Two-body separation type extraterrestrial celestial body dielectric constant detection device and detection method

Abstract

The invention discloses a two-body separation type extraterrestrial celestial body dielectric constant detection device and method, and the device comprises a surface body which is located on the surface of a penetrated medium when penetrating the penetrated medium, and is internally provided with a surface body control module, the surface body control module comprises a first electromagnetic pulse emission source and a first electromagnetic pulse receiving source; and the penetration body is connected with the surface body through a cable and located in the penetrated medium when penetrating the penetrated medium, a penetration body control module is arranged in the penetration body, and the penetration body control module comprises a second electromagnetic pulse emitting source and a second electromagnetic pulse receiving source. According to the invention, in combination with kinetic energy penetration flight capability, dielectric constant in-situ detection of any position of an extraterrestrial celestial body can be realized, such as penetration analysis of orbit-surrounding release.

Description

Technical Field

[0001] The present invention relates to the field of extraterrestrial object detection, and in particular to a two-body separated extraterrestrial object dielectric constant detection device and detection method. Background Art

[0002] For the exploration of extraterrestrial bodies, the physical characteristic parameters of deep stellar soil are the key to inferring the mechanism of earth evolution, the source of water on earth, the distribution law of cosmic components, etc., especially the measurement of dielectric constant, which is closely related to the calibration of remote sensing parameters. Moreover, the measurement of dielectric constant requires in-situ wide-area detection to be more accurate. The sample returned by sampling is small in scale and there is the influence of sample contamination.

[0003] Some existing detectors use TECP (Thermal and Electrical Conductivity Probe), such as Figure 1 As shown, the dielectric constant of lunar soil can be detected. During the detection process, the physical property probe penetrated into the surface Martian soil, probe No. 1 was used as a heat source, and the temperature changes of physical property probes 2 and 3 were measured. The temperature of probe No. 4, which was farthest from the heat source, was used as the reference temperature. The length of TECP is 118.76 mm, and the length of the physical property probe is 15 mm. Its measurement accuracy is ±10%. However, since TECP was not arranged for drilling detection, its detection depth was limited, so only relevant physical property parameters of surface samples could be obtained.

[0004] The kinetic energy penetration detector is a detection method with low kinetic energy cost and large detection depth, which is convenient for in-situ on-orbit dielectric constant testing and analysis, and can achieve high speed and deep layer, long distance and large range. The kinetic energy penetration is conveniently arranged on the surface of extraterrestrial bodies, combined with the principle of electromagnetic emission, to achieve in-situ detection of dielectric constant.

[0005] Some existing kinetic energy penetration detectors use a multi-probe fixed measurement solution, that is, multiple fixed-position probe heads (electromagnetic transmitting probes and electromagnetic receiving probes) are set at the head of the penetration section. During the penetration and landing process, the head of the penetration section enters the penetrated medium under the action of kinetic energy to detect the dielectric constant. However, this method has the following disadvantages: (1) During the penetration stage, multiple probe heads need to enter the penetrated medium at the same time, and the contact surface is large. The rigidity requirements of the probe itself are high during the design process (simulation). If the probe is deformed, the data will be questioned; (2) Due to the small size of the penetration section, only the dielectric constant of the penetration medium at a close distance between the probes can be detected, and the data is not representative. This scheme provides a self-calibrated large-scale extraterrestrial dielectric constant detection method. Summary of the invention

[0006] The purpose of the present invention is to overcome the deficiencies of the prior art and to provide a two-body separated extraterrestrial body dielectric constant detection device and detection method.

[0007] The objective of the present invention is achieved through the following technical solutions:

[0008] The first aspect of the present invention provides a two-body separated extraterrestrial body dielectric constant detection device, comprising:

[0009] The surface body is located on the surface of the penetrated medium when penetrating the penetrated medium, and a surface body control module is arranged inside the surface body, and the surface body control module includes a first electromagnetic pulse transmitting source and a first electromagnetic pulse receiving source;

[0010] The penetrating body is connected to the surface body through a cable and is located inside the penetrated medium when penetrating the penetrated medium. A penetrating body control module is arranged inside the penetrating body, and the penetrating body control module includes a second electromagnetic pulse transmitting source and a second electromagnetic pulse receiving source.

[0011] Furthermore, the first electromagnetic pulse transmitting source and the second electromagnetic pulse transmitting source transmit electromagnetic pulses in different forms, and the electromagnetic pulse forms include square waves, sine waves, and modulated waves.

