CN112067651A - Heat flow measuring thermal probe inside resident type outer star body and measuring method - Google Patents
Heat flow measuring thermal probe inside resident type outer star body and measuring method Download PDFInfo
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- CN112067651A CN112067651A CN202010793251.5A CN202010793251A CN112067651A CN 112067651 A CN112067651 A CN 112067651A CN 202010793251 A CN202010793251 A CN 202010793251A CN 112067651 A CN112067651 A CN 112067651A
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- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
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- G01K1/026—Means for indicating or recording specially adapted for thermometers arrangements for monitoring a plurality of temperatures, e.g. by multiplexing
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- G01K1/14—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations
- G01K1/146—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations arrangements for moving thermometers to or from a measuring position
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- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/16—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements
- G01K7/18—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements the element being a linear resistance, e.g. platinum resistance thermometer
- G01K7/20—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements the element being a linear resistance, e.g. platinum resistance thermometer in a specially-adapted circuit, e.g. bridge circuit
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Abstract
The invention relates to a heat flow measuring thermal probe inside a resident type outer star body and a measuring method, wherein the thermal probe comprises a connecting part, a sensor supporting part and a temperature measuring part, the connecting part is used for being connected with a drilling component, the connecting part is of a hollow structure, the sensor supporting part is positioned in the hollow structure, and the temperature measuring part is arranged on the sensor supporting part; the sensor supporting part can drive the temperature measuring part to penetrate out of or retract into the hollow structure along the direction perpendicular to the drilling component drill rod, so that the temperature measuring part is horizontally pricked into the outer star body and retracted into the connecting part. The thermal probe adopts a sensor supporting structure, so that the temperature measuring part can penetrate out of or retract into the connecting part, the temperature measuring part penetrating out of the connecting part can be directly inserted into the outer star body to measure the temperature, the contact between the temperature measuring part and the outer star body is increased, the influence of the contact thermal resistance is reduced, the obvious contact thermal resistance and the influence of the axial heat conduction inside the drill pipe on the temperature/temperature difference measuring precision are avoided, and more accurate longitudinal section temperature distribution inside the outer star body can be obtained.
Description
Technical Field
The invention relates to a resident type heat probe and a resident type heat measuring method for heat flow inside a planet body, in particular to a resident type heat probe and a resident type heat measuring method for heat flow inside the planet body based on a steady-state Fourier heat conduction law and a transient hot-wire method.
Background
The temperature distribution of the surface and internal layers of the star is affected by both external radiation and internal heat generation. The external radiation includes electromagnetic radiation of the sun, etc., and the internal heat generation includes heat generated by dissipated heat stored inside during the formation of the planet and radioactive decay of unstable isotopes. The internal heat flow of the planet is an important parameter for measuring the crustal movement and the activity of volcanic activity of the planet, and has important significance for revealing the origin and evolution of the planet. The overall trend of the star body thermal evolution is to cool continuously, the moon is finally formed by the accumulation of gas and cosmic dust about 45 hundred million years ago, but the thermal evolution process is not finished so far. Numerical simulation research is an important method for understanding the thermal evolution process of the moon, but the reliability of numerical simulation depends on accurate measurement of thermal parameters of the moon. The microseism method can obtain the geological structure inside the planet, but cannot obtain the thermophysical parameters such as heat flow, heat conductivity coefficient and the like inside the planet. Therefore, it is necessary to perform in situ measurements of heat flow inside the moon.
The moon is the only satellite of the earth and the first station for humans to explore extraterrestrial celestial bodies. Understanding the formation and evolution process of the moon is of great significance in revealing earth-moon system origin and human development. Among them, the measurement of the thermal environment and thermal parameters of the moon plays an important role in understanding the history of the formation and evolution of the moon.
1971-1972, the lunar fever developed by Apollo project in the United statesThe flow experiment realizes the direct measurement of the heat flow in the moon for the first time in human history, and based on the basic principle of the transient hot-line method, the densities of the heat flow in the moon at Apollo15 and Apollo 17 landing sites are 21mW/m respectively2And 16mW/m2The heat flux density inside the moon is substantially 18-24% of the heat flux inside the earth. However, the two measurements are both at the interface between the lunar surface plateau and the lunar sea, and the measurement results do not indicate the average heat flow level of the whole interior of the moon.
