Near space balloon and rocket-mounted in-situ detection device and method

Abstract

The application provides a near space balloon and rocket-mounted in-situ detection device and method, and belongs to the technical field of near space environment detection. The near space ascending module sends the in-situ detection device from the ground to different altitudes in the near space through a multi-stage ascending mode, the near space descending module sends the in-situ detection device from the maximum altitude in the near space to the ground through a parachute, the device control module senses the motion posture of the in-situ detection device and controls the near space ascending module and the near space descending module, the data acquisition module detects the atmosphere in the near space in real time in the whole process of ascending and descending, and obtains near space atmospheric data, and the motion posture information of the in-situ detection device and the near space atmospheric data are transmitted to the ground through the data transmission module. The application solves the technical problem that the existing near space in-situ detection technology cannot have high-altitude coverage, low cost and high-frequency use.

Description

Technical Field

[0001] This invention belongs to the field of near-space environment detection technology, specifically relating to an in-situ detection device and method carried by near-space balloons and rockets. Background Technology

[0002] Near space refers to the airspace 20 to 100 km above the ground. It is a transitional zone between aviation and spaceflight. High-precision detection of the atmospheric environment in this area is of great significance for exploring and mastering the strategic resources of near space.

[0003] Currently, there are two main technologies for in-situ near-space exploration: sounding balloons and sounding rockets. Sounding balloons carry probes and ascend slowly using buoyancy, continuously collecting atmospheric parameters during their ascent. This allows for low-cost and continuous data collection. However, sounding balloons are limited by the expansion characteristics of the rising gas and the decrease in atmospheric density with altitude, making it difficult to reach higher altitudes. Their detection limit is generally limited to 30 km, failing to effectively cover the mid-to-high regions of near-space. Sounding rockets use their propulsion system to rapidly deliver probes to the target altitude, then release them via drop or scattering. During descent, they achieve in-situ atmospheric measurements. The maximum detection altitude of a sounding rocket is determined by its performance, reaching up to the top of near-space. However, the high launch cost severely limits its application in routine, high-frequency exploration missions.

[0004] Existing near-space in-situ exploration technologies have significant shortcomings in terms of exploration altitude, operating costs, and operational flexibility. While sounding balloons are economical, their exploration altitude is limited. Although sounding rockets can achieve high-altitude coverage, their launch costs are high, preparation cycles are long, and they are difficult to deploy frequently. Summary of the Invention

[0005] In view of the above-mentioned shortcomings in the prior art, the present invention provides an in-situ detection device and method carried by near-space balloons and rockets, which solves the technical problems that existing near-space in-situ detection technologies cannot simultaneously achieve high-altitude coverage, low cost and high frequency of use.

[0006] To achieve the above objectives, the technical solution adopted by the present invention is as follows: An in-situ detection device carried by a near-space balloon and rocket includes: The near-space ascent module is used to send the in-situ detection device from the ground to the first near-space height, the second near-space height and the third near-space height respectively through a multi-stage ascent method, so as to obtain the first detection stage, the second detection stage and the third detection stage. The near-space descent module is used to send the in-situ detection device from the third near-space height to the ground, thus obtaining the fourth detection stage; The device control module is used to control the operation of the near-space ascent module and the near-space descent module, and to obtain device control information. The data acquisition module is used to detect the atmosphere of near space in the first, second, third and fourth detection phases and obtain near space atmospheric data. The data transmission module is used to process the device's control information and near-space atmospheric data to obtain integrated information, which is then transmitted to the ground.

[0007] To address the technical problems of insufficient detection altitude of sounding balloons and high launch costs and difficulties in high-frequency deployment of sounding rockets in existing near-space in-situ detection technologies, this invention proposes a near-space ascent module, including a sounding balloon and a rocket booster. First, the sounding balloon propels the in-situ detection device from the ground to a first near-space altitude. Then, the rocket booster propels the device from the first near-space altitude to second and third near-space altitudes, achieving full coverage of the low, medium, and high near-space regions. Finally, through the near-space descent module, the in-situ detection device descends from the third near-space altitude back to the ground, forming a total of four detection stages. The device is controlled by a module... The system operates and controls the near-space ascent and descent modules, generating control information. Through the data acquisition module, it obtains atmospheric data of the external near-space environment. The data transmission module transmits the atmospheric data and control information to the ground, providing real-time near-space atmospheric data and the status of the in-situ detection device. This achieves the acquisition of near-space data from the ground to maximum altitude and from maximum altitude to the ground with a single deployment, while reducing rocket launch costs and preparation time. It combines the low cost of a sounding balloon with the high coverage of a sounding rocket, reducing the overall investment in high-altitude detection missions and achieving cost-effective vertical atmospheric sounding.