[0012] Furthermore, the surface body is provided with a penetrating body mounting portion, and when the penetrating body penetrates the penetrated medium, the penetrating body leaves the penetrating body mounting portion based on the action of kinetic energy, thereby penetrating the inside of the penetrated medium.

[0013] Furthermore, the penetration portion of the penetration body is conical, and the medium contact portion of the surface body is plate-shaped.

[0014] A second aspect of the present invention provides a detection method of a two-body separated extraterrestrial body dielectric constant detection device as described in the first aspect, comprising:

[0015] When penetration is completed, the surface body is located on the surface of the penetrated medium, and the penetrating body is located inside the penetrated medium;

[0016] The first electromagnetic pulse emission source of the surface body control module and the second electromagnetic pulse emission source of the penetrating body control module respectively send electromagnetic pulses;

[0017] The first electromagnetic pulse receiving source of the surface body control module and the second electromagnetic pulse receiving source of the penetrating body control module receive the electromagnetic pulse reflected waves respectively;

[0018] Convert the voltage amplitude of the electromagnetic pulse reflected wave into dielectric constant.

[0019] Furthermore, the step of converting the voltage amplitude of the electromagnetic pulse reflected wave into a dielectric constant includes:

[0020] Calculate a voltage difference ΔV between a first voltage V1 generated by the first electromagnetic pulse receiving source of the surface control module inducing an electromagnetic pulse sent by the second electromagnetic pulse transmitting source of the penetrating control module and a second voltage V2 generated by the second electromagnetic pulse receiving source of the penetrating control module inducing an electromagnetic pulse sent by the first electromagnetic pulse transmitting source of the surface control module;

[0021] According to the voltage difference ΔV and the sending current size I t , obtain the impedance Z of the measured medium t , The first electromagnetic pulse transmitting source of the surface control module and the second electromagnetic pulse transmitting source of the penetration control module transmit an alternating electrical signal of a certain frequency, and the sending current is I t =i t exp(jωt), where i t represents the current amplitude, ω represents the AC frequency, and t represents the time;

[0022] According to the relationship between the imaginary part of impedance and frequency, the capacitance C of the measured medium is obtained, that is, In the formula, Im{Z t} represents the impedance Z t The imaginary part of

[0023] The dielectric constant ε is obtained through the capacitance C of the measured medium, C = εf s ; where f s is the layout factor, which is calculated by fitting the mutual inductance impedance function.

[0024] Furthermore, the function of mutual inductance impedance is calculated and fitted in the following way:

[0025] Acquire experimental data on the ground: perform detection tests at different postures and displacements on the medium with known standard dielectric constant and capacitance, and obtain experimental layout factors at different postures and displacements;

[0026] The impedance, displacement and posture data are used as independent variables and the experimental layout factor is used as the dependent variable to fit the mutual inductance impedance function.

[0027] Furthermore, the displacement data is obtained by integrating acceleration collected by an acceleration sensor installed on the penetrator.

[0028] The beneficial effects of the present invention are:

[0029] In an exemplary embodiment of the present invention, combined with the kinetic penetration flight capability, it is possible to achieve in-situ detection of the dielectric constant at any position of an extraterrestrial body, such as orbital release for penetration analysis; and, an electromagnetic pulse transmitting source and an electromagnetic pulse receiving source are respectively provided on the surface body and the penetrating body, so that during the penetration process, only one probe head needs to enter the interior of the penetrated medium, reducing the contact surface of the probe, thereby reducing the possibility of deformation and further reducing the complexity of the design process (simulation) and the rigidity requirements of the probe itself; in addition, since there is a distance between the surface body and the penetrating body after penetrating the penetrated medium (preferably the maximum distance can be limited by a cable), the dielectric constant data of the penetrated medium detected is more accurate (avoiding the data of the penetrated medium being unrepresentative due to the close distance). BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of TECP of the prior art;

[0031] Figure 2 A schematic diagram before penetration of a two-body separated extraterrestrial body dielectric constant detection device provided in an exemplary embodiment of the present invention;

[0032] Figure 3 A schematic diagram of a two-body separated extraterrestrial body dielectric constant detection device after penetration provided in an exemplary embodiment of the present invention;

[0033] Figure 4 A schematic diagram of the penetration process of a two-body separated extraterrestrial body dielectric constant detection device provided in an exemplary embodiment of the present invention;

