CN111874263A - In-situ detector for near-earth space atmospheric environment carried by launch vehicle - Google Patents
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- CN111874263A CN111874263A CN202010697294.3A CN202010697294A CN111874263A CN 111874263 A CN111874263 A CN 111874263A CN 202010697294 A CN202010697294 A CN 202010697294A CN 111874263 A CN111874263 A CN 111874263A
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Abstract
The embodiment of the invention provides a near-earth space atmospheric environment in-situ detector carried by a carrier rocket, which is characterized by comprising the following components: the system comprises a power supply module, a wireless communication module, a protective shell, a central control module, a thermal control module and a pose measurement module; the protective shell is a hollow sphere, a spherical closed cabin body is formed by two semicircular shells, and the cabin body is internally used for placing the modules; the thermal control module is used for acquiring and adjusting the temperature of the cabin body and ensuring that the temperature in the cabin body is stable and controllable during a task; the pose measurement module is used for acquiring attitude information such as the position, the acceleration, the angular velocity and the like of the detector in real time; the wireless communication module is used for transmitting the temperature and pose measurement acquired by the detector and various internal acquired information to the ground through the built-in antenna for receiving and analyzing; the power supply module supplies power to other modules in the detector; the central control module is used for integrating data of other modules and completing functions of collecting, distributing, fault diagnosing and data processing of detection information.
Description
Technical Field
The invention belongs to the technical field of detection applied to near-earth space (with the height of 20-150km), and relates to a near-earth space atmospheric environment in-situ detector carried by launch of a carrier rocket.
Background
The near-earth space (height 20-150km) is a transition region of an aviation and aerospace service region, the research on the atmospheric environment of the region has great value for the research on military affairs, communication, climate evolution and the like, the region gradually becomes the focus of the current domestic and foreign environment research in recent years, and the current means capable of carrying out the in-situ detection of the atmospheric environment of the region has the following defects in application, and the defects are mainly shown in the following:
1. the existing conventional detection scheme is difficult to meet the requirements. In the existing means for carrying out the detection of the near-earth space environment by the ground-based radar, the optical means is easily influenced by the weather environment, the radio observation elements are only limited to wind fields, and only fixed-point area detection can be carried out; the space-based satellite is mainly used for carrying out remote sensing detection by using a occultation technology, fixed-point detection cannot be carried out, the detection effective height range is low, and the elements are limited. Both detection modes are difficult to meet the requirements of scientific research at present;
2. the detection space is not covered. At present, the atmospheric environment in the near-earth space (with the height of 20-150km) has the in-situ detection capability: the atmosphere in-situ detection means below 30km can carry various means such as balloons, airplanes, airships and the like, and detection is carried out through a conventional sonde; the detection can be carried out by various devices such as an expansion falling ball device, a parachute sonde and the like within 30-60 km; the in-situ detection equipment which can perform detection by utilizing an expansion falling ball at 60-100km and even cover the whole height range of 20-150km is not available at present;
3. the launch carrying means are limited. At present, atmospheric environment in-situ detection of a near-earth space (with the height of 20-150km) is carried out by using a sounding rocket carrying detection device basically; the carrier rocket is used for carrying out in-situ detection, the speed of the carrier rocket is much higher than that of an air sounding rocket, the speed of the detector after being separated from the rocket far exceeds the speed of the detector when the air sounding rocket is separated, the requirement on the aerodynamic thermal design protection capability of the detection device is high, and the existing detection device basically does not have the protection capability required by carrying, launching and carrying out detection on the carrier rocket;
4. the existing in-situ detection has higher cost. For the detection under the height of 30km, low-cost sounding balloons can be utilized, the atmosphere in-situ detection above the height of 30km depends on the carrying and launching of sounding rockets at present, and the single detection cost is high;
the existing near-earth space atmospheric environment detection technology has the defects of small coverage area, limited measurement space, time, elements and the like, the existing in-situ detection equipment also has the defects of high detection cost, small detection space range and the like, and a detection device for carrying out in-situ detection on an atmospheric environment with the height of 20-150km by using a carrier rocket is not available at present.