Besides the United states, the former Soviet Union has conducted many lunar exploration, but no related studies on the measurement of heat flow inside the moon have been published. Japan developed the Lunar-A Lunar exploration program (2004), but finally the launch program was cancelled (2007). The Lunar-a project designed a conical thermal probe, and planned to perform thermal conductivity and heat flow measurements on the Lunar surface. At present, besides the moon, other thermal parameter measurement researches of extraterrestrial celestial bodies are also carried out in related countries. Such as the american ' phoenix ' and ' insight ' mars probes, are both intended to measure thermal parameters of the mars's earth surface. The 'Phoenix' detector (2008) adopts the basic measurement principle of a transient hot-wire method, and measurement of the heat conductivity coefficient of soil on the surface of the Mars is carried out. The 'insights' Mars detector (2018) also adopts the basic measurement principle of the transient hot-wire method to measure the heat conductivity coefficient distribution of Mars deep soil. Meanwhile, the heat flux density inside the spark is obtained by utilizing the temperature distribution of the longitudinal section of the spark. The European Union Rosetta/Philae comet detector (2004) measures the thermal parameters of 67P comets to obtain the temperature distribution and the thermal conductivity of the shallow surface layer of the comets.
It can be seen that the current human measurement of heat flow inside the moon is very limited, and the obtained data is obviously insufficient in representativeness. Many researchers now study the problem of heat flow in the moon, and only the original data obtained by Apollo planning before 50 years can be used for analysis by adopting a new data processing means. Reanalysis of the raw data obtained from the Apollo program also continually exposes the shortcomings of the Apollo program heat flow experimental method. At present, the research of related measurement technologies in China is blank. Therefore, more reasonable methods and devices for measuring heat flow inside the moon are needed to be designed based on the current technology, and more moon heat flow detection researches are carried out through the national moon detection plan.
In 1971-. In the field measurement, the astronaut drills a hole on the lunar surface in advance, and the hole depth is 1.6-2.3 m. And after drilling is finished, the hollow drill rod is left in the drill hole so as to reinforce the hole wall. A thermal probe is then placed in the borehole and temperature measurements are started after the effect of the heat generated by the borehole has disappeared.
Apollo plans the thermal probe to be constructed from two and a half-meter long rigid cylinders connected by a flexible material. Temperature sensors are arranged at four different locations on each cylinder, and the temperature difference between two relative locations and the absolute temperature of each location can be measured. In addition, in order to obtain the thermal conductivity of lunar soil, two heaters are arranged on each section of the cylinder, and the thermal conductivity of lunar soil is obtained by measuring the change of the position temperature of the heaters along with time by adopting a transient hot wire method.
Apollo thermal probes suffer from the following disadvantages:
the first disadvantage is that: temperature/temperature difference measurements are inaccurate. After the heat probe enters the surface of the moon and is drilled, the temperature sensor on the surface of the heat probe measures the temperature of the lunar soil outside the drill rod through the hollow drill rod. Gaps exist between the temperature sensor and the inner wall of the drill rod and between the outer wall of the drill rod and the lunar soil, so that obvious thermal contact resistance exists between the temperature sensor and the section lunar soil in the temperature measuring process, and the measured temperature/temperature difference deviates from the true value. In addition, because the heat conductivity coefficient of the lunar soil is extremely low, and the heat conductivity coefficient of the drill rod is relatively high, the measured lunar soil profile temperature difference is smaller than the true value due to the axial heat conduction in the drill rod in the temperature measuring process.
The second disadvantage is that: the temperature information used for inversion in the lunar soil thermal conductivity measurement is limited (only one temperature value). The lunar soil thermal conductivity measurement adopts an approximate transient hot line method, but only one heating plate is used as a temperature measuring point for inverting the lunar soil thermal conductivity, which causes the reliability and accuracy of inversion to be reduced.
In 11 late months in 2018, the American 'insights' Mars probe starts to measure and research the interior of Mars when the Mars safely lands. HP3 mole (Heat Flow and Physical Properties Probe) equipment carried on the insights can measure the heat conductivity coefficient and the temperature gradient of soil inside the mars, and further the heat Flow inside the mars is obtained through the Fourier heat conduction law. The HP3 mole can realize that the underground drilling depth is 5m, a soil thermal conductivity measurement module is integrated at the tail part (Payload component) of the equipment, a physical model is established through a corrected transient hot line method, and the thermal conductivity of Mars soil is obtained through inversion. PT 100 temperature sensors are equidistantly arranged on the temperature gradient measuring belt, so that the temperature distribution inside the spark is obtained. In addition, in order to obtain the heat flow boundary conditions of the Mars surface, radiometers are arranged near the "insight" lander.