[0034] Figure 5 A flow chart of a detection method of a two-body separated extraterrestrial body dielectric constant detection device provided in an exemplary embodiment of the present invention;

[0035] In the figure, 1-surface body, 101-penetrating body installation part, 2-penetrating body, 3-surface body control module, 4-penetrating body control module, 5-penetrated medium, 6-cable, 7-electromagnetic pulse, 8-landing orbit, 9-orbiting orbit, 10-extraterrestrial body. DETAILED DESCRIPTION

[0036] The technical solution of the present invention is described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] In the description of the present invention, it should be noted that the directions or positional relationships indicated by "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. are directions or positional relationships based on the drawings, which are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0038] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0039] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0040] See also Figure 2 and Figure 3 , Figure 2 and Figure 3 A schematic diagram of a two-body separated extraterrestrial body dielectric constant detection device provided in an exemplary embodiment of the present invention before and after penetration is shown, comprising:

[0041] The surface body 1 is located on the surface of the penetrated medium 5 when penetrating the penetrated medium 5. A surface body control module 3 is arranged inside the surface body 1. The surface body control module 3 includes a first electromagnetic pulse transmitting source and a first electromagnetic pulse receiving source.

[0042] The penetrating body 2 is connected to the surface body 1 through a cable 6 and is located inside the penetrated medium 5 when penetrating the penetrated medium 5. A penetrating body control module 4 is provided inside the penetrating body 2, and the penetrating body control module 4 includes a second electromagnetic pulse transmitting source and a second electromagnetic pulse receiving source.

[0043] Specifically, in this exemplary embodiment, the two-body separated extraterrestrial celestial body dielectric constant detection device is located in the orbit 9 and the landing orbit 8 outside the extraterrestrial celestial body 10. Figure 4 As shown, the penetration and landing of the extraterrestrial object 10 is achieved through orbital transfer, and the surface of the extraterrestrial object 10 is the penetrated medium 5.

[0044] like Figure 2As shown in FIG. 1 , before the detection device lands on the landing track 8 on the penetrated medium 5, the surface body 1 and the penetrating body 2 are integrated. Figure 3 As shown, under the action of a certain kinetic energy, the detection device penetrates into the penetrated medium 5. When the surface body 1 and the penetrating body 2 are in contact with the penetrated medium 5, under the action of factors such as overload, the surface body 1 and the penetrating body 2 separate, the surface body 1 is located on the surface of the penetrated medium 5, and the penetrating body 2 penetrates the penetrated medium 5. The surface body 1 and the penetrating body 2 are connected by a cable 6 between the two bodies. After the penetration is completed, the following will be formed Figure 3 The layout form.

[0045] After the intrusion is completed, the first electromagnetic pulse transmitting source of the surface body control module 3 located on the surface of the penetrated medium 5 and the second electromagnetic pulse transmitting source of the penetrating body control module 4 located inside the penetrated medium 5 generate electromagnetic pulses, and the electromagnetic pulse reflected waves will be received by the first electromagnetic pulse receiving source of the surface body control module 3 and the second electromagnetic pulse receiving source of the penetrating body control module 4. Subsequently, the average dielectric constant of the penetrated position can be analyzed according to the self-mutual impedance principle.

[0046] In summary, in this exemplary embodiment, combined with the kinetic penetration flight capability, it is possible to achieve in-situ detection of the dielectric constant at any position of the extraterrestrial body 10, such as orbital release for penetration analysis; and, an electromagnetic pulse transmitting source and an electromagnetic pulse receiving source are respectively provided on the surface body 1 and the penetrating body 2, so that during the penetration process, only one probe head needs to enter the interior of the penetrated medium, reducing the contact surface of the probe, thereby reducing the possibility of deformation and further reducing the complexity of the design process (simulation) and the rigidity requirements of the probe itself; in addition, since after penetrating the penetrated medium 5, there is a distance between the surface body 1 and the penetrating body 2 (preferably the maximum distance can be limited by the cable 6), the detected dielectric constant data of the penetrated medium 5 is more accurate (avoiding the data of the penetrated medium 5 being unrepresentative due to the close distance).

[0047] More preferably, in an exemplary embodiment, the first electromagnetic pulse transmitting source and the second electromagnetic pulse transmitting source transmit electromagnetic pulses 7 in different forms, and the electromagnetic pulses 7 include square waves, sine waves, and modulated waves.

