the technical field of measurement, and includes a temperature and humidity sensitive head, a circuit board, a battery, a battery cavity, a flange, and an antenna; the temperature and humidity sensitive head is used for sensitive environmental temperature and humidity; It is used to collect the measurement data of the temperature and humidity sensitive head, and send the measurement data through the antenna; the battery compartment is connected with the flange to form a hollow cavity, and the battery, circuit board and antenna are installed in the cavity; the battery is used to supply power to the circuit board; The temperature and humidity sensitive head includes an ABS protective cover, an integral sintering protective cover, a humidity sensitive element, a temperature sensitive element, and a probe rod; the humidity sensitive element and the temperature sensitive element are installed at the end of the probe rod, and the integral sintered protective cover is sleeved on the probe rod; The ABS protective cover is set on the integral sintered protective cover; the ABS protective cover is provided with a hollow groove in the area where the humidity sensitive element and the temperature sensitive element are located; the probe rod and the ABS protective cover are connected with the flange.
Description
Technical Field
The invention relates to a temperature and humidity sensor and a monitoring system for a carrier rocket, and belongs to the technical field of measurement.
Background
At present, the traditional wired mode is adopted for a plurality of ground test systems of the carrier rocket, and various problems are faced, such as complicated work of laying, testing and withdrawing long cables; the wire is easy to break in the using process; the long-term exposure to severe environment leads to easy aging and the like.
For the environmental monitoring of the fairing, particularly for large rockets, as the position of the fairing is higher, long cables up to tens of meters are required to be laid from the ground, the human resource cost is increased, and the working efficiency is reduced. And a set of fixed wired network topology is difficult to meet the application requirements of numerous projects, and for different models, cables with different lengths need to be designed and produced independently according to actual conditions, so that the system development cost and the management and guarantee cost are increased to a certain extent.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the temperature and humidity sensor comprises a temperature and humidity sensing head, a circuit board, a battery cavity, a flange and an antenna; the temperature and humidity sensing head is used for sensing the temperature and the humidity of the environment; the circuit board is used for collecting the measurement data of the temperature and humidity sensing head and sending the measurement data through the antenna; the battery cabin is connected with the flange to form a hollow cavity, and the battery, the circuit board and the antenna are all arranged in the cavity; the battery is used for supplying power to the circuit board; the temperature and humidity sensing head comprises an ABS protective cover, an integral sintering protective cover, a humidity sensitive element, a temperature sensitive element and a probe rod; the humidity sensitive element and the temperature sensitive element are arranged at the end part of the probe rod, and the integral sintering protective cover is sleeved on the probe rod; the ABS protective cover is sleeved on the integral sintering protective cover; the ABS protective cover is provided with hollow grooves in the areas where the humidity sensitive element and the temperature sensitive element are located; the probe rod and the ABS protective cover are both connected with the flange.
The purpose of the invention is realized by the following technical scheme:
a temperature and humidity sensor for a carrier rocket comprises a temperature and humidity sensing head, a circuit board, a battery cavity, a flange and an antenna;
the temperature and humidity sensing head is used for sensing the temperature and the humidity of the environment; the circuit board is used for collecting the measurement data of the temperature and humidity sensing head and sending the measurement data through the antenna; the battery cabin is connected with the flange to form a hollow cavity, and the battery, the circuit board and the antenna are all arranged in the cavity; the battery is used for supplying power to the circuit board;
the temperature and humidity sensing head comprises an ABS protective cover, an integral sintering protective cover, a humidity sensitive element, a temperature sensitive element and a probe rod; the humidity sensitive element and the temperature sensitive element are arranged at the end part of the probe rod, and the integral sintering protective cover is sleeved on the probe rod and is connected with the probe rod; the ABS protective cover is sleeved on the integral sintering protective cover; the integral sintering protective cover is made by sintering polytetrafluoroethylene particles and has a cylindrical structure; the ABS protective cover is provided with hollow grooves in the areas where the humidity sensitive element and the temperature sensitive element are located; the probe rod and the ABS protective cover are both connected with the flange; the probe rod is made of ABS engineering plastics.
Preferably, the flange is provided with a clamping plate and a fastening device, and the temperature and humidity sensor can be clamped at the opening position of the carrier rocket through the fastening device and the clamping plate.
Preferably, polytetrafluoroethylene pads are arranged on the flanges and the clamping plates and are used for preventing the flanges and the clamping plates from wearing the structure of the carrier rocket.
Preferably, the outer diameter of the ABS shield does not exceed 18 mm.
Preferably, the circuit board transmits signals by adopting a ZigBee communication protocol standard.
Preferably, the temperature and humidity sensor is used for measuring the temperature and humidity inside and outside the fairing of the carrier rocket.
Preferably, the continuous power supply time of the battery is not less than 30 days.
