CN116609854B - Ground testing device and method for inspection quality in-orbit release process - Google Patents
Ground testing device and method for inspection quality in-orbit release process Download PDFInfo
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- CN116609854B CN116609854B CN202310899705.0A CN202310899705A CN116609854B CN 116609854 B CN116609854 B CN 116609854B CN 202310899705 A CN202310899705 A CN 202310899705A CN 116609854 B CN116609854 B CN 116609854B
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- 230000007246 mechanism Effects 0.000 claims abstract description 149
- 230000009467 reduction Effects 0.000 claims abstract description 70
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- 239000003990 capacitor Substances 0.000 description 19
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
- G01V13/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices covered by groups G01V1/00 – G01V11/00
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
- G01V7/00—Measuring gravitational fields or waves; Gravimetric prospecting or detecting
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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Abstract
The application provides a ground test device and a ground test method for an on-orbit release process of a test mass, wherein the test mass is positioned in the center of a whole falling cabin and has two states of locking fixation and free suspension. The falling cabin module comprises a falling cabin release mechanism and a falling cabin shell, and provides a microgravity environment for the testing device in the process of free falling. The locking and releasing mechanism comprises a three-stage locking and releasing function and is used for locking and releasing the inspection quality. The wireless control module is connected with the locking release mechanism through a signal wire and receives external wireless signals to control the locking release mechanism to execute corresponding functions. The sensing and control module comprises a capacitance polar plate, a capacitance displacement sensing and electrostatic feedback control circuit and is used for detecting and controlling the released inspection quality. The two-stage vibration reduction structure comprises a high-rigidity spring vibration reduction primary mechanism, a low-rigidity reed secondary vibration reduction mechanism and a movable bolt, and damage to the internal structure and functions of the testing device caused by impact during landing is prevented. The application reduces the risk of failure of the on-orbit release of the proof mass.
Description
Technical Field
The application belongs to the field of precise measurement, and particularly relates to a ground testing device and method for an on-orbit release process of a test quality.
Background
The gravitational wave detection has important significance in the fields of generalized relativity, astronomical observation, astronomy and the like. The inertial sensor is used as a core load for space gravitational wave detection, satellite gravity measurement and the like, the core task is to ensure that the inspection mass in the inertial sensor is free to suspend in a frame, and the locking release mechanism is one of core key technologies for realizing suspension of the inspection mass in an ideal position. Firstly, in the satellite launching and lifting stage, the inspection quality needs to be locked and fixed, so that the inspection quality and the sensitive probe are prevented from being damaged due to a severe vibration environment; secondly, when the satellite reaches a certain orbit height, the locking and releasing mechanism is required to release the inspection quality with higher positioning precision and extremely low residual speed, and the inspection quality is free to suspend, so that an inertial reference is provided for gravitational wave detection. During the track release phase, if the proof mass fails to release or the release speed is too high, the capacitive control system will not be able to pull the proof mass back to the ideal suspended state, which will result in the failure of the entire task. Therefore, we need to perform a ground test on the proof mass in-orbit release process before satellite transmission.
The inertial sensor that the LISA-Pathfinder program of 2016 was designed to be installed was equipped with a lock release mechanism and subjected to extensive ground testing prior to its launch. The Trento university builds a ground simulation evaluation device (TMMF device for short) for on-orbit release of an inertial sensor on the ground, but only researches on adhesion characteristics generated by contact of a test mass and a release mechanism during on-orbit are not really reproduced in a process of three complete stages of a locking release mechanism.
Disclosure of Invention
Aiming at the defects of the prior art, the application aims to provide a ground test device and a ground test method for an on-orbit release process of a test quality, and aims to solve the problems that the prior art cannot truly reproduce the locking release process of the test quality on the ground and cannot perform ground test on the test quality in advance.