[0008] Furthermore: the near-space ascent module includes a weather balloon submodule and a rocket booster submodule; The weather balloon submodule is used to send the in-situ detection device from the ground to a first near-space altitude, and separate from the in-situ detection device at the first near-space altitude to obtain the first detection stage; The rocket booster submodule is used to send the in-situ detection device from the first near space altitude to the second near space altitude, and separate from the in-situ detection device at the second near space altitude to obtain the second detection stage; After the rocket booster module separates from the in-situ detection device, the in-situ detection device rises to the third near-space altitude by inertia, thus entering the third detection stage.

[0009] To address the challenges of sounding balloons reaching the upper and middle reaches of near space and the high cost of sounding rocket launches, this invention designs the near-space ascent module as a combination of sounding balloon ascent and rocket booster propulsion. The sounding balloon first initiates the ascent, reaching its maximum altitude, before the rocket booster module takes over, lifting the in-situ detection device to an even higher altitude. After the rocket booster module's propellant is depleted, the in-situ detection device continues to glide upwards by inertia, reaching its maximum altitude. This three-stage ascent design enables the in-situ detection device to be lifted from the ground to the upper and middle reaches of near space, achieving full near-space coverage. Furthermore, the combination of sounding balloon and rocket booster reduces the energy costs of sounding rocket launches from the ground, while simultaneously reaching near-space regions inaccessible to sounding balloons. This invention ensures full near-space coverage while achieving low-cost in-situ detection device ascent, enabling high-frequency daily operation.

[0010] Furthermore: the near-space descent module includes a shell release submodule and a parachute module; The shell detachment submodule is used to discard the top shell of the in-situ detection device at a third adjacent space height. The parachute submodule is used to deploy the parachute after the top shell detaches, sending the in-situ detection device from the third near-space altitude to the ground, thus obtaining the fourth detection stage.

[0011] This invention deploys the parachute at a third near-space altitude, enabling the in-situ detection device to be slowly and stably returned to the ground. Simultaneously, it obtains in-situ detection data from the third near-space altitude to the ground, achieving the recovery of the in-situ detection device and allowing it to be reused. This reduces the operating cost and preparation cycle of near-space in-situ detection missions.

[0012] Furthermore: the device control module includes an attitude sensing submodule, an ascent control submodule, and a descent control submodule; The attitude perception submodule includes a GNSS unit and an INS unit, which are used to acquire the position data, velocity data and attitude information of the in-situ detection device and process them to obtain motion state data. The ascent control submodule is used to send commands to control the adjacent space ascent module at the first critical space height and the second critical space height. The descent control submodule is used to send commands at the third critical space height to control the adjacent space descent module. To ensure the successful ascent of the detection device, the ascent control submodule controls the near-space ascent module at the first and second critical space altitudes, guaranteeing the continuity and accuracy of power conversion during ascent. The descent control submodule sends commands at the third critical space altitude to control the near-space descent module to deploy its parachute, ensuring the safety of the in-situ detection device during its return phase. This invention uses an attitude sensing submodule to capture the real-time attitude of the in-situ detection device, ensuring the normal operation of both the ascent and descent control submodules. This allows the in-situ detection device to effectively collect atmospheric environmental data throughout the entire detection phase and can be safely recovered and reused.

[0013] Furthermore: the rise control submodule includes an ignition control unit, a pyrotechnic triggering unit, and a pyrotechnic device; The ignition control unit is used to control the rocket booster submodule of the critical space ascent module at the first critical space altitude. The pyrotechnic triggering unit is used to drive the pyrotechnic to move at the second critical height, thereby completing the separation of the rocket booster submodule of the critical space ascent module from the in-situ detection device.

[0014] The ignition control unit of this invention controls the rocket booster module to ignite at the first near-space altitude, ensuring a smooth transition of the in-situ detection device from buoyancy ascent to rocket propulsion. This reduces altitude loss due to ignition delay and energy waste due to premature ignition. The pyrotechnic triggering unit drives the pyrotechnic device to move at the second near-space altitude, quickly severing the mechanical connection between the rocket booster module and the in-situ detection device, reducing attitude disturbances caused by incomplete or untimely separation. This invention ensures the continuity from the weather balloon ascent to the rocket booster ascent, and from the rocket booster ascent to the inertial glide ascent, enabling the in-situ detection device to smoothly reach its maximum altitude and achieve full near-space coverage.

[0015] Furthermore: the data acquisition module includes an atmospheric temperature sensing submodule, an atmospheric pressure sensing submodule, an atmospheric density sensing submodule, and a data correction submodule; The atmospheric temperature sensing submodule is used to detect the atmosphere in the near space during the first detection phase, the second detection phase, the third detection phase, and the fourth detection phase, and obtain atmospheric temperature data. The atmospheric pressure sensing submodule is used to detect the atmosphere in near space during the first detection phase, the second detection phase, the third detection phase, and the fourth detection phase, and obtain atmospheric pressure data. The atmospheric density sensing submodule is used to detect the atmosphere in the near space during the first detection phase, the second detection phase, the third detection phase, and the fourth detection phase, and obtain atmospheric density data. The data correction submodule is used to correct atmospheric temperature data, atmospheric pressure data, and atmospheric density data to obtain near-space atmospheric data.