Disclosure of Invention
The invention aims to provide a near-earth space atmospheric environment in-situ detector carried by a carrier rocket, which is characterized by comprising the following components: the system comprises a power supply module 1, a wireless communication module 2, a protective shell 3, a central control module 6, a thermal control module 5 and a pose measurement combination; wherein,
the protective shell 3 is a hollow sphere, and a spherical closed cabin body is formed by two semicircular shells and is used for placing the modules;
the thermal control module 5 is used for collecting and adjusting the temperature of the cabin body, and ensuring that the temperature in the cabin body is stable and controllable during a task;
the position and attitude measurement combination (the three-axis accelerometer 4, the GNSS positioning navigation unit 7 and the gyroscope 8) is used for acquiring the position and attitude information of the detector in real time;
the wireless communication module is used for sending the information acquired by the thermal control module and the pose measurement module to the ground through the built-in antenna for receiving and analyzing;
the power supply module supplies power to other modules in the detector;
the central control module 6 is used for integrating data of other modules and completing functions of collecting, distributing, fault diagnosing and data processing of detection information.
Preferably, the protective shell 3 is made of a non-metal hard wave-transmitting material, and the outer side surface is smooth.
Preferably, the outer material of the protective shell 3 has high temperature resistance and heat resistance; the middle is a heat insulation layer; the interior is a cabin body.
Preferably, the thermal control module 5 comprises a temperature sensor, a heater and a heat conducting material; the temperature sensor is used for acquiring the internal temperature of the detector; the heater and the heat conducting material are used for balancing the temperature inside the detector.
Preferably, the pose measurement module comprises a GNSS positioning and navigation unit for implementing positioning information during an in situ survey probe task.
Preferably, the pose measurement module further comprises a three-axis accelerometer (4) arranged at the centroid position of the detector and used for measuring the acceleration of the in-situ detector during the detection and the falling.
Preferably, the pose measurement combination comprises a GNSS positioning navigation unit (7) for implementing positioning information during an in situ measurement probe task.
Preferably, the pose measurement module further comprises a gyroscope (8) for implementing measurement of angular velocity of rotation during a detection fall of the in-situ detector.
The hard falling ball in-situ detection device provided by the invention can adapt to harsh environmental conditions such as temperature, vibration, impact, high speed and the like in the launching process of a carrier rocket, can carry out in-situ detection on atmospheric environmental parameters in a height space with the height of 20-150km, has the characteristics of small volume and light weight, can fully utilize surplus transportation capacity on the basis of the main launching task of the carrier rocket, and has the advantage of not influencing the main launching task of the carrier rocket. Compared with the existing in-situ detection device, the invention has the advantages that: the device can be carried with a carrier rocket for detection and can be suitable for detection activities of a sounding rocket; the device has the detection capability of full coverage of the in-situ detection range of the high atmospheric environment with the height of 20-150 km.
Drawings
FIG. 1 is a schematic structural diagram of a near-earth space atmospheric environment detector based on carrier rocket carrying;
FIG. 2 is a schematic diagram of a full detection process of the near-earth space atmospheric environment detector based on carrier rocket carrying, launching, separation from the rocket, throwing out and detection.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
The invention aims to provide an in-situ detection device which is applied to environment detection in a near-earth space (with the height of 20-150km) and is based on carrier rocket carrying and launching. The problem that an in-situ detection device cannot adapt to the severe requirements of pneumatic thermal protection in the launching and detection processes of a carrier rocket is solved; the problems that the conventional detection device has a limited vertical detection range and cannot cover the detection of a height space with the whole height of 20-150km and the like are solved. In order to solve the defects of the prior art, the invention provides the hard ball falling detector which has the strict requirement on the adaptability to the aerodynamic thermal environment for adapting to the launching of a carrier rocket and can cover the in-situ detection of the atmospheric environment in the space with the height of 20-150km and the height close to the ground. And the high-precision in-situ detection technical capability is realized.