The HP3 heat probe suffers from the following disadvantages:
the first disadvantage is that: the temperature information used for inversion in the lunar soil thermal conductivity measurement is limited (only one temperature value). Like the Apollo thermal probe, the HP3 thermal probe can only measure the temperature change at the heating plate when measuring the thermal conductivity of the soil, and then the thermal conductivity of the soil is obtained by inversion by adopting an approximate transient hot-line method. The method for inverting by only using the temperature change at the heating plate has the defects of low reliability and low precision.
The second disadvantage is that: the design of the heat flow experiment drilling equipment has defects. The HP3 heat probe is an unmanned heat flow detection device, the Mars profile temperature distribution and the heat conductivity coefficient measurement depend on a front HP3 mole drill bit to continuously drill into the ground, but the drill bit is difficult to drill into the ground. The HP3 mole drill bit can only be driven into the ground after more than one year after Mars is logged in from the 'insights', and the information disclosed by the American aerospace office shows that the drill bit is not driven downwards according to the expected vertical direction, which has certain influence on the measurement result of the heat flow inside the Mars.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art and provides a resident external star body internal heat flow measuring thermal probe and a measuring method.
The technical scheme for solving the technical problems is as follows: a resident type heat probe for measuring heat flow inside an outer star body comprises a connecting part, a sensor supporting part and a temperature measuring part, wherein the connecting part is used for being connected with a drilling component, the connecting part is of a hollow structure, the sensor supporting part is positioned in the hollow structure, and the temperature measuring part is installed on the sensor supporting part; the sensor supporting part can drive the temperature measuring part to penetrate out of or retract into the hollow structure along the direction perpendicular to the drilling component drill rod, so that the temperature measuring part is horizontally pricked into the outer star body and is retracted into the connecting part.
The invention has the beneficial effects that: the thermal probe adopts a sensor supporting structure, so that the temperature measuring part can penetrate out of or retract into the connecting part, the temperature measuring part penetrating out of the connecting part can be directly inserted into the outer star body to measure the temperature, the contact between the temperature measuring part and the outer star body is increased, the influence of the contact thermal resistance is reduced, the obvious contact thermal resistance and the influence of the axial heat conduction inside the drill pipe on the temperature/temperature difference measuring precision are avoided, and more accurate longitudinal section temperature distribution inside the outer star body can be obtained.
On the basis of the technical scheme, the invention can be further improved as follows.
Further, the temperature measurement portion includes from last first temperature sensor, second temperature sensor and the third temperature sensor who arranges extremely down in proper order, be equipped with the heating unit on the third temperature sensor.
The beneficial effect of adopting the further scheme is that: the three temperature sensors which are sequentially arranged from top to bottom are adopted, the heating unit is arranged on the third temperature sensor, the outer star body soil body at the third temperature sensor can be heated at constant power, the second temperature sensor and the third temperature sensor measure a heating temperature field together, and therefore the heat conductivity coefficient of the lunar soil is measured by utilizing the basic principle of a transient hot wire method.
Further, the temperature measuring part comprises a needle-shaped supporting structure and a temperature sensor, the needle-shaped supporting structure is fixed on the sensor supporting part, and the temperature sensor is fixed at the tip of the needle-shaped supporting structure.
The beneficial effect of adopting the further scheme is that: the needle-shaped supporting structure is convenient to be pricked into the external star soil body.
Furthermore, the sensor supporting part comprises a supporting rod, two groups of symmetrically arranged link mechanisms and a driving part for providing power for the movement of the link mechanisms, the supporting rod is arranged along the direction parallel to the drilling component drill rod, one end of each group of link mechanisms is hinged to the same position of the supporting rod, and the other end of each group of link mechanisms is movably connected to the supporting rod; one group of the connecting rod mechanisms is fixed on the side wall of the connecting part, and the temperature measuring part is arranged on the other group of the connecting rod mechanisms.
The beneficial effect of adopting the further scheme is that: the connecting rod mechanism is matched with the supporting rod, the driving of the temperature measuring part is realized, and the pushing out to radial star soil and the temperature measurement can be realized in the limited diameter of the drill pipe.
Further, the link mechanism is a three-link mechanism, wherein the middle link of one group of three-link mechanism is fixed on the side wall of the connecting part, and the temperature measuring part is arranged on the middle link of the other group of three-link mechanism.
The beneficial effect of adopting the further scheme is that: and a three-link mechanism is adopted, so that the connection driving of the temperature measuring part is conveniently realized.
Further, the bracing piece is the screw rod, the drive division is connected and is driven the bracing piece, threaded connection has the screw thread sliding sleeve on the screw rod, and the other end of two sets of link mechanism articulates on the screw thread sliding sleeve.
The temperature measuring device comprises a temperature measuring part, and is characterized by further comprising an excitation power supply module, a signal acquisition module and a data transmission module, wherein the excitation power supply module is connected with the temperature measuring part and provides an excitation power supply and heating power for the temperature measuring part, the signal acquisition module is connected with the temperature measuring part and converts signals measured by the temperature measuring part into temperature information after filtering and amplifying, and the data transmission module is used for transmitting the temperature information to a data receiving and transmitting station on the surface of the outer star.
Further, the connection portion includes a drill pipe, and the sensor support portion is mounted in the drill pipe.
Furthermore, the outer side wall of the drill pipe is provided with external threads, and the drill pipe is made of a material with a low heat conductivity coefficient.
The beneficial effect of adopting the further scheme is that: the drill pipe is convenient to arrange and is connected with the drill rod, and the drill pipe can be made of polyimide fiber/carbon fiber composite materials with low heat conductivity coefficients, so that the weight of the drill pipe is reduced, and the heat conductivity coefficients of the drill pipe are reduced. The drill pipe structure with low heat conductivity coefficient can effectively inhibit the influence of axial heat conduction in the drill pipe on the temperature distribution of the star body, and obviously weaken the 'heat pipe effect' of the drill pipe.
A method for measuring heat flow inside a resident extraterrestrial body comprises the following steps:
s1, after the thermal probe penetrates into the drill hole, the temperature measuring part penetrates out of the hollow structure of the thermal probe connecting part through the sensor supporting part, and the temperature measuring part is horizontally inserted into the outer star body;
s2, enabling the first temperature sensor positioned at the top in the temperature measuring part to measure the temperature and temperature difference distribution in the outer star body;
s3, enabling the heating unit on the third temperature sensor positioned at the lowest part in the temperature measuring part to heat the interior of the planet body at a constant power, and enabling the third temperature sensor and the second temperature sensor positioned at the middle part in the temperature measuring part to simultaneously measure the temperature of the heating temperature field; the heat conductivity coefficient of the soil of the outer star body is calculated by adopting the basic principle of a transient hot wire method and a heat conduction inverse problem method, and the heat flow parameters of different soil layers of the outer star body are calculated by utilizing the Fourier heat conduction law.
The invention has the beneficial effects that: the temperature of the longitudinal section inside the outer star body is directly inserted into the outer star body through the first temperature sensor with the needle-shaped structure, so that the influence of obvious contact thermal resistance and axial heat conduction inside the drill pipe on the temperature/temperature difference measurement precision is avoided, and more accurate temperature distribution of the longitudinal section inside the outer star body can be obtained; in the process of measuring the external star heat conductivity coefficient, the temperature change of the heating unit (the third sensor) is measured, and the temperature change of the position (the second sensor) away from the heating unit is measured, so that the reliability of the inversion calculation of the external star heat conductivity coefficient is higher, and the measurement precision is higher.
Drawings
FIG. 1 is a first schematic view of a thermal probe according to the present invention in a use state;
FIG. 2 is a schematic diagram of a second usage state of the thermal probe according to the present invention.
In the drawings, the components represented by the respective reference numerals are listed below:
100. a thermal probe; 101. a support bar; 102. a threaded sliding sleeve; 103. a link mechanism; 104. a drive section; 105. the device comprises a signal acquisition module and an excitation power supply module; 106. a data transmission module; 107. a first temperature sensor; 108. a second temperature sensor; 109. a third temperature sensor; 110. a heating unit; 111. a power supply cable; 112. drilling a pipe; 113. a middle connecting rod; 114. a needle-like support structure; 115. a platinum resistor;
200. and (6) drilling.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth to illustrate, but are not to be construed to limit the scope of the invention.