[0016] To address the issues of incomplete and unreliable atmospheric data in near-space exploration caused by environmental interference and single detection phases, this invention employs an atmospheric temperature sensing submodule, an atmospheric pressure sensing submodule, an atmospheric density sensing submodule, and a data correction submodule to conduct continuous and synchronous monitoring throughout the four detection phases of ascent and descent. This acquires multi-dimensional near-space data, obtaining complete atmospheric data from the ground to high altitudes and from high altitudes to the ground. The data correction submodule then performs data compensation and correction, reducing environmental noise and equipment interference, and improving the authenticity and consistency of atmospheric environmental data.

[0017] This invention also provides an in-situ detection method carried by near-space balloons and rockets, comprising the following steps: Using a weather balloon to carry an atmospheric sounder, the atmospheric sounder is launched from the ground and raised to the first near-space altitude to obtain atmospheric data for the first detection phase. The booster is ignited at the first near-space altitude to raise the atmospheric sounder from the first near-space altitude to the second near-space altitude, and the near-space atmospheric data of the second detection phase is obtained. The control booster separates from the atmospheric sounder at the second near-space altitude. The atmospheric sounder continues to ascend by inertia, from the second near-space altitude to the third near-space altitude, and obtains near-space atmospheric data in the third detection phase. The parachute is deployed at the third near-space altitude to lower the atmospheric sounder to the ground, where it will detect atmospheric data for the fourth phase of the detection, thus completing an in-situ near-space atmospheric environment detection mission.

[0018] Furthermore: the third near-space altitude is the maximum altitude reached by the atmospheric sounder.

[0019] To address the long-standing lack of effective detection coverage in the upper and middle levels of near space due to the low upper limit of sounding balloon altitude and the high cost of sounding rocket launches, this invention first uses an inexpensive sounding balloon to send the payload to a first near space altitude and acquire lower-level data. Then, a rocket booster is activated to ascend to a second near space altitude, and the payload continues to rise to a third near space altitude using inertia. Throughout the ascent, continuous sensing and sampling are performed. Finally, a parachute is deployed at the third critical space altitude. This invention disperses the energy requirements for ascent, avoids the extreme ascent altitude of the sounding balloon, saves the high cost of launching sounding rockets from the ground, significantly reduces mission costs and time, and achieves low-cost and high-frequency near-space atmospheric environment monitoring. Attached Figure Description

[0020] Figure 1 A schematic diagram of a module for an in-situ detection device carried by a near-space balloon and a rocket; Figure 2 A schematic diagram of the structure of an in-situ detection device carried by a near-space balloon and rocket; Figure 3 This is a flowchart illustrating an in-situ detection method using near-space balloons and rockets. Detailed Implementation

[0021] The specific embodiments of the present invention are described below to enable those skilled in the art to understand the present invention. However, it should be understood that the present invention is not limited to the scope of the specific embodiments. For those skilled in the art, various changes are obvious as long as they are within the spirit and scope of the present invention as defined and determined by the appended claims. All inventions utilizing the concept of the present invention are protected.

[0022] Example 1 like Figure 1 As shown, the present invention provides an in-situ detection device carried by a near-space balloon and a rocket, comprising: The near-space ascent module is used to send the in-situ detection device from the ground to the first near-space height, the second near-space height and the third near-space height respectively through a multi-stage ascent method, so as to obtain the first detection stage, the second detection stage and the third detection stage. The near-space descent module is used to send the in-situ detection device from the third near-space height to the ground, thus obtaining the fourth detection stage; The device control module is used to sense the motion attitude of the in-situ detection device, control the operation of the near space rising module and the near space descending module, and obtain device control information. The data acquisition module is used to detect the atmosphere of near space in the first, second, third and fourth detection phases and obtain near space atmospheric data. The data transmission module is used to process the device's control information and near-space atmospheric data to obtain integrated information, which is then transmitted to the ground.

[0023] In this invention, the near-space ascent module includes a weather balloon sub-module and a rocket booster sub-module; The weather balloon submodule is used to send the in-situ detection device from the ground to a first near-space altitude, where it separates from the in-situ detection device to obtain the first detection stage. The weather balloon submodule is used in the same way as conventional weather balloons, and can raise the in-situ detection device from the ground to the first near-space altitude, which can be referred to as the balloon buoyancy detection stage, i.e., the first detection stage. The first critical space altitude is the limit altitude that the weather balloon can reach. Based on this, the present invention combines rocket booster for relay ascent, which can reduce the energy cost consumed by rocket launch from the ground, reduce the preparation cycle of in-situ detection missions, and reach near-space altitudes that conventional weather balloons cannot reach, achieving high coverage and low cost of near-space atmospheric detection. The rocket booster submodule is used to send the in-situ detection device from a first near-space altitude to a second near-space altitude, where it separates from the in-situ detection device to obtain the second detection stage. This invention adds a rocket booster method to the basic structure of a weather balloon. After the in-situ detection device reaches the first near-space altitude, the rocket booster submodule is activated until the propellant of the rocket booster submodule is exhausted, raising the in-situ detection device to the second near-space altitude. This can be referred to as the booster climb detection stage, i.e., the second detection stage. After the propellant in the rocket booster module is exhausted, in order to reach the maximum altitude that the in-situ detection device can reach, the rocket booster module and the in-situ detection device need to be separated in time. After the rocket booster module and the in-situ detection device are separated, the in-situ detection device continues to rise to the third near space altitude through inertia, which can be recorded as the inertial ascent stage, i.e. the third detection stage.