The invention provides a near-earth space atmospheric environment in-situ detector carried by a carrier rocket, which is characterized by comprising the following components: the system comprises a power supply module 1, a wireless communication module 2, a protective shell 3, a central control module 6, a thermal control module 5 and a pose measurement combination (a three-axis accelerometer 4, a GNSS positioning navigation unit 7 and a gyroscope 8); the protective shell 3 is a hollow sphere, and a spherical closed cabin body is formed by two semicircular shells and is used for placing the modules; the thermal control module 5 is used for collecting and adjusting the temperature of the cabin body, and ensuring that the temperature in the cabin body is stable and controllable during a task; the pose measurement module is used for acquiring the position and posture information of the detector in real time; the wireless communication module is used for sending the information acquired by the thermal control module and the pose measurement module to the ground through the built-in antenna for receiving and analyzing; the power supply module supplies power to other modules in the detector; the central control module 6 is used for integrating data of other modules and completing functions of collecting, distributing, fault diagnosing and data processing of detection information.
The hard ball falling detector based on carrier rocket carrying develops in-situ detection through carrier rocket carrying, the detector is installed in a first sub-stage of the carrier rocket, a second sub-stage of the carrier rocket is separated and then passively pops up in the launching process of the carrier rocket, the main launching task of the carrier rocket is not affected, the detector develops in-situ measurement of environmental parameters in the throwing process in the near-ground space (height of 20-150km) environment, and detection data are transmitted to the ground in real time.
According to one embodiment of the invention, the overall design configuration of the detector adopts a smooth sphere closed structure, the structure is made of nonmetal hard wave-transmitting materials, the outer part of the structure is a heat-proof layer, the middle part of the structure is a heat-insulating layer, and the inner part of the structure is an instrument cabin (for installing all functional components and modules). Wherein, the heat-proof layer adopts ceramic double-core material, has high temperature resistant protective capability.
According to one embodiment of the invention, the thermal control module 5 adopts temperature measurement, active heat conduction and temperature heating modes, and the temperature in the controller cabin is stably controllable during a task. Acquiring the temperature of each part in the detector by adopting a temperature sensor; the heater and the heat conducting material are adopted to balance the internal temperature and the change rate of the detector.
According to one embodiment of the invention, the pose measurement combination further comprises a three-axis accelerometer 4 disposed at the detector centroid position for performing measurement of three-axis acceleration during the in-situ detector detection fall. The pose measurement assembly comprises a GNSS positioning navigation unit 7 for implementing positioning information in the in-situ measurement probe task process. The inertial measurement unit comprises a gyroscope 8; for implementing a measurement of the angular velocity of rotation during the fall detected by the in-situ detector. For example, a three-axis accelerometer 4, configured to perform measurement of three-axis acceleration information during a drop detected by the in-situ probe; the GNSS positioning navigation unit 7 is used for implementing positioning information in the task process of the in-situ measurement detector, and comprises speed, position and time elements; and the gyroscope 8 is used for implementing measurement of rotation angular velocity information during the detection and the falling of the in-situ detector.
According to an embodiment of the invention, the central control module 6 performs comprehensive management on information and electricity of the detector, integrates the realization of electrical information functions such as control, measurement and information processing, and completes functions such as information interaction, data management, fault diagnosis and processing of the detector.
According to an embodiment of the present invention, the wireless communication module 2 is responsible for data communication between the detector and the ground, and transmits the detection data to the ground in real time. For example, GNSS global navigation positioning information, acceleration, rotational angular velocity data, and probe internal temperature information of a hard ball-falling probe are transmitted to the ground via a built-in antenna and are received and analyzed.
According to one embodiment of the invention, the power management module 1 is responsible for power management of the detector, including power supply functions.
The hard falling ball in-situ detection device provided by the invention can adapt to harsh environmental conditions such as temperature, vibration, impact, high speed and the like in the launching process of a carrier rocket, can carry out in-situ detection on atmospheric environmental parameters in a height space with the height of 20-150km, has the characteristics of small volume and light weight, can fully utilize surplus transportation capacity on the basis of the main launching task of the carrier rocket, and has the advantage of not influencing the main launching task of the carrier rocket. Compared with the existing in-situ detection device, the invention has the advantages that: the device can be carried with a carrier rocket for detection and can be suitable for detection activities of a sounding rocket; the device has the detection capability of full coverage of the in-situ detection range of the high atmospheric environment with the height of 20-150 km.