Example 1
As shown in fig. 1 and fig. 2, the resident external satellite internal heat flow measurement heat probe of the present embodiment includes a connection portion for connecting with a drilling component, a sensor support portion and a temperature measurement portion, wherein the connection portion is a hollow structure, the sensor support portion is located in the hollow structure, and the temperature measurement portion is mounted on the sensor support portion; the sensor supporting part can drive the temperature measuring part to penetrate out of or retract into the hollow structure along the direction perpendicular to the drilling component drill rod, so that the temperature measuring part is horizontally pricked into the outer star body and is retracted into the connecting part.
The thermal probe of this embodiment adopts sensor bearing structure, can make temperature measurement portion wear out or retract in the connecting portion, and the temperature measurement portion of wearing out the connecting portion can directly prick the internal portion of extra large star and carry out the temperature measurement, increases the contact between temperature measurement portion and the extra large star, reduces the influence of thermal contact resistance, has avoided obvious thermal contact resistance and the inside axial heat conduction of drill pipe to the influence of temperature/difference in temperature measurement accuracy, can obtain more accurate extra large star internal portion longitudinal section temperature distribution.
A specific scheme of this embodiment is that, as shown in fig. 1 and fig. 2, the temperature measuring portion includes a first temperature sensor 107, a second temperature sensor 108, and a third temperature sensor 109 that are sequentially arranged from top to bottom, a heating unit 110 is disposed on the third temperature sensor 109, and the third temperature sensor 109 is connected through a power supply cable 111 and a data transmission module 106, specifically, as shown in an enlarged schematic diagram of a portion a in fig. 2. The three temperature sensors which are sequentially arranged from top to bottom are adopted, the heating unit is arranged on the third temperature sensor, the outer star body soil body at the third temperature sensor can be heated at constant power, the second temperature sensor and the third temperature sensor measure a heating temperature field together, and therefore the heat conductivity coefficient of the lunar soil is measured by utilizing the basic principle of a transient hot wire method.
Specifically, as shown in fig. 1 and 2, the temperature measuring portion includes a needle-shaped support structure 114 and a temperature sensor, the needle-shaped support structure 114 is fixed on the sensor support portion, and the temperature sensor is fixed at the tip of the needle-shaped support structure 114. The temperature sensor may be a platinum resistor 115. The temperature sensor with the needle-shaped structure is conveniently inserted into the external star soil body. The heating unit 110 is a heating plate fixed at the tip of the needle-shaped supporting structure; the heating sheet can be annular heating sheet (copper sheet) and is sleeved on the tip of the needle-shaped supporting structure.
As shown in fig. 1 and 2, the sensor support portion of the present embodiment includes a support rod 101, two sets of symmetrically arranged link mechanisms 103, and a driving portion 104 for providing power for the movement of the link mechanisms 103, wherein the support rod 101 is arranged in a direction parallel to a drill rod of a drilling component, one end of each of the two sets of link mechanisms 103 is hinged at the same position of the support rod 101, and the other end of each of the two sets of link mechanisms 103 is movably connected to the support rod 101; one group of link mechanisms 103 is fixed on the side wall of the connecting part, and the temperature measuring part is arranged on the other group of link mechanisms 103. The driving part can select a driving motor. The screw rod drives the connecting rod mechanism, and the pushing out to radial star soil and the temperature measurement can be realized in the limited diameter of the drill pipe.
As shown in fig. 1 and 2, the link mechanism 103 of the present embodiment is a three-link mechanism, wherein the middle link 113 of one set of three-link mechanism is fixed on the side wall of the connecting portion, and the temperature measuring portion is mounted on the middle link 113 of the other set of three-link mechanism. The supporting rod 101 is a screw rod, the driving portion 104 is connected with and drives the supporting rod 101, a threaded sliding sleeve 102 is connected to the screw rod in a threaded mode, and the other ends of the two groups of link mechanisms 103 are hinged to the threaded sliding sleeve 102. And a three-link mechanism is adopted, so that the connection driving of the temperature measuring part is conveniently realized. Specifically, the intermediate connecting rod 113 can be made of a supporting plate structure, so that the connection and installation are convenient. The length of the connecting rod hinged at the two ends of the middle connecting rod 113 is the same, so that the folding support is convenient.
In the embodiment, the driving motor is used for driving the screw rod to rotate, a bearing can be arranged at the joint of the screw rod and the driving motor, and the two groups of three-link mechanisms are respectively hinged with the bearing. The screw rod rotates to enable the threaded sliding sleeve to move along the screw rod, the three-connecting-rod mechanism is driven to fold or unfold, and then the temperature measuring part on the middle connecting rod is driven to move.
As shown in fig. 1 and fig. 2, the thermal probe 100 of this embodiment further includes a data transmission module 106, a signal acquisition module, and an excitation power module 105, where the excitation power module 105 is connected to the temperature measurement portion and provides an excitation power and a heating power for the temperature measurement portion, the signal acquisition module is connected to the temperature measurement portion and converts a signal measured by the temperature measurement portion into temperature information after filtering and amplifying, and the data transmission module 106 is configured to transmit the temperature information to a data transceiver station on the surface of an outer satellite.
As shown in fig. 1 and 2, the connection part includes a drill pipe 112, and the sensor support part is installed in the drill pipe 112. The outer side wall of the drill pipe 112 is provided with external threads, and the drill pipe 112 is made of a material with a low heat conductivity coefficient. In use, drill pipe 112 is positioned within borehole 200. The drill pipe 112 is provided with a through hole for the three sensors to extend out or retract. The drill pipe is convenient to arrange and is connected with the drill rod, and the drill pipe can be made of polyimide fiber/carbon fiber composite materials with low heat conductivity coefficients, so that the weight of the drill pipe is reduced, and the heat conductivity coefficients of the drill pipe are reduced. The drill pipe structure with low heat conductivity coefficient can effectively inhibit the influence of axial heat conduction in the drill pipe on the temperature distribution of the star body, and obviously weaken the 'heat pipe effect' of the drill pipe.
Example 2
The method for measuring the internal heat flow of the resident extraterrestrial body comprises the following steps:
s1, after the thermal probe 100 goes deep into the drill hole 200, the temperature measuring part penetrates out of the hollow structure of the connection part of the thermal probe 100 through the sensor supporting part, and the temperature measuring part is horizontally pricked into the outer star body;
s2, the first temperature sensor 107 positioned at the top in the temperature measuring part measures the temperature and temperature difference distribution in the outer star body;
s3, heating the inner part of the planet body with constant power by the heating unit 110 on the third temperature sensor 109 positioned at the lowest part in the temperature measuring part, and simultaneously measuring the temperature of the heating temperature field by the third temperature sensor 109 and the second temperature sensor 108 positioned at the middle part in the temperature measuring part; the heat conductivity coefficient of the outer star body is calculated by adopting the basic principle of a transient hot wire method and a heat conduction inverse problem method, and the heat flow parameters of different soil layers of the outer star body are calculated by utilizing the Fourier heat conduction law.
According to the measuring method, the temperature of the longitudinal section inside the outer star body is directly inserted into the outer star body for measurement through the first temperature sensor with the needle-shaped structure, so that the influence of obvious thermal contact resistance and axial heat conduction inside the drill pipe on the temperature/temperature difference measuring precision is avoided, and more accurate temperature distribution of the longitudinal section inside the outer star body can be obtained; in the process of measuring the heat conductivity of the external star, the temperature change of the heating unit (the third sensor) is measured, and the temperature change of the position (the second sensor) away from the heating unit is measured, so that the reliability of the inversion calculation of the heat conductivity of the external star is higher, and the measurement precision is higher.
The resident type heat flow measuring probe for the internal heat flow of the external star body (such as the moon) based on the steady-state Fourier heat conduction law and the transient hot wire method is used as a scientific experimental load to finish accurate in-situ measurement of the internal heat flow of the external star body (such as the moon), and has important significance for understanding the formation and evolution processes of the external star body (such as the moon).
The thermal probe and the heat flow measuring method of the present invention will be described with reference to the moon.
The lunar heat flow experiment comprises three key problems of lunar soil temperature gradient, heat conductivity coefficient measurement and probe structure design. Each of which will be described in detail below.
The basic principle of heat flow measurement inside the moon is the fourier heat conduction law:
where Δ T is the temperature difference between two points (i.e., where the second temperature sensor and the third temperature sensor are located) that are spaced apart by L, and λ is the thermal conductivity of lunar soil. The platinum resistor has good stability and high temperature linearity, so the longitudinal temperature difference delta T of the lunar soil is measured by the platinum resistor (the platinum resistor can be adopted by the first temperature sensor, the second temperature sensor and the third temperature sensor). Because the depth of the moon drilling is limited and the value of the temperature difference is very small (Apollo planned measurement results show that the longitudinal temperature gradient of the lunar soil is about 1.7K/m), a bridge is required to be used for direct measurement so as to improve the accuracy of temperature difference measurement. The relation between the output voltage of the platinum resistance bridge and the temperature difference is obtained by calibration. The temperature signal of the platinum resistor is obtained by filtering and amplifying through a high-precision electronic circuit.
The lunar soil thermal conductivity coefficient lambda is measured by adopting the basic principle of a transient hot wire method. One-dimensional transient heat conduction equation without internal heat source in cylindrical coordinate
When a heating wire with infinite length, as small as possible heat capacity and as small as possible diameter is inserted into an infinite sample to be measured, the contact thermal resistance between the heating wire and the sample is not considered, and the temperature change rate of the heating wire is proportional to the natural logarithm of time, namely the temperature change rate of the heating wire is proportional to the natural logarithm of time according to the equation and the corresponding boundary conditions, namely
Wherein Q is a heating power per unit length of the heat ray. The thermal conductivity of the sample is thus obtained by measuring the temperature change of the hot wire versus the logarithm of time. The measurement of the lunar soil thermal conductivity coefficient is more complicated, and the arrangement of the actual heating unit deviates from an ideal model of a hot-line method, so that the inversion and correction of the measurement result need to be carried out by adopting a numerical simulation and heat conduction inverse problem method.
In the drilling process, the disturbance and the damage of the drill rod of the drill bit to lunar soil around the hole wall are difficult to avoid, so that the lunar soil structure and the thermophysical properties around the hole wall of the drill hole are changed. In addition, perfect contact is not achieved between the hollow drill pipe and the lunar soil and between the heat probe and the hollow drill pipe, and obvious thermal contact resistance is required to exist. The thermal probe can reduce the thermal contact resistance between the thermal probe and a well wall, between the well wall and lunar soil and the influence of an affected area of the lunar soil on temperature measurement. The heat flow measuring system is modularized, the number of the used heat flow measuring system can be freely combined according to needs, the assembling distance can be designed to be self-defined by corresponding interfaces and installing position structures, for example, the interfaces can be connected with other parts of a drill pipe in a threaded assembling or buckling assembling mode, the specific installing position is determined by the length of the connected drill pipe and the assembling length, as shown in figure 1, if the gradient in the heat flow/temperature depth direction is calculated, the assembling distance needs to be calibrated in advance. After the thermal probe penetrates into the drill hole, the needle-shaped sensor structure is opened through the sensor supporting part, and the three sensors are horizontally pricked into the lunar soil, so that the affected area of the lunar soil is broken through, meanwhile, the contact between the sensors and the lunar soil is increased, and the influence of thermal contact resistance is reduced. The uppermost first sensor of the three sensors measures the temperature and the temperature difference of the lunar soil; the heating unit on the third sensor can perform constant-power heating on the lunar soil, and the second sensor and the third sensor together measure a heating temperature field, so that the heat conductivity coefficient of the lunar soil is measured by using the basic principle of a transient hot wire method. The surface of the moon is free of air, and the heat conduction process of the lunar soil depends on radiation and contact heat conduction among lunar soil particles. The radiation is obviously influenced by the temperature, and the degree of contact among particles is obviously influenced by the depth of the lunar soil, so that the heat conductivity of the lunar soil is a function of the temperature and the depth, and the heat conductivity of the lunar soil needs to be measured at different depth positions.
The vacuum environment of the moon results in a low thermal conductivity of the lunar soil, and in order to reduce the influence of the axial thermal conductivity of the drill pipe on the measurement of the temperature gradient of the lunar soil and reduce the 'heat pipe effect' of the drill pipe, the thermal conductivity of the drill pipe should be as low as possible. Meanwhile, the thermal environment of the moon is very harsh, the temperature fluctuation range is large, and the material selection of the drill pipe should meet the service environment of the moon. The main structure of the drill pipe in the design of the thermal probe is designed to adopt non-metal materials with low thermal conductivity coefficient, such as polyimide fiber composite materials, PEEK composite materials or glass fiber composite materials. In order to meet the functional requirement of the spiral drilling of the drill rod, the threads on the periphery of the drill pipe are made of titanium alloy materials with higher strength.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. The resident type heat probe for measuring the heat flux inside the outer star body is characterized by comprising a connecting part, a sensor supporting part and a temperature measuring part, wherein the connecting part is used for being connected with a drilling component, the connecting part is of a hollow structure, the sensor supporting part is positioned in the hollow structure, and the temperature measuring part is arranged on the sensor supporting part; the sensor supporting part can drive the temperature measuring part to penetrate out of or retract into the hollow structure along the direction perpendicular to the drilling component drill rod, so that the temperature measuring part is horizontally pricked into the outer star body and is retracted into the connecting part.
2. The resident outer star internal heat flow measurement heat probe of claim 1, wherein the temperature measuring portion comprises a first temperature sensor, a second temperature sensor and a third temperature sensor arranged in sequence from top to bottom, and the third temperature sensor is provided with a heating unit.
3. The resident exo-satellite internal heat flow measurement thermal probe of claim 1 or 2, wherein the thermometry section comprises a needle support structure affixed to the sensor support and a temperature sensor affixed to a tip of the needle support structure.
4. The resident external star internal heat flow measurement thermal probe according to claim 1 or 2, wherein the sensor support part comprises a support rod, two sets of symmetrically arranged link mechanisms and a driving part for providing power for the movement of the link mechanisms, the support rod is arranged along a direction parallel to a drill rod of the drilling component, one end of each set of link mechanisms is hinged at the same position of the support rod, and the other end of each set of link mechanisms is movably connected to the support rod; one group of the connecting rod mechanisms is fixed on the side wall of the connecting part, and the temperature measuring part is arranged on the other group of the connecting rod mechanisms.
5. The resident outer star internal heat flow measurement thermal probe according to claim 4, wherein the linkage mechanism is a three-bar linkage mechanism, wherein the middle bar of one set of three-bar linkage mechanism is fixed on the side wall of the connecting part, and the temperature measuring part is installed on the middle bar of the other set of three-bar linkage mechanism.
6. The resident outer star internal heat flow measurement thermal probe according to claim 4, wherein the support rod is a screw rod, the driving part connects and drives the support rod, a threaded sliding sleeve is connected to the screw rod in a threaded manner, and the other ends of the two sets of link mechanisms are hinged on the threaded sliding sleeve.
7. The resident external-star internal heat flow measurement thermal probe according to any one of claims 1 to 2 and 5 to 6, further comprising an excitation power supply module, a signal acquisition module and a data transmission module, wherein the excitation power supply module is connected with the temperature measurement part and provides excitation power and heating power for the temperature measurement part, the signal acquisition module is connected with the temperature measurement part and converts signals measured by the temperature measurement part into temperature information after filtering and amplifying, and the data transmission module is used for transmitting the temperature information to a data transceiver station on the surface of the external star.
8. The resident external satellite internal heat flow measuring thermal probe of any one of claims 1-2, 5-6, wherein the connection portion comprises a drill pipe, the sensor support mounted within the drill pipe.
9. The resident external star internal heat flow measurement heat probe of claim 8, wherein the external thread is provided on the external sidewall of the drill pipe, and the drill pipe is made of a material with low thermal conductivity.
10. A method for measuring heat flow inside a resident extraterrestrial body is characterized by comprising the following steps:
s1, after the thermal probe penetrates into the drill hole, the temperature measuring part penetrates out of the hollow structure of the thermal probe connecting part through the sensor supporting part, and the temperature measuring part is horizontally inserted into the outer star body;
s2, enabling the first temperature sensor positioned at the top in the temperature measuring part to measure the temperature and temperature difference distribution in the outer star body;
s3, enabling the heating unit on the third temperature sensor positioned at the lowest part in the temperature measuring part to heat the interior of the planet body at a constant power, and enabling the third temperature sensor and the second temperature sensor positioned at the middle part in the temperature measuring part to simultaneously measure the temperature of the heating temperature field; the heat conductivity coefficient of the soil of the outer star body is calculated by adopting the basic principle of a transient hot wire method and a heat conduction inverse problem method, and the heat flow parameters of different soil layers of the outer star body are calculated by utilizing the Fourier heat conduction law.
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