[0024] In this invention, the near-space descent module includes a shell release submodule and a parachute module; The housing detachment submodule is used to discard the top housing of the in-situ detection device at a third near-space altitude. The parachute module is used to deploy the parachute after the top shell detaches, sending the in-situ detection device from the third near-space altitude to the ground, thus obtaining the fourth detection stage.

[0025] In a specific embodiment, the top of the in-situ detection device is provided with a shell, which can be connected to the in-situ detection device through a shell separation device, such as a self-releasing bolt or an unlocking separation mechanism. When the third near-space altitude is reached, the separation device is triggered to release the constraint on the shell, and the top shell of the in-situ detection device is discarded. At this time, the parachute submodule deploys the parachute to achieve a stable and slow descent, which can be referred to as the parachute slow descent detection stage, i.e., the fourth detection stage. The near-space descent module enables the in-situ detection device to be reused, reducing the operating cost and preparation cycle of near-space in-situ detection missions.

[0026] In this invention, the device control module includes an attitude sensing submodule, an ascent control submodule, and a descent control submodule; The attitude perception submodule includes a GNSS unit and an INS unit. The GNSS unit acquires the latitude, longitude, altitude, and three-axis velocity information of the in-situ detection device, while the INS unit acquires high-frequency attitude angle, angular rate, and acceleration data. The GNSS and INS units work together to acquire the position, velocity, and attitude information of the in-situ detection device, and process this data to obtain motion state data. In a specific embodiment of the invention, the first, second, and third near-space altitudes can all be determined using the motion state data acquired by the attitude perception submodule.

[0027] The ascent control submodule is used to send commands to control the adjacent space ascent module at the first critical space height and the second critical space height. The rise control submodule includes an ignition control unit, a pyrotechnic triggering unit, and a pyrotechnic device. The ignition control unit is used to control the operation of the rocket booster submodule of the critical space ascent module at the first critical space altitude. At this point, the first near space altitude is reached, and the sounding balloon will stop ascending. The connection between the sounding balloon and the in-situ detection device is disconnected. The sounding balloon cable can be separated from the in-situ detection device through components such as explosive bolts and separation nuts. At the same time, the ignition control unit sends an ignition command to the rocket booster submodule, and the rocket booster submodule starts working, pushing the in-situ detection device to continue climbing. When the rocket booster submodule reaches the second near space altitude, that is, when the propellant of the rocket booster submodule is exhausted, the pyrotechnic triggering unit starts to activate. The pyrotechnic triggering unit is used to drive the pyrotechnic device to operate at the second critical altitude. The pyrotechnic device works rapidly to quickly sever the mechanical connection between the rocket booster submodule and the in-situ detection device, completing the separation of the rocket booster submodule and the in-situ detection device in the critical space ascent module. This reduces the occurrence of attitude instability caused by incomplete or untimely separation, ensures seamless connection of ascent power, and avoids maximum altitude loss caused by separation delay and structural collision caused by premature separation.

[0028] The descent control submodule is used to send commands to control the adjacent space descent module at the third critical space altitude. When it is determined that the third adjacent space altitude has been reached, that is, when the in-situ detection device has risen to the maximum altitude by inertia and is about to start descent, the descent control submodule sends commands to the shell separation submodule and the parachute submodule to jettison the top shell and open the parachute, ensuring that the in-situ detection device can be successfully deployed at the maximum altitude and realizing the recovery of the detection device.

[0029] This invention, through the refined operation and coordinated operation of the attitude sensing submodule, ascent control submodule, and descent control submodule, achieves the smooth ascent and safe recovery of the in-situ detection device, ensuring the acquisition of high-quality near-space atmospheric data. In this invention, the data acquisition module includes an atmospheric temperature sensing submodule, an atmospheric pressure sensing submodule, an atmospheric density sensing submodule, and a data correction submodule. The atmospheric temperature sensing submodule is used to detect the atmosphere in the near space during the first, second, third, and fourth detection phases and obtain atmospheric temperature data. The atmospheric pressure sensing submodule is used to detect the atmosphere in near space during the first, second, third, and fourth detection phases and obtain atmospheric pressure data. The atmospheric density sensing submodule is used to detect the atmosphere in near space during the first, second, third, and fourth detection phases and obtain atmospheric density data. The data correction submodule is used to correct atmospheric temperature data, atmospheric pressure data, and atmospheric density data to obtain near-space atmospheric data.