To achieve the above object, in a first aspect, the present application provides a ground test device for an on-orbit release process of a proof mass, comprising: the device comprises a cabin falling module, a locking and releasing mechanism, a quality inspection, a sensing and control module and a two-stage vibration reduction mechanism;
the detection mass is arranged in the sensing and control module, and the sensing and control module is arranged in the locking and releasing mechanism; the locking release mechanism and the two-stage vibration reduction mechanism are arranged in the cabin falling module, and the two-stage vibration reduction mechanism connects the locking release mechanism with the cabin falling module; the cabin falling module is arranged in a microgravity environment;
the lock release mechanism includes: the locking device comprises a plurality of first-stage locking rods, a plurality of second-stage locking release plungers and a plurality of third-stage release ejector pins, wherein the third-stage release ejector pins are positioned in the second-stage locking release plungers; the primary locking rod is used for exerting force at a plurality of edges and corners of the inspection mass so as to lock and fix the inspection mass; when the cabin falling module freely falls, the locking release mechanism releases the inspection quality, at the moment, the primary locking rod is retracted, the secondary locking release plunger is advanced towards the center of the inspection quality to fix the inspection quality, then the secondary locking release plunger is retracted, the tertiary release thimble is advanced towards the center of the inspection quality to fix the inspection quality, and finally the tertiary release thimble is quickly retracted, so that the inspection quality is released; when the distance between the cabin falling mechanism and the ground is smaller than a preset value, the primary locking rod locks the inspection quality again;
the sensing and control module comprises a capacitance polar plate frame, a capacitance polar plate and a capacitance displacement sensing and electrostatic feedback control circuit; the capacitive plate frame is fixedly connected with the inner wall of the locking release mechanism, the inspection quality is arranged in the capacitive plate frame, the capacitive plate is fixed on the capacitive plate frame, the capacitive displacement sensing and electrostatic feedback control circuit is used for detecting differential capacitance signals generated by the capacitive plate after the inspection quality is released, and feedback control voltage is applied to the capacitive plate according to the differential capacitance signals so as to control the inspection quality at a preset balance position;
the two-stage vibration reduction mechanism comprises a first-stage vibration reduction mechanism and a second-stage vibration reduction mechanism; the first-stage vibration reduction mechanism is positioned at the bottom of the cabin falling module, the second-stage vibration reduction mechanism is positioned at the upper end of the first-stage vibration reduction mechanism, and the locking release mechanism is suspended and carried; the first-stage vibration reduction mechanism is used for absorbing severe impact generated when the cabin falling module falls to the ground, and the second-stage vibration reduction mechanism is used for absorbing residual weak impact which is not thoroughly absorbed by the first-stage vibration reduction mechanism.
It should be noted that, performing a complete ground release test on the inspection quality requires three issues to be considered: the first aspect considers environmental factors, needs to provide space-like microgravity environment for the release process, the second aspect considers locking-release of the inspection mass and locking protection process before landing, and the third aspect considers vibration reduction protection problem after release of the inspection mass before landing. The release distance of the ground is limited after all, unlike in space environment, if the inspection quality falls directly on the ground, the inspection quality can be damaged by vibration or the service life can be affected.
The device provided by the application can well solve the problems in the three aspects, and provides a complete scheme for ground test for quality inspection.
Optionally, the ground test device determines the test result by: determining whether the inspection quality can be controlled at a balance position in the cabin falling module releasing process according to the differential capacitance signal generated by the inspection quality released and the capacitance polar plate;
if the inspection quality cannot be controlled at the balance position in a certain test, the parameters of the release process of the locking release mechanism are adjusted or different release schemes are adopted, so that the inspection quality can be controlled at the balance position in the release process of the cabin falling module in the subsequent test.
Optionally, the external structure of the drop cabin module is a spherical structure.
Optionally, the primary vibration reduction mechanism adopts a spring, and the secondary vibration reduction mechanism adopts a reed.
Optionally, the two-stage vibration damping mechanism further comprises: a first latch and a second latch;
the primary vibration reduction mechanism is connected with the cabin falling module through a fixed connection clamp;
the secondary vibration reduction mechanism is connected with the primary vibration reduction mechanism and the locking release mechanism through the fixed connection clamp and is positioned at two sides of the locking release mechanism;
the first bolt is positioned in the middle of the first-stage vibration reduction mechanism, and the second bolt is positioned in the middle of the second-stage vibration reduction mechanism; the first bolt and the second bolt are used for ensuring that the first-stage vibration reduction mechanism and the second-stage vibration reduction mechanism do not work in the falling process of the cabin falling mechanism when working;
when the distance between the cabin falling mechanism and the ground is smaller than a preset value, the bolt does not work any more so as to start the primary vibration reduction mechanism and the secondary vibration reduction mechanism to reduce vibration.