A monitoring system for a carrier rocket comprises a wireless receiving controller, a wireless handheld beacon machine, an environment monitoring workstation and a plurality of temperature and humidity sensors;
the temperature and humidity sensors are used for measuring the temperature and humidity inside and outside the carrier rocket fairing, and measurement data can be sent to the wireless receiving controller through multiple hops among the temperature and humidity sensors; the wireless receiving controller sends the measurement data of the temperature and humidity sensors to an environment monitoring workstation; the environment monitoring workstation is used for monitoring and interpreting the measurement data;
the wireless handheld beacon is used for sending a control instruction to the temperature and humidity sensor and adjusting the working mode of the temperature and humidity sensor.
Preferably, the working modes of the temperature and humidity sensor include a normal acquisition mode, a high-speed acquisition mode and a standby sleep mode.
Preferably, the packet loss rate of the measurement data of the monitoring system is not higher than 5% o.
Compared with the prior art, the invention has the following beneficial effects:
the invention provides a wireless, low-power-consumption and long-standby fairing environment monitoring system for a carrier rocket, which meets the long-time monitoring requirement of the environment of a fairing of the carrier rocket. The method can complete quick and automatic networking without erecting network infrastructure, reduce testing personnel and testing time, improve the reliability and transmission efficiency of data wireless transmission, ensure that remote nodes can still reliably transmit information, and check the states, working modes, real-time monitoring data and the like of all sensors by utilizing upper computer monitoring software. The method is applicable to various carrier rockets through commercialization, can realize rapid arrangement of the fairing environment monitoring system, has the characteristics of low power consumption, long standby, high efficiency and the like, can continuously monitor for more than 30 days on line, and has the packet loss rate not higher than 5 per thousand. The temperature and humidity sensor is designed in an integrated mode, a lithium battery is contained in the temperature and humidity sensor for self power supply, the size and the weight are reduced, power consumption is greatly reduced by adopting Zigbee wireless communication, and more importantly, flexible and reliable arrangement and selection of measuring points of the fairing of the carrier rocket are achieved.
Drawings
Fig. 1 is a wireless environment monitoring system architecture for a fairing.
Fig. 2 is a schematic structural diagram of the temperature and humidity sensor.
Fig. 3 is an exploded view of the temperature and humidity sensor.
Fig. 4 is a partial structural schematic diagram of the temperature and humidity sensing head.
FIG. 5 is a scanning electron micrograph of a polytetrafluoroethylene shield.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
A wireless fairing environment monitoring system comprises a wireless sensor node, a wireless receiving controller, a wireless handheld beacon and an environment monitoring workstation. And wireless temperature and humidity sensors are arranged in local areas outside the inner cover of the fairing cover and are used for measuring temperature and humidity environment parameters. The sensors transmit data to the wireless receiving controller through multi-hop, and the wireless receiving controller transmits the data to the wireless data terminal monitoring software of the front-end testing room through wired Ethernet for real-time processing and display, and transmits the data to the rear-end data browsing workstation through the optical fiber of the general network for interpretation and display. In addition, the front-end personnel can control the working modes (normal acquisition, high-speed acquisition and standby dormancy) of the wireless sensor through the wireless remote control terminal and can synchronously display monitoring data, as shown in fig. 1.
The overall technical scheme is as follows:
1) adopt wireless sensor monitoring system's scheme, can save loaded down with trivial details long cable laying, test, withdraw work, reduce manpower resources, promote efficiency of software testing.
2) The wireless sensor adopts an integrated design, a lithium battery is contained in the wireless sensor for self power supply, the size and the weight are reduced, the Zigbee wireless communication is adopted for greatly reducing the power consumption, and the long-time continuous power-on monitoring of the fairing environment for more than 30 days can be realized. Meanwhile, the sensor has three working modes of silence, normal and high speed, can be set and switched on line, and is suitable for different application scene requirements.
3) The sensor structural design is provided with structures such as connecting bolts, the outer wall of the fairing is not required to be specially processed with threaded holes, the clamping plate buckling mechanism is ingeniously designed, the sensor can be fastened at the air outlet of the fairing, the complex sensor mounting and dismounting work is omitted, and meanwhile, the environment monitoring requirement of the fairing is met through the reasonable arrangement of measuring points.
Before the installation, splint arrow point is "from", and the buckle subassembly inserts the radome fairing air outlet, anticlockwise rotation splint, and the arrow point is "closed", and in splint embedding sensor base draw-in groove, the butterfly nut of screwing can accomplish the installation simultaneously.
In the installation process of the buckle assembly, the contact part of the buckle assembly and the arrow wall is made of polytetrafluoroethylene nonmetal materials, so that the arrow wall cannot be damaged. The buckle components are connected by mechanical structures, so that the generation of redundant materials in the installation and disassembly processes can be effectively avoided.
4) The humidity of part of the emission field is high, the salt spray environment is severe, and the sensor probe is easily corroded by the salt spray. The integrally sintered polytetrafluoroethylene protective cover is used for protecting the probe, is formed by sintering polytetrafluoroethylene particles, has small porosity, can reduce the deposition of salt spray particles, meets the requirement of monitoring the environment temperature and humidity in real time, and greatly improves the salt spray resistance and the environment adaptability of products. The sensor and probe protection structures are shown in figures 2-4, and the scanning electron microscope picture of the section of the integrally sintered polytetrafluoroethylene protection cover is shown in figure 5.