[0030] The system acquires near-space atmospheric data from the ground to the maximum altitude and from the maximum altitude to the ground through atmospheric temperature sensing, atmospheric pressure sensing, and atmospheric density sensing submodules. It also collects atmospheric parameters such as temperature, pressure, and density of the external environment in real time to obtain raw measurement data. The data correction module then compensates and corrects the raw measurement data to obtain near-space atmospheric data. In a specific embodiment, the original measurement data is compensated and corrected by the data correction module, specifically including: correcting the atmospheric temperature data and correcting the atmospheric pressure data; Correcting atmospheric temperature data: In the embodiments of the present invention, a thermistor sensor is used to collect atmospheric temperature data. The thermistor sensor always conforms to the first law of thermodynamics. In this thermistor system, the expression for the change in the internal energy of the thermistor is as follows:

[0031] in, This refers to the convective heat energy transferred to the thermistor per unit time. For heat exchange through radiation, To conduct and exchange heat energy, For self-heating; by analyzing and expanding the expression for the change in the internal energy of the thermistor, the various compensation terms for temperature can be obtained; these mainly include the aerodynamic heating correction term, the hysteresis effect correction term, the solar radiation correction term, the solar radiation correction term reflected by the ground and clouds, the long-wave radiation correction term, the sensor's thermal radiation correction term to the environment, and the measurement circuit heat loss correction term.

[0032] The pneumatic heating correction term refers to the heat transfer process from a high-temperature gas generated when an object is in high-speed relative motion with air or other gases. Its expression is:

[0033]

[0034] in, This is a correction item for pneumatic heating. The coefficient of restitution can be calculated using the formula for the coefficient of restitution in any flow regime. The speed of the sensor relative to the air. The specific heat capacity of air at constant pressure is a constant value of 1004 (J / kg∙K); For continuous flow, the coefficient of restitution is... The coefficient of restitution for free molecular flow. Mach number, These are aerodynamic parameters. Where is the Reynolds number, in practical applications, under subsonic conditions, the coefficients of restitution for continuous flow and free molecular flow measured for bead-shaped thermistors are respectively, =0.75, =1.55, =2.19.

[0035] The lagged effect correction term refers to the phenomenon where the dependent variable is affected by the values ​​of itself or another explanatory variable in previous periods. Its expression is:

[0036] in, This is a lag effect correction term. This refers to the temperature change per unit time measured by the temperature sensor. The thermistor's heat capacity represents the amount of heat required to raise its temperature by 1 K. The surface area of ​​the thermistor The convective heat exchange coefficient; The convective heat transfer coefficient represents the convective heat exchange capacity between a fluid and a solid surface. Aerodynamic similarity theory provides a general expression for the convective heat transfer coefficient:

[0037] in, The geometric dimensions of the sensor's convective heat transfer surface are... The thermal conductivity of air. The Nusselt number represents the ratio of the thermal resistance to the convective heat transfer resistance of the airflow layer, and is usually determined experimentally.

[0038] The solar radiation correction term refers to the effect of solar radiation absorbed by the sounding component on temperature measurement, and its expression is:

[0039] in, This is a solar radiation correction term. This refers to the effective area of ​​the thermistor exposed to solar radiation. The absorption rate of the thermistor to solar radiation. The solar constant is the density of solar radiation flux received per second per unit area at the top boundary of the atmosphere perpendicular to sunlight at the average distance between the Earth and the Sun.

[0040] The ground and cloud-reflected solar radiation correction term refers to the impact of absorption and scattering of solar radiation by the atmosphere, ground, and clouds on the detection components. Its expression is:

[0041] in, This is a correction term for solar radiation reflected from the ground and clouds. The effective area of ​​the thermistor that receives solar radiation reflected from the ground and clouds. The overall reflection coefficient is used to replace various absorption and loss factors, thus facilitating calculations. This value is usually chosen as a fixed value based on the geographical location. This represents the absorption rate of solar radiation by the thermistor.

[0042] The temperature correction term includes long-wave radiation, which primarily originates from the infrared radiation of the environment surrounding the detection module. Infrared radiation can be categorized into three directions: long-wave radiation from the upper atmospheric boundary, radiation received by the detection module itself, and long-wave radiation from the lower atmospheric boundary due to reflection and refraction. Since temperature cannot be directly measured, it is converted into an equivalent blackbody temperature calculation, expressed as:

[0043] in, This is the long-wave radiation correction term for temperature. The long-wavelength absorption rate of the thermistor, It is the Stefan-Boltzmann constant. , and The blackbody temperatures in the three directions can be calculated using the following formula:

[0044]

[0045]

[0046] in, To detect the height of the component, To detect the vertex height reached by the component, The surface temperature at the peak. The calculation expression is related to the structure of the detection component, and an approximate value is often obtained by fitting a curve.