Optionally, the primary locking lever, the secondary locking release plunger and the tertiary release plunger fix the proof mass by penetrating a hole reserved on the capacitor plate frame.
Optionally, the microgravity environment is provided by a vacuum tower or a vacuum well.
In a second aspect, the application provides a ground test method for an on-orbit release process of a proof mass, comprising the following steps:
applying a force to lock the inspection mass at the corner of the inspection mass, and placing the locked inspection mass in a microgravity environment;
allowing the inspection mass to freely fall in a locked state at the corner, withdrawing the force at the corner of the inspection mass in the falling process, applying force to the inspection mass center to fix the corner, withdrawing the force at the inspection mass center, applying force to the inspection mass center again to fix the corner, and finally quickly withdrawing the applied force so as to release the inspection mass;
when the distance between the inspection mass and the ground is smaller than a preset value, applying force to the corner of the inspection mass again to lock the inspection mass;
determining a differential capacitance signal after the inspection quality is released through a capacitance plate around the inspection quality, and applying feedback control voltage on the capacitance plate according to the differential capacitance signal so as to control the inspection quality at a preset balance position;
the vibration reduction mechanism is adopted to absorb severe impact and residual weak impact generated when the module internally bearing the inspection mass falls to the ground.
Optionally, determining whether the inspection quality can be controlled at the balance position after being released according to the differential capacitance signal generated by the capacitor plate after the inspection quality is released;
if the proof mass cannot be controlled in the equilibrium position during a test, the parameters of the proof mass release process are adjusted or a different release scheme is employed so that subsequent tests can control the proof mass in the equilibrium position during the proof mass release process.
In general, the above technical solutions conceived by the present application have the following beneficial effects compared with the prior art:
the application provides a ground test device and a ground test method for an on-orbit release process of a test mass.
The application provides a ground test device and a ground test method for an on-orbit release process of a test quality, wherein a cabin falling structure is designed into a spherical structure, and the structure can reduce the influence of different flow directions of gas on an internal locking release mechanism; the ground testing device for the on-orbit release process of the inspection quality adopts a two-stage vibration reduction mechanism to absorb the landing impact, so that the internal structure and the functions of the testing device are protected from being damaged; the latch structure ensures that the testing device is fixedly connected with the cabin falling module and the locking release mechanism respectively in the falling process, and ensures that the spring and the reed do not damage the microgravity environment of the testing device.
The application provides a ground test device and a ground test method for on-orbit release of a test mass, which can carry out ground test and debugging on the on-orbit release process of the test mass on the ground and protect the test mass from being damaged by landing impact. The application tests the complete process of on-orbit release and the electrostatic capture process of the inspection quality on the ground, eliminates the potential risk of on-orbit, and reduces the risk of failure of on-orbit release of the inspection quality.
Drawings
FIG. 1 is a functional block diagram of a ground test device for an on-orbit release process of proof mass provided by an embodiment of the present application;
FIG. 2 is a schematic diagram of a ground test environment for an on-orbit release process of proof mass provided by an embodiment of the present application;
fig. 3 is a schematic front view of a ground test device for an on-orbit release process of a proof mass according to an embodiment of the present application.
Throughout the drawings, the same reference numerals are used to designate the same elements or structures, including: the device comprises a cabin falling module 1, a locking and releasing mechanism 2, a wireless control module 3, a check mass 4, a sensing and control module 5, a two-stage vibration reduction mechanism 6, a fixed connection clamp 7, a fixed rod 8, a cabin falling and releasing mechanism 101, an external structure 102, a primary locking rod 201, a secondary locking and releasing plunger 202, a tertiary releasing thimble 203, a capacitor plate frame 501, a capacitor plate 502, a capacitor displacement sensing and control circuit 503, a primary vibration reduction mechanism 601, a secondary vibration reduction mechanism 602 and a bolt 603.
Detailed Description
For convenience of understanding, the following explains and describes english abbreviations and related technical terms related to the embodiments of the application.
Embodiments of the present application will be described below with reference to the accompanying drawings in the embodiments of the present application.