As shown in fig. 2, which is a schematic diagram of the full detection process of the present invention, the detector is installed in a stage section of a launch vehicle, enters a near-earth space along with launch of the launch vehicle, performs an in-situ detection activity of atmospheric environmental parameters of the near-earth space within a height range of 20-150km on a drop trajectory path of the launch vehicle after a first-and-second-stage separation, a backup separation, a pop-up, a high-throw, and a drop after the launch vehicle is separated, and transmits measurement information of the acquired detector, such as time, position, speed, acceleration, angular velocity, temperature, etc., to a ground receiving device in real time, and the measurement information can be used for settling environmental parameter information of the space atmospheric temperature, pressure, density, wind field, etc., of an inverted.
It will be apparent to those skilled in the art that various changes and modifications may be made in the invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (7)
1. An in-situ detector for an atmospheric environment in a near-earth space carried by a carrier rocket, the in-situ detector is characterized by comprising: the device comprises a power supply module (1), a wireless communication module (2), a protective shell (3), a central control module (6), a thermal control module (5) and a pose measurement combination; wherein,
the protective shell (3) is a hollow sphere, and a spherical closed cabin body is formed by two semicircular shells and is used for placing the modules;
the thermal control module (5) is used for acquiring and adjusting the temperature of the cabin body and ensuring that the temperature in the cabin body is stable and controllable during a task;
the pose measurement module is used for acquiring the position and posture information of the detector in real time;
the wireless communication module is used for sending the information acquired by the thermal control module and the pose measurement module to the ground through the built-in antenna for receiving and analyzing;
the power supply module supplies power to other modules in the detector;
the central control module (6) is used for integrating data of other modules and completing functions of collecting, distributing, fault diagnosing and data processing of detection information.
2. The in-situ probe according to claim 1, wherein the protective shell (3) is made of a non-metallic rigid wave-transparent material and has a smooth outer side.
3. The in-situ probe according to claim 2, characterized in that the outer material of the protective shell (3) has high temperature protection capability; the middle is a heat insulation layer; the interior is a cabin body.
4. The in-situ probe according to claim 1, wherein the thermal control module (5) comprises a temperature sensor, a heater and a thermally conductive material; the temperature sensor is used for acquiring the internal temperature of the detector; the heater and the heat conducting material are used for balancing the temperature inside the detector.
5. The in-situ detector of claim 1, characterized in that the pose measurement module further comprises a three-axis accelerometer (4) disposed at the detector's centroid position for performing measurements of acceleration during a detection throw by the in-situ detector.
6. The in-situ probe according to claim 5, characterized in that the pose measurement module comprises a GNSS positioning navigation unit (7) for implementing positioning information during in-situ probe tasks.
7. The in-situ detector of claim 6, characterized in that the pose measurement module further comprises a gyroscope (8) implemented to measure rotational angular velocity during in-situ detector detection toss.
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Cited By (4)
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| CN114136366A (en) * | 2021-10-29 | 2022-03-04 | 中国人民解放军63921部队 | Space environment comprehensive monitoring system based on rail leaving tail sublevel |
| CN114459949A (en) * | 2021-10-18 | 2022-05-10 | 上海埃依斯航天科技有限公司 | Near space atmospheric density detection system and device |
| CN115979329A (en) * | 2022-05-19 | 2023-04-18 | 中国科学院国家空间科学中心 | Full-height expansion falling ball in-situ detection device and method for near space |
| CN116149396A (en) * | 2023-04-18 | 2023-05-23 | 东方空间技术(山东)有限公司 | Temperature control system of arrow-borne flight control combination and preparation method of flexible heating device |
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Cited By (6)
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| CN115979329A (en) * | 2022-05-19 | 2023-04-18 | 中国科学院国家空间科学中心 | Full-height expansion falling ball in-situ detection device and method for near space |
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| CN116149396A (en) * | 2023-04-18 | 2023-05-23 | 东方空间技术(山东)有限公司 | Temperature control system of arrow-borne flight control combination and preparation method of flexible heating device |
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