[0047] The sensor's correction term for ambient thermal radiation also utilizes the Stefan-Boltzmann law. This law allows the sensor's response to ambient thermal radiation to be converted into equivalent blackbody radiation, expressed as follows:

[0048] in, For ambient temperature, The thermal emissivity of the thermistor.

[0049] The heat loss correction term for the measurement circuit: The heat generated by the work done by the current in the measurement circuit of the detection component also affects the accuracy of temperature measurement. The formula for correcting the heat loss of the measurement circuit is as follows:

[0050] in, This is the sensor's operating voltage. For sensor resistance; The formula for calculating the resistance of a thermistor is:

[0051] in, For thermistors in Resistance at temperature For thermistors in The nominal resistance at temperature, These are the fixed parameters of the thermistor.

[0052] Correcting atmospheric pressure data: In one embodiment of the present invention, a Pirani sensor is used to detect atmospheric pressure data. The Pirani sensor is then corrected for atmospheric pressure. The temperature range at altitudes of 20-70 km is approximately 190 K to 270 K. Therefore, simulations were performed on 1060 sets of data for temperatures of 190 K, 200 K, 210 K, 220 K, 230 K, 240 K, 250 K, 260 K, and 270 K, and atmospheric pressures of 1 Pa to 20 Pa (1 Pa interval) and 21 Pa to 991 Pa (10 Pa interval). The error values ​​of the Pirani sensor under different temperatures and atmospheric pressures were obtained. Then, using measured atmospheric pressure and ambient temperature as inputs and actual atmospheric pressure as output, polynomial fitting was performed on the data to reduce the error of the Pirani sensor. To improve fitting accuracy, a piecewise fitting method was adopted, dividing the original data into two groups based on a temperature boundary of 220 K. Polynomial surface fitting was performed on each of the two groups of data, and the Pirani atmospheric pressure data received by the detection component was corrected using the fitting formula.

[0053] In this invention, a data transmission module is used to organize device control information and near-space atmospheric data to obtain integrated information, which is then transmitted to the ground. The device control information includes the operational status information of the near-space ascent module, the near-space descent module, and the device control module. The data transmission module can continuously and synchronously monitor the four detection phases, acquire multi-dimensional data of near-space and the status information of the in-situ detection device, and provide the operational status and execution time of each module in the in-situ detection device. This helps the ground to understand whether the in-situ detection device is operating normally and ensures the normal progress of the in-situ detection mission.

[0054] Example 2 Based on the in-situ detection device carried by a near-space balloon and rocket provided in Example 1, such as Figure 2 The diagram shown is a structural schematic of an in-situ detection device carried by a near-space balloon and a rocket according to the present invention. As a general structural illustration of the in-situ detection device of the present invention, it includes, from top to bottom, a weather balloon submodule, a near-space descent module, a descent control submodule, a data acquisition module, an attitude sensing submodule, a data transmission module, an ascent control submodule, and a rocket booster submodule. The near-space descent module includes a shell separation submodule and a parachute module; the data acquisition module includes an atmospheric temperature sensing submodule, an atmospheric pressure sensing submodule, an atmospheric density sensing submodule, and a data correction submodule; the attitude perception submodule includes a GNSS unit and an INS unit; and the ascent control submodule includes an ignition control unit, a pyrotechnic triggering unit, and pyrotechnics.

[0055] The rocket booster submodule is located at the bottom of the in-situ detection device. It can employ a solid rocket propulsion system or a micro-liquid propulsion system and is equipped with a corresponding fixed connection structure. The rocket booster submodule is electrically connected to the ignition control unit. Upon receiving an ignition signal, it generates thrust to release the in-situ detection device from the weather balloon and rapidly propel it upwards, completing an active ascent. The near-space descent module is located at the top of the in-situ detection device and includes a shell separation submodule, a parachute submodule, and corresponding deceleration connecting ropes. The parachute module can use aerospace-grade parachutes to achieve a stable and gentle descent of the in-situ detection device. When the detection instrument reaches its maximum altitude, this system, along with the near-space descent module, receives a parachute deployment command, triggering the shell separation device to jettison the detector's head shell and release the parachute, enabling the detector to descend slowly.

[0056] The present invention discloses an in-situ detection device carried by a near-space balloon and a rocket. After being carried to the first critical space altitude by a weather balloon, it continues to rise with the help of a rocket. After the propellant is exhausted, the in-situ detection device rises to the top by inertia, and the parachute automatically opens to enter the descent phase. During the entire flight, the in-situ detection device realizes continuous in-situ measurement during both ascent and descent.