The application provides a ground testing device based on microgravity environment for an inspection quality on-orbit release process, which is shown in figure 1 and comprises a cabin falling module 1, a locking release mechanism 3, a wireless control module 2, an inspection quality 4, a sensing and control module 5 and a two-stage vibration reduction mechanism 6; the cabin falling module 1 internally comprises a locking and releasing mechanism 2, a wireless control module 2, a check mass 4, a sensing and control module 5 and a two-stage vibration reduction mechanism 6.
The locking and releasing mechanism 3 is arranged in the center of the cabin falling module 1, and realizes locking and fixing and releasing the inspection quality 4 through a three-stage locking and releasing function; the wireless control module 5 is arranged above the inside of the locking and releasing mechanism 3 and is used for receiving external signals to control the locking and releasing mechanism 3 to execute corresponding functions; the check mass 4 is arranged in the center of the locking and releasing mechanism 3, namely, the check mass 4 is positioned in the center of the cabin falling module, and the locking and releasing mechanism 3 realizes the in-orbit releasing process of the cabin falling module 1 in the free falling process; the sensing and control module 5 is arranged in the locking and releasing mechanism 3, and after the inspection mass 4 is released by the locking and releasing mechanism 3, the sensing and control module 5 is used for detecting the movement information of the inspection mass 4 after being released and controlling the movement information to be at a balance position; the two-stage vibration reduction mechanism 6 is fixedly connected with the cabin falling module 1 and the locking release mechanism 3 and is used for absorbing huge impact generated when the cabin falling module 1 falls to the ground, so that the internal structure and functions of the testing device are protected from being damaged.
In one embodiment, as shown in FIG. 2, the overall exterior structure of the drop module 1 is designed as a spherical structure, and free-fall motion is performed in a vacuum drop tower or drop well 20, providing a microgravity environment 19 for the testing device 18.
Still further, the drop module includes a drop release mechanism and an external structure; the falling cabin release mechanism is positioned right above the falling cabin module, can be of a mechanical fixing structure and can be fixed and separated from an external device in a sucking disc manner of an electromagnet; the external structure is designed into a spherical structure, so that the influence of different flow directions of gas on the internal locking and releasing mechanism can be reduced.
Furthermore, the first-stage locking rod in the locking release mechanism locks and fixes the inspection quality in the initial stage, when the cabin falling module falls down, the first-stage locking rod is firstly transferred to the second-stage release plunger, then the second-stage release plunger is transferred to the third-stage release thimble, and then the third-stage release thimble is quickly retracted, so that the inspection quality is released, and the above steps are the on-track release process of the inspection quality.
Furthermore, the third-stage release thimble is positioned inside the second-stage release plunger and can perform telescopic movement.
Furthermore, the inspection mass is in a cube shape and is in a free suspension state in the capacitor plate frame after being released by the three-stage release ejector pins.
The ground test device and the ground test method for the on-orbit release process of the inspection mass are mainly applied to the ground test of the on-orbit release process of the inspection mass in the inertial sensor; the inspection quality is positioned in the center of the whole measuring device and has two states of locking fixation and free suspension.
As shown in fig. 3, the locking and releasing mechanism 2, the wireless control module 3, the inspection mass 4, the sensing and control module 5, the two-stage vibration damping mechanism 6, the fixed connection clamp 7 and the fixed rod 8 are all installed in the cabin falling module 1. The falling cabin module 1 comprises a falling cabin release mechanism 101 and an external structure 102, wherein the falling cabin release mechanism 101 is positioned right above the falling cabin module 1, the falling cabin module 1 and an external device are fixed and separated in a mechanical structure or an electromagnet sucker mode, the external structure 102 adopts a spherical structure, and the influence of different flow directions of gas on the internal locking release mechanism 2 in the free falling process of the falling cabin module 1 can be reduced.