5) The sensor adopts miniaturized design, satisfies actual installation environment demand, nevertheless can bring the concentrated problem of generating heat, and the heat spreads the sensitive probe fast and can lead to the humiture precision of measuring to be out of alignment. In order to reduce the influence of the self-heating of the sensor and the temperature rise of the shell on the measurement precision, nonmetal (0.25W/m.k ABS engineering plastic with lower heat conductivity coefficient and better processability and mechanical strength) is adopted as a probe material, and a longer sensitive probe and a lead with a smaller cross section area are adopted, so that the speed of transferring the heat of the circuit board to the temperature and humidity probe can be reduced, and the reliability of a product is further improved.
6) By adopting a self-organizing network mode, each sensor can be used as a relay node to forward sensing data acquired by other nodes until the sensing data are sent to the main node, so that special relay equipment is saved while the requirement is met.
7) The wireless sensing network of the fairing is fused with the master control network, test data directly enter the master control network, are framed according to a specific data frame format and then are sent to a rear-end fairing environment monitoring workstation, the master control network command communication workstation and a power measurement and control parameter display workstation for a rear-end measurement and development hall designer to carry out real-time monitoring and interpretation. Meanwhile, the time synchronization frame sent by the command workstation of the master control network can be received to complete the time synchronization of the equipment.
8) The wireless receiving controllers are designed in a redundant mode, the system is provided with 2 wireless receiving controllers which are mutually in hot backup, and meanwhile wireless sensing data are received and forwarded, so that the reliability of a wireless sensing network is improved.
Example 1:
a temperature and humidity sensor for a carrier rocket comprises a temperature and humidity sensing head, a circuit board, a battery cavity, a flange and an antenna;
the temperature and humidity sensing head is used for sensing the temperature and the humidity of the environment; the circuit board is used for collecting the measurement data of the temperature and humidity sensing head and sending the measurement data through the antenna; the battery cabin is connected with the flange to form a hollow cavity, and the battery, the circuit board and the antenna are all arranged in the cavity; the battery is used for supplying power to the circuit board;
the temperature and humidity sensing head comprises an ABS protective cover, an integral sintering protective cover, a humidity sensitive element, a temperature sensitive element and a probe rod; the humidity sensitive element and the temperature sensitive element are arranged at the end part of the probe rod, and the integral sintering protective cover is sleeved on the probe rod and is connected with the probe rod; the ABS protective cover is sleeved on the integral sintering protective cover; the integral sintering protective cover is made by sintering polytetrafluoroethylene particles and has a cylindrical structure; the ABS protective cover is provided with hollow grooves in the areas where the humidity sensitive element and the temperature sensitive element are located; the probe rod and the ABS protective cover are both connected with the flange; the probe rod is made of ABS engineering plastics.
The flange is provided with a clamping plate and a fastening device, and the temperature and humidity sensor can be clamped at the opening position of the carrier rocket through the fastening device and the clamping plate. And polytetrafluoroethylene pads are arranged on the flanges and the clamping plates and are used for preventing the flanges and the clamping plates from wearing the structure of the carrier rocket.
The outer diameter of the ABS protective cover is not more than 18 mm. The circuit board sends signals by adopting a ZigBee communication protocol standard. The temperature and humidity sensor is used for measuring the temperature and the humidity inside and outside the carrier rocket fairing. The continuous power supply time of the battery is not less than 30 days.
A monitoring system for a carrier rocket is characterized by comprising a wireless receiving controller, a wireless handheld beacon machine, an environment monitoring workstation and a plurality of temperature and humidity sensors;
the temperature and humidity sensors are used for measuring the temperature and humidity inside and outside the carrier rocket fairing, and measurement data can be sent to the wireless receiving controller through multiple hops among the temperature and humidity sensors; the wireless receiving controller sends the measurement data of the temperature and humidity sensors to an environment monitoring workstation; the environment monitoring workstation is used for monitoring and interpreting the measurement data;
the wireless handheld beacon is used for sending a control instruction to the temperature and humidity sensor and adjusting the working mode of the temperature and humidity sensor.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
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| CN201911193614.5A CN111174821A (en) | 2019-11-28 | 2019-11-28 | Temperature and humidity sensor and monitoring system for carrier rocket |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911193614.5A CN111174821A (en) | 2019-11-28 | 2019-11-28 | Temperature and humidity sensor and monitoring system for carrier rocket |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112067081A (en) * | 2020-07-14 | 2020-12-11 | 上海宇航系统工程研究所 | Method for monitoring additional parameters before launching of carrier rocket |
| CN113916052A (en) * | 2021-08-30 | 2022-01-11 | 北京宇航系统工程研究所 | Ground wireless monitoring method for carrier rocket |
| CN119364308A (en) * | 2024-12-26 | 2025-01-24 | 上海航天设备制造总厂有限公司 | Method and system for collecting temperature and humidity parameters inside launch vehicle fairing |
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