CN111169663A - Deep space detection impact overload test and data wireless transmission measuring device - Google Patents
Deep space detection impact overload test and data wireless transmission measuring device Download PDFInfo
- Publication number
- CN111169663A CN111169663A CN202010054234.XA CN202010054234A CN111169663A CN 111169663 A CN111169663 A CN 111169663A CN 202010054234 A CN202010054234 A CN 202010054234A CN 111169663 A CN111169663 A CN 111169663A
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- antenna
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- outer shell
- overload
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G4/00—Tools specially adapted for use in space
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- G—PHYSICS
- G08—SIGNALLING
- G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
- G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
- G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
Abstract
The invention relates to a deep space exploration impact overload test and data wireless transmission measuring device, belonging to the technical field of deep space exploration; the invention comprises an outer shell with two ends designed as bell mouths, wherein a second overload sensor is arranged in a concave surface at the front end of the outer shell; an inner shell and an antenna cup are sleeved in the outer shell, and a first overload sensor, an acquisition control module, a battery and an antenna module are arranged in the inner shell; an antenna is arranged in the antenna cup. The battery is connected with the acquisition control module, the acquisition control module is connected with the antenna module, the antenna module is connected with the antenna, and the first overload sensor and the second overload sensor are both connected with the acquisition control module. The device has scientific design, simple structure and high equipment integration level, and the multilayer design of the inner shell and the outer shell can be widely applied to deep space detection and high overload recording devices to lay a solid foundation for the subsequent measurement of landing overload of the deep space detection detector.
Description
Technical Field
The invention relates to the technical field of deep space exploration, in particular to a deep space exploration impact overload test and data wireless transmission measuring device.
Background
At present, human beings have more and more exploration tasks on the deep space, and the situation of losing connection is easy to occur after the detector is landed at the current stage, so that the landing of the deep space detector is the key point of the deep space exploration. In addition, the detector is subjected to very severe space environment conditions, a special protection structure is needed, the measurement of the landing overload of the detector in the current stage is still in a blank stage, and the measurement of the overload and the transmission of test data need to be researched. Therefore, there is a need to design a carrier device to solve the above problems.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provide a deep space impact overload test and data wireless transmission measuring device. The device can realize the recording and transmission of data, the device and the landing device are two independent power supply systems, the landing device can store the data into the device in real time, and the data is transmitted back in a wireless mode after the landing.
The invention is realized by the following technical scheme:
a deep space exploration impact overload test and data wireless transmission measuring device comprises an outer shell, wherein the outer shell is cylindrical, the front end of the outer shell is closed, the rear end of the outer shell is open, an outward-expanding front end bell mouth is arranged on the periphery of the front end of the outer shell in a forward extending mode, and the rear end of the outer shell is designed into an outward-expanding rear end bell mouth; a second overload sensor is arranged in a concave surface formed by the horn mouth at the front end of the outer shell, and an external thread is arranged on the outer wall of the horn mouth at the rear end of the outer shell; a buffer cushion is arranged on the front end face in the inner cavity of the outer shell, the inner shell, the outer shell rear end cover, the antenna cup nylon, the antenna cup nylon cover and the compression ring are sequentially arranged in the inner cavity of the outer shell from the front end face to the rear end bell mouth, and a buffer material is arranged between the outer shell rear end cover and the antenna cup nylon; the front end of the inner shell is provided with an inner shell front end cover, and the rear end of the inner shell is provided with an inner shell rear end cover; a first overload sensor, an acquisition control module, a battery and an antenna module are arranged in the inner cavity of the inner shell; the inner shell and the outer shell are tightly matched and assembled by arranging a buffer material; an antenna is arranged in the antenna cup, and a buffer material is filled in a gap between the antenna and the antenna cup; the shell wall of the inner shell is provided with an inner shell antenna cable outlet hole and an inner shell control cable outlet hole, and the shell wall of the outer shell is provided with a second overload sensor outlet hole, a control cable wiring hole, an antenna cable outlet hole and an antenna cable wiring hole; the battery is connected with the acquisition control module, the acquisition control module is connected with the antenna module, and the antenna module sequentially penetrates through the antenna cable outlet hole, the antenna cable outlet hole and the antenna cable wiring hole of the inner shell through cables and then is connected with the antenna; the second overload sensor is connected with the acquisition control module after sequentially passing through the second overload sensor wire outlet hole, the control cable wire outlet hole and the inner shell control cable wire outlet hole through cables, and the first overload sensor is connected with the acquisition control module through cables.
The working principle of the device is as follows: the during operation, the striking produces the high overload of axial in the twinkling of an eye, the interior casing receives the trend of inertial action to the forward motion this moment, make, form relative motion between the shell body, buffer material hardness is lower, compress the original shape of buffer material and absorb the energy that the striking transships produced to the interior casing when the interior casing moves forward, because the hardness of blotter is higher than buffer material, the blotter begins deformation to absorb overload energy when reaching certain energy, the cushioning effect that buffer material in the antenna cup played at the striking in-process is with the same, the holistic buffering guard action of structure has been formed like this. When the impact is carried out, the overload sensor senses that an overload signal is transmitted to the acquisition control module through the cable, the acquisition control module carries out signal conditioning and acquisition storage, test data are sent to the antenna module through the acquisition control module after the impact process is finished, the test data are sent to the antenna through the conditioning of the antenna module and finally sent to the ground through the antenna, and the data are displayed on the ground terminal through the upper computer software through demodulation after the signals are received on the ground. The overall appearance of the device is designed into a shape of bell mouths at two ends, the bell mouths can generate deformation to absorb energy when high overload impact occurs, and the energy transmitted to the inner shell at the moment of impact is effectively reduced, so that the aim of protecting the inner shell is fulfilled.
As the preferred technical scheme, an S-shaped wiring groove is formed in the wall of the shell of the outer shell, and a second overload sensor wire outlet, a control cable wiring hole, an antenna cable wire outlet and an antenna cable wiring hole are formed in the S-shaped wiring groove. The S-shaped wiring groove and the fillet design of the wiring groove reduce the stress concentration of the structure of the outer shell structure when the structure is impacted and overloaded, and effectively improve the overload resistance of the structure.
As a preferable technical scheme, the first overload sensor and the second overload sensor are installed and fixed through sensor thread installation holes.
As the preferred technical scheme, the acquisition control module, the antenna module and the antenna are all installed and fixed through fixed nylon.
Preferably, the cushion pad has a hardness higher than that of the cushion material.
The device solves the problem of testing the impact overload environment in the landing process of the deep space probe, and can accurately transmit impact overload data to the ground terminal through wireless transmission after the deep space probe is impacted. The device has scientific design, simple structure and high equipment integration level, and the multilayer design of the inner shell and the outer shell can be widely applied to deep space detection and high overload recording devices to lay a solid foundation for the subsequent measurement of landing overload of the deep space detection detector.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate exemplary embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention.
Fig. 1 is a schematic three-dimensional appearance of the device of the present invention.
Fig. 2 is a first front view of the apparatus of the present invention.
Fig. 3 is a second front view of the device of the present invention.
3 fig. 3 4 3 is 3 a 3 sectional 3 view 3 taken 3 along 3 line 3 a 3- 3 a 3 in 3 fig. 3 2 3. 3
Fig. 5 is a first front view of the inner housing of the device of the present invention.
Fig. 6 is a second front view of the inner housing of the device of the present invention.
In the figure: 1-outer shell, 2-front end bell mouth, 3-rear end bell mouth, 4-sensor thread mounting hole, 5-second overload sensor, 6-external thread, 7-buffer pad, 