In the embodiment of the application, the locking and releasing mechanism 2 comprises a primary locking rod 201, a secondary locking and releasing plunger 202 and a tertiary releasing thimble 203; the 8 primary locking rods 201 are symmetrically arranged on two sides of the locking and releasing mechanism 2, and the 8 primary locking rods 201 apply thousands of N-level force at 8 edges of the inspection mass 4 to lock and fix the inspection mass 4; the 2 secondary locking release plungers 202 are symmetrically arranged on two sides of the locking release mechanism 2, and the 2 secondary locking release plungers 202 apply force at the center of the inspection mass 4 to lock and fix the inspection mass 4; the 2 three-stage release pins 203 are respectively located in the 2 two-stage locking release plungers 202, and can perform telescopic movement for fixing and releasing the inspection mass 4. The locking release mechanism 2 is arranged at the middle position of the cabin falling module 1, and in the falling process of the cabin falling module 1, an external instruction is received through the wireless control module 3, the locking release mechanism 2 firstly retracts the primary locking rod 201, simultaneously the secondary release plunger 202 advances to fix the inspection mass 4, then the secondary release plunger 202 retracts, simultaneously the tertiary release thimble 203 advances to fix the inspection mass 4, and then the tertiary release thimble 203 is quickly retracted, so that the inspection mass is released; when the cabin falling module 1 is about to fall to the ground, an external instruction is received again, and the check mass 4 is locked and fixed again by the primary locking rod 201 of the locking and releasing mechanism 2, so that the check mass 4 is prevented from being damaged due to the falling impact of the cabin falling module 1.
In the embodiment of the application, the wireless control module 3 is arranged right above the locking and releasing mechanism 2 and is used for receiving an external wireless instruction to control the locking and releasing mechanism 2, so that the three-level performance of the locking and releasing mechanism 2 is realized and the inspection quality 4 is released.
In the embodiment of the application, the inspection mass 4 is arranged at the center of the locking release mechanism 2, namely the center of the cabin falling module 1, and the shape of the inspection mass 4 adopts a cube shape.
In the embodiment of the present application, the sensing and control module 5 includes a capacitor plate frame 501, a capacitor plate 502, and a capacitor displacement sensing and control circuit 503. The capacitor plate frame 501 is connected with the locking and releasing mechanism 2 through a fixing rod 8, the capacitor plate 502 is directly and fixedly connected to the capacitor plate frame 501, the gap between the capacitor plate 502 and the inspection mass 4 is 3mm-5mm, the capacitor displacement sensing and electrostatic feedback control circuit 503 is arranged right below the locking and releasing mechanism 2 and connected with the capacitor plate through a wire, and is used for detecting differential capacitance signals generated by the capacitor plate 8 after the inspection mass 4 is released, and applying feedback control voltage on the capacitor plate 8 according to the differential capacitance signals to generate electrostatic force so as to control the inspection mass at a balance position.
In the embodiment of the application, the two-stage vibration reduction mechanism 6 comprises a first-stage high-stiffness spring vibration reduction mechanism 601, a second-stage low-stiffness reed vibration reduction mechanism 602 and a bolt 603, wherein the first-stage vibration reduction mechanism 601 and the second-stage vibration reduction mechanism 602 are fixedly connected with the locking release mechanism 2 and the cabin falling module 1 through a fixed connection clamp 7, the first-stage high-stiffness spring vibration reduction mechanism 601 is positioned at the bottom of the cabin falling module, and the second-stage low-stiffness reed vibration reduction mechanism 602 is positioned at two sides of the locking release mechanism 2. The bolt 603 is respectively positioned between the primary vibration reduction mechanism 601 and the secondary vibration reduction mechanism 602, and ensures that the testing device is respectively fixedly connected with the falling cabin module 1 and the locking release mechanism 1 in the falling process of the falling cabin module in the falling process, so that the spring and the reed are ensured not to damage the microgravity environment of the testing device; just before landing, the bolt 603 structure is not fixedly connected with the landing module 1 and the locking release mechanism, the primary spring and the secondary reed damping mechanism start to work, the landing impact is absorbed, and the internal structure and the functions of the testing device are protected from being damaged.
The application also provides a method for measuring the release of the inspection quality by the ground testing device for the release of the inspection quality on the track, which comprises the following steps:
(1) The cabin falling module is fixed and separated from an external device through a cabin falling releasing mechanism, and in the cabin falling process, the wireless control module receives an external instruction to control the locking releasing mechanism so as to realize the release of the inspection quality;
(2) After the inspection mass is released by the locking and releasing mechanism, detecting motion information of six degrees of freedom of the inspection mass after the inspection mass is released by the capacitor polar plate and the capacitor displacement sensing circuit, and pulling the inspection mass back to the balance position through the electrostatic feedback control circuit;
(3) Before the falling module falls to the ground, the two-stage vibration reduction mechanism starts to work, so that the impact of the falling module in the landing process is guaranteed not to damage an internal measuring device and the performance is guaranteed not to be damaged.