[0057] Example 3 Based on Examples 1 and 2, the present invention provides an in-situ detection method carried by near-space balloons and rockets, comprising the following steps: Using a weather balloon to carry an atmospheric sounder, the atmospheric sounder is launched from the ground and raised to the first near-space altitude to obtain atmospheric data for the first detection phase. The booster is ignited at the first near-space altitude to raise the atmospheric sounder from the first near-space altitude to the second near-space altitude, and the near-space atmospheric data of the second detection phase is obtained. The control booster separates from the atmospheric sounder at the second near-space altitude. The atmospheric sounder continues to ascend by inertia, from the second near-space altitude to the third near-space altitude, and obtains near-space atmospheric data in the third detection phase. The parachute is deployed at the third near-space altitude to lower the atmospheric sounder to the ground, where it will detect atmospheric data for the fourth phase of the detection, thus completing an in-situ near-space atmospheric environment detection mission.

[0058] Among them, the atmospheric detector is the in-situ detection device in Embodiments 1 and 2, which can detect the atmospheric environment in the near space. The third near space altitude is the maximum altitude reached by the atmospheric detector.

[0059] like Figure 3The diagram illustrates a flow chart of an in-situ detection method using a near-space balloon and rocket. Based on an in-situ detection device used in near-space balloons and rockets according to Embodiment 2, the method completes in-situ detection tasks in four stages: balloon ascent, boost ascent, inertial ascent, and parachute descent. Balloon lift-off and initial exploration: The atmospheric sounder is carried by a weather balloon and floats up to a preset altitude of 20 km, which is the first critical space altitude. During the lift-off, the atmospheric sounder continuously collects and corrects external environmental parameters to obtain atmospheric data during the balloon's lift-off phase and transmits the atmospheric data and its own motion status to the ground in real time. Booster ignition and active climb detection: When the atmospheric sounder reaches a preset altitude of 20 km, the ignition control submodule, based on the elevation angle and altitude-related data from the data acquisition module and attitude perception submodule, triggers the rocket booster ignition through the ignition control unit. After the rocket booster starts, the atmospheric sounder climbs rapidly under the thrust. During the booster climb, the atmospheric sounder continuously collects and corrects external environmental parameters to obtain atmospheric data during the booster climb phase, and transmits the atmospheric data and its own motion status to the ground in real time. Booster Separation and Inertial Ascent Detection: After the rocket booster propellant is exhausted, the rocket booster submodule sends a separation command to the ascent control submodule. The ascent control submodule then activates the pyrotechnic trigger unit, using pyrotechnics to separate the rocket booster submodule from the main body of the atmospheric sounder. Subsequently, the atmospheric sounder continues to ascend by inertia until it reaches a maximum altitude of 60 km, which is the altitude of the third near space. During the inertial ascent, the atmospheric sounder continuously collects and corrects external environmental parameters, obtains atmospheric data during the inertial ascent phase, and transmits the atmospheric data and its own motion status to the ground in real time. Parachute deployment and recovery and descent phase detection: When the atmospheric sounder reaches its maximum altitude of 60 km, the descent control submodule issues a parachute deployment command, triggering the near-space descent module's shell separation submodule and parachute submodule to jettison the top shell and release the parachute. After the parachute has stably deployed, the atmospheric sounder enters the descent phase. During the parachute descent, the atmospheric sounder continuously collects and corrects external environmental parameters to obtain atmospheric data during the parachute descent phase, and transmits the atmospheric data and its own motion status to the ground in real time. Ultimately, the atmospheric sounder landed safely, completing an in-situ near-space atmospheric environment sounding mission covering both ascent and descent profiles.

[0060] The beneficial effects of this invention are as follows: (1) Combining the advantages of high detection altitude and low cost: This invention integrates the detection ideas of sounding balloons and sounding rockets. It uses sounding balloons to smoothly transport the detector to the lower layer of near space, and then starts the booster to push it further up to the middle and upper layers of near space. This invention not only inherits the advantages of sounding balloons in terms of low operating cost and flexible deployment, but also breaks through the bottleneck of limited detection altitude. At the same time, compared with traditional sounding rockets, it avoids high launch costs and complex ground support systems, significantly reduces the overall investment in high-altitude detection missions, and achieves high cost-effective vertical atmospheric detection.

[0061] (2) High detection flexibility and repeatability: The atmospheric detector can be quickly integrated based on the existing weather balloon platform without the need for special launch facilities. It has the characteristics of fast response, easy deployment and high-frequency operation. The in-situ detection device carried by the near-space balloon and rocket of the present invention can adopt an aerodynamic conformal structure design, so that the booster and the detector form a continuous and smooth outline, reducing aerodynamic drag and attitude disturbance during high-speed ascent, improving flight stability and ensuring the working reliability of sensitive instruments in dynamic environments. At the same time, the design of the in-situ detection device carried by the near-space balloon and rocket of the present invention is conducive to the recovery and reuse of the device, and enhances the adaptability of the in-situ detection device in multi-scenario and routine detection missions.