[0048] More preferably, in an exemplary embodiment, if Figure 3 As shown, the surface body 1 is provided with a penetrating body mounting portion 101 , and the penetrating body 2 leaves the penetrating body mounting portion 101 based on kinetic energy when penetrating the penetrated medium 5 , thereby penetrating the inside of the penetrated medium 5 .

[0049] Specifically, in this exemplary embodiment, the surface body 1 and the penetrating body 2 are installed together before penetration. During the penetration process, affected by kinetic energy, the surface body 1 remains on the surface of the penetrated medium 5, and the penetrating body 2 leaves the penetrating body mounting portion 101 of the surface body 1 and enters the interior of the penetrated medium 5.

[0050] More preferably, in an exemplary embodiment, Figure 2 and Figure 3 As shown, the penetration portion of the penetration body 2 is conical, and the medium contact portion of the surface body 1 is plate-shaped.

[0051] Specifically, in this exemplary embodiment, the outer diameters of the surface body 1 and the penetrating body 2 are different. When the surface body 1 contacts the penetrated medium 5, the two bodies will separate under the impact, and the penetrating body 2 penetrates to a certain depth.

[0052] See also Figure 5 , Figure 5 An exemplary embodiment of the present invention provides Figure 2-Figure 3 A detection method of a two-body separated extraterrestrial body dielectric constant detection device as described in the above, comprising:

[0053] When the penetration is completed, the surface body 1 is located on the surface of the penetrated medium 5, and the penetration body 2 is located inside the penetrated medium 5;

[0054] The first electromagnetic pulse emission source of the surface body control module 3 and the second electromagnetic pulse emission source of the penetrating body control module 4 respectively send electromagnetic pulses 7;

[0055] The first electromagnetic pulse receiving source of the surface body control module 3 and the second electromagnetic pulse receiving source of the penetrating body control module 4 receive the electromagnetic pulse reflected waves respectively;

[0056] Convert the voltage amplitude of the electromagnetic pulse reflected wave into dielectric constant.

[0057] Specifically, in this exemplary embodiment, after the invasion is completed, the penetrator control module 4 and the surface body control module 3 will generate an electromagnetic pulse 7, and the voltage amplitude of the electromagnetic pulse reflection wave is processed to obtain the dielectric constant of the corresponding position of the extraterrestrial object 10.

[0058] More preferably, in an exemplary embodiment, converting the voltage amplitude of the electromagnetic pulse reflected wave into a dielectric constant comprises:

[0059] Calculate a voltage difference ΔV between a first voltage V1 generated by the first electromagnetic pulse receiving source of the surface control module inducing an electromagnetic pulse sent by the second electromagnetic pulse transmitting source of the penetrating control module and a second voltage V2 generated by the second electromagnetic pulse receiving source of the penetrating control module inducing an electromagnetic pulse sent by the first electromagnetic pulse transmitting source of the surface control module;

[0060] According to the voltage difference ΔV and the sending current size I t , obtain the impedance Z of the measured medium t , The first electromagnetic pulse transmitting source of the surface control module and the second electromagnetic pulse transmitting source of the penetration control module transmit an alternating electrical signal of a certain frequency, and the sending current is I t =i t exp(jωt), where i t represents the current amplitude, ω represents the AC frequency, and t represents the time;

[0061] According to the relationship between the imaginary part of impedance and frequency, the capacitance C of the measured medium is obtained, that is, In the formula, Im{Z t} represents the impedance Z t The imaginary part of

[0062] The dielectric constant ε is obtained through the capacitance C of the measured medium, C = εf s ; where f s is the layout factor, which is calculated by fitting the mutual inductance impedance function.

[0063] Specifically, in this exemplary embodiment, remote sensing measurement is performed by time domain reflection wave analysis. After the intrusion is completed, electromagnetic pulses will be generated in the control module inside the intruder and the control module on the surface of the body. The voltage amplitude of the electromagnetic pulse reflection wave is normalized to obtain the voltage difference and is equivalent to impedance. The total impedance is inversely proportional to the dielectric constant. Combined with geometric parameters and signal processing, the dielectric constant of the corresponding position of the extraterrestrial body is obtained. Combined with the kinetic penetration flight capability, in-situ detection of the dielectric constant at any position of the extraterrestrial body can be achieved.

[0064] More preferably, in an exemplary embodiment, the function of the mutual inductance impedance is calculated and fitted in the following manner:

[0065] Acquire experimental data on the ground: perform detection tests at different postures and displacements on the medium with known standard dielectric constant and capacitance, and obtain experimental layout factors at different postures and displacements;

[0066] The impedance, displacement and posture data are used as independent variables and the experimental layout factor is used as the dependent variable to fit the mutual inductance impedance function.