It is to be understood that the terms such as "comprises" and "comprising," which may be used in this application, indicate the presence of the disclosed functions, operations or elements, and are not limited to one or more additional functions, operations or elements. In the present application, terms such as "comprising" and/or "having" may be construed to mean a particular feature, number, operation, constituent element, component, or combination thereof, but may not be construed to exclude the presence or addition of one or more other features, numbers, operations, constituent elements, components, or combination thereof.
Furthermore, in the present application, the expression "and/or" includes any and all combinations of the words listed in association. For example, the expression "a and/or B" may include a, may include B, or may include both a and B.
In describing embodiments of the present application, it should be noted that the term "coupled" should be interpreted broadly, unless otherwise explicitly stated and defined, for example, the term "coupled" may be either detachably coupled or non-detachably coupled; may be directly connected or indirectly connected through an intermediate medium. Wherein, "fixedly connected" means that the relative positional relationship is unchanged after being connected with each other. "rotationally coupled" means coupled to each other and capable of relative rotation after coupling. "slidingly coupled" means coupled to each other and capable of sliding relative to each other after being coupled. References to directional terms in the embodiments of the present application, such as "top", "bottom", "inner", "outer", "left", "right", etc., are merely with reference to the directions of the drawings, and thus are used in order to better and more clearly illustrate and understand the embodiments of the present application, rather than to indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the embodiments of the present application.
In addition, in embodiments of the present application, the mathematical concepts mentioned are symmetrical, equal, parallel, perpendicular, etc. These definitions are all for the state of the art and not strictly defined in a mathematical sense, allowing for minor deviations, approximately symmetrical, approximately equal, approximately parallel, approximately perpendicular, etc. For example, a is parallel to B, meaning that a is parallel or approximately parallel to B, and the angle between a and B may be between 0 degrees and 10 degrees. A and B are perpendicular, which means that the angle between A and B is between 80 degrees and 100 degrees.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any person skilled in the art will readily recognize that variations or substitutions are within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. A ground testing device for an on-orbit release process of a proof mass, comprising: the device comprises a cabin falling module, a locking and releasing mechanism, a quality inspection, a sensing and control module and a two-stage vibration reduction mechanism;
the detection mass is arranged in the sensing and control module, and the sensing and control module is arranged in the locking and releasing mechanism; the locking release mechanism and the two-stage vibration reduction mechanism are arranged in the cabin falling module, and the two-stage vibration reduction mechanism connects the locking release mechanism with the cabin falling module; the cabin falling module is arranged in a microgravity environment;
the lock release mechanism includes: the locking device comprises a plurality of first-stage locking rods, a plurality of second-stage locking release plungers and a plurality of third-stage release ejector pins, wherein the third-stage release ejector pins are positioned in the second-stage locking release plungers; the primary locking rod is used for exerting force at a plurality of edges and corners of the inspection mass so as to lock and fix the inspection mass; when the cabin falling module freely falls, the locking release mechanism releases the inspection quality, at the moment, the primary locking rod is retracted, the secondary locking release plunger is advanced towards the center of the inspection quality to fix the inspection quality, then the secondary locking release plunger is retracted, the tertiary release thimble is advanced towards the center of the inspection quality to fix the inspection quality, and finally the tertiary release thimble is quickly retracted, so that the inspection quality is released; when the distance between the cabin falling mechanism and the ground is smaller than a preset value, the primary locking rod locks the inspection quality again;
the sensing and control module comprises a capacitance polar plate frame, a capacitance polar plate and a capacitance displacement sensing and electrostatic feedback control circuit; the capacitive plate frame is fixedly connected with the inner wall of the locking release mechanism, the inspection quality is arranged in the capacitive plate frame, the capacitive plate is fixed on the capacitive plate frame, the capacitive displacement sensing and electrostatic feedback control circuit is used for detecting differential capacitance signals generated by the capacitive plate after the inspection quality is released, and feedback control voltage is applied to the capacitive plate according to the differential capacitance signals so as to control the inspection quality at a preset balance position;
the two-stage vibration reduction mechanism comprises a first-stage vibration reduction mechanism and a second-stage vibration reduction mechanism; the first-stage vibration reduction mechanism is positioned at the bottom of the cabin falling module, the second-stage vibration reduction mechanism is positioned at the upper end of the first-stage vibration reduction mechanism, and the locking release mechanism is suspended and carried; the first-stage vibration reduction mechanism is used for absorbing severe impact generated when the cabin falling module falls to the ground, and the second-stage vibration reduction mechanism is used for absorbing residual weak impact which is not thoroughly absorbed by the first-stage vibration reduction mechanism.