Claims

1. An in-situ detection device carried by a near-space balloon and rocket, characterized in that, include: The near-space ascent module is used to send the in-situ detection device from the ground to the first near-space height, the second near-space height and the third near-space height respectively through a multi-stage ascent method, so as to obtain the first detection stage, the second detection stage and the third detection stage. The near-space descent module is used to send the in-situ detection device from the third near-space height to the ground, thus obtaining the fourth detection stage; The device control module is used to sense the motion attitude of the in-situ detection device, control the operation of the near space rising module and the near space descending module, and obtain device control information. The data acquisition module is used to detect the atmosphere of near space in the first, second, third and fourth detection phases and obtain near space atmospheric data. The data transmission module is used to process the device's control information and near-space atmospheric data to obtain integrated information, which is then transmitted to the ground.

2. The in-situ detection device carried by a near-space balloon and rocket according to claim 1, characterized in that, The near-space ascent module includes a weather balloon submodule and a rocket booster submodule; The weather balloon submodule is used to send the in-situ detection device from the ground to a first near-space altitude, and separate from the in-situ detection device at the first near-space altitude to obtain the first detection stage; The rocket booster submodule is used to send the in-situ detection device from the first near space altitude to the second near space altitude, and separate from the in-situ detection device at the second near space altitude to obtain the second detection stage; After the rocket booster module separates from the in-situ detection device, the in-situ detection device rises to the third near-space altitude by inertia, thus entering the third detection stage.

3. The in-situ detection device carried by a near-space balloon and rocket according to claim 1, characterized in that, The near-space descent module includes a shell separation submodule and a parachute module; The shell detachment submodule is used to discard the top shell of the in-situ detection device at a third adjacent space height. The parachute submodule is used to deploy the parachute after the top shell detaches, sending the in-situ detection device from the third near-space altitude to the ground, thus obtaining the fourth detection stage.

4. The in-situ detection device carried by a near-space balloon and rocket according to claim 1, characterized in that, The device control module includes an attitude sensing submodule, an ascent control submodule, and a descent control submodule; The attitude sensing submodule is used to acquire the motion state data of the in-situ detection device; The ascent control submodule is used to send commands to control the adjacent space ascent module at the first critical space height and the second critical space height. The descent control submodule is used to send commands at the third critical space height to control the adjacent space descent module.

5. The in-situ detection device carried by a near-space balloon and rocket according to claim 4, characterized in that, The attitude awareness submodule includes a GNSS unit and an INS unit; The GNSS unit and INS unit work together to acquire the position data, velocity data and attitude information of the in-situ detection device, and process them to obtain motion state data.

6. The in-situ detection device carried by a near-space balloon and rocket according to claim 4, characterized in that, The rise control submodule includes an ignition control unit, a pyrotechnic triggering unit, and a pyrotechnic device; The ignition control unit is used to control the rocket booster submodule of the critical space ascent module at the first critical space altitude. The pyrotechnic triggering unit is used to drive the pyrotechnic to move at the second critical height, thereby completing the separation of the rocket booster submodule of the critical space ascent module from the in-situ detection device.

7. The in-situ detection device carried by a near-space balloon and rocket according to claim 1, characterized in that, The data acquisition module includes an atmospheric temperature sensing submodule, an atmospheric pressure sensing submodule, an atmospheric density sensing submodule, and a data correction submodule. The atmospheric temperature sensing submodule is used to detect the atmosphere in the near space during the first detection phase, the second detection phase, the third detection phase, and the fourth detection phase, and obtain atmospheric temperature data. The atmospheric pressure sensing submodule is used to detect the atmosphere in near space during the first detection phase, the second detection phase, the third detection phase, and the fourth detection phase, and obtain atmospheric pressure data. The atmospheric density sensing submodule is used to detect the atmosphere in the near space during the first detection phase, the second detection phase, the third detection phase, and the fourth detection phase, and obtain atmospheric density data. The data correction submodule is used to correct atmospheric temperature data, atmospheric pressure data, and atmospheric density data to obtain near-space atmospheric data.

8. A method for in-situ detection carried by near-space balloons and rockets, characterized in that, Includes the following steps: Using a weather balloon to carry an atmospheric sounder, the atmospheric sounder is launched from the ground and raised to the first near-space altitude to obtain atmospheric data for the first detection phase. The booster is ignited at the first near-space altitude to raise the atmospheric sounder from the first near-space altitude to the second near-space altitude, and the near-space atmospheric data of the second detection phase is obtained. The control booster separates from the atmospheric sounder at the second near-space altitude. The atmospheric sounder continues to ascend by inertia, from the second near-space altitude to the third near-space altitude, and obtains near-space atmospheric data in the third detection phase. The parachute is deployed at the third near-space altitude to lower the atmospheric sounder to the ground, where it will detect atmospheric data for the fourth phase of the detection, thus completing an in-situ near-space atmospheric environment detection mission.

9. The in-situ detection method using near-space balloons and rockets according to claim 8, characterized in that, The third near-space altitude is the maximum altitude reached by the atmospheric sounder.

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