[0067] Specifically, in this exemplary embodiment, the mutual inductance impedance function is fitted on the ground by fitting multiple known data (posture, displacement, impedance) and experimental layout factors obtained from experiments. The fitting can be done in any feasible way, such as a neural network or other methods.

[0068] More preferably, in an exemplary embodiment, the displacement data is obtained by integrating acceleration collected by an acceleration sensor installed on the penetrator.

[0069] Obviously, the above embodiments are merely examples for clear explanation, and are not intended to limit the implementation methods. For ordinary technicians in the relevant field, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived from them are still within the protection scope of the invention.

Claims

1. A two-body separation type extraterrestrial body dielectric constant detection device, characterized in that: include: The surface body is located on the surface of the penetrated medium when penetrating the penetrated medium, and a surface body control module is arranged inside the surface body, and the surface body control module includes a first electromagnetic pulse transmitting source and a first electromagnetic pulse receiving source; The penetrating body is connected to the surface body through a cable and is located inside the penetrated medium when penetrating the penetrated medium. A penetrating body control module is arranged inside the penetrating body, and the penetrating body control module includes a second electromagnetic pulse transmitting source and a second electromagnetic pulse receiving source.

2. The device according to claim 1, characterized in that: The first electromagnetic pulse transmitting source and the second electromagnetic pulse transmitting source transmit electromagnetic pulses in different forms, including square waves, sine waves, and modulated waves.

3. The device according to claim 1, characterized in that: The surface body is provided with a penetrating body installation portion. When the penetrating body penetrates the penetrated medium, it leaves the penetrating body installation portion based on the action of kinetic energy, thereby penetrating the inside of the penetrated medium.

4. The device according to claim 1, characterized in that: The penetration portion of the penetration body is conical, and the medium contact portion of the surface body is plate-shaped.

5. A detection method for a two-body separated extraterrestrial body dielectric constant detection device as claimed in any one of claims 1 to 4, characterized in that: include: When penetration is completed, the surface body is located on the surface of the penetrated medium, and the penetrating body is located inside the penetrated medium; The first electromagnetic pulse emission source of the surface body control module and the second electromagnetic pulse emission source of the penetrating body control module respectively send electromagnetic pulses; The first electromagnetic pulse receiving source of the surface body control module and the second electromagnetic pulse receiving source of the penetrating body control module receive the electromagnetic pulse reflected waves respectively; Convert the voltage amplitude of the electromagnetic pulse reflected wave into dielectric constant.

6. The method according to claim 5, characterized in that: The step of converting the voltage amplitude of the electromagnetic pulse reflected wave into a dielectric constant comprises: Calculate a voltage difference ΔV between a first voltage V1 generated by the first electromagnetic pulse receiving source of the surface control module inducing an electromagnetic pulse sent by the second electromagnetic pulse transmitting source of the penetrating control module and a second voltage V2 generated by the second electromagnetic pulse receiving source of the penetrating control module inducing an electromagnetic pulse sent by the first electromagnetic pulse transmitting source of the surface control module; According to the voltage difference ΔV and the sending current size I t , obtain the impedance Z of the measured medium t , The first electromagnetic pulse transmitting source of the surface control module and the second electromagnetic pulse transmitting source of the penetration control module transmit an alternating electrical signal of a certain frequency, and the sending current is I t =i t exp(jωt), where i t represents the current amplitude, ω represents the AC frequency, and t represents the time; According to the relationship between the imaginary part of impedance and frequency, the capacitance C of the measured medium is obtained, that is, In the formula, Im{Z t } represents the impedance Z t The imaginary part of The dielectric constant ε is obtained through the capacitance C of the measured medium, C = εf s ; where f s is the layout factor, which is calculated by fitting the mutual inductance impedance function.

7. The method according to claim 6, characterized in that: The function of mutual inductance impedance is calculated and fitted as follows: Acquire experimental data on the ground: perform detection tests at different postures and displacements on the medium with known standard dielectric constant and capacitance, and obtain experimental layout factors at different postures and displacements; The impedance, displacement and posture data are used as independent variables and the experimental layout factor is used as the dependent variable to fit the mutual inductance impedance function.

8. The method according to claim 7, characterized in that: The displacement data is obtained by integrating the acceleration collected by an acceleration sensor installed on the penetrator.

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