2. The apparatus of claim 1, wherein the surface testing apparatus determines the test result by: determining whether the inspection quality can be controlled at a balance position in the cabin falling module releasing process according to the differential capacitance signal generated by the inspection quality released and the capacitance polar plate;
if the inspection quality cannot be controlled at the balance position in a certain test, the parameters of the release process of the locking release mechanism are adjusted or different release schemes are adopted, so that the inspection quality can be controlled at the balance position in the release process of the cabin falling module in the subsequent test.
3. The apparatus of claim 1, wherein the exterior structure of the drop module is a spherical structure.
4. The apparatus of claim 1, wherein the primary vibration reduction mechanism employs a spring and the secondary vibration reduction mechanism employs a reed.
5. The apparatus of claim 1, wherein the two-stage vibration reduction mechanism further comprises: a first latch and a second latch;
the primary vibration reduction mechanism is connected with the cabin falling module through a fixed connection clamp;
the secondary vibration reduction mechanism is connected with the primary vibration reduction mechanism and the locking release mechanism through the fixed connection clamp and is positioned at two sides of the locking release mechanism;
the first bolt is positioned in the middle of the first-stage vibration reduction mechanism, and the second bolt is positioned in the middle of the second-stage vibration reduction mechanism; the first bolt and the second bolt are used for ensuring that the first-stage vibration reduction mechanism and the second-stage vibration reduction mechanism do not work in the falling process of the cabin falling mechanism when working;
when the distance between the cabin falling mechanism and the ground is smaller than a preset value, the bolt does not work any more so as to start the primary vibration reduction mechanism and the secondary vibration reduction mechanism to reduce vibration.
6. The apparatus of any one of claims 1 to 5, wherein the primary lock lever, secondary lock release plunger and tertiary release spike secure the proof mass by penetrating a hole reserved in the capacitive plate frame.
7. The apparatus of any one of claims 1 to 5, wherein the microgravity environment is provided by a vacuum tower or a vacuum well.
8. A ground testing method of a ground testing device for an on-orbit release process of a proof mass according to any one of claims 1 to 7, comprising the steps of:
applying a force to lock the inspection mass at the corner of the inspection mass, and placing the locked inspection mass in a microgravity environment;
allowing the inspection mass to freely fall in a locked state at the corner, withdrawing the force at the corner of the inspection mass in the falling process, applying force to the inspection mass center to fix the corner, withdrawing the force at the inspection mass center, applying force to the inspection mass center again to fix the corner, and finally quickly withdrawing the applied force so as to release the inspection mass;
when the distance between the inspection mass and the ground is smaller than a preset value, applying force to the corner of the inspection mass again to lock the inspection mass;
determining a differential capacitance signal after the inspection quality is released through a capacitance plate around the inspection quality, and applying feedback control voltage on the capacitance plate according to the differential capacitance signal so as to control the inspection quality at a preset balance position;
the vibration reduction mechanism is adopted to absorb severe impact and residual weak impact generated when the module internally bearing the inspection mass falls to the ground.
9. The method of claim 8, wherein determining whether the proof mass is released can be controlled to an equilibrium position based on a differential capacitance signal generated by the proof mass and the capacitive plate after the proof mass is released;
if the proof mass cannot be controlled in the equilibrium position during a test, the parameters of the proof mass release process are adjusted or a different release scheme is employed so that subsequent tests can control the proof mass in the equilibrium position during the proof mass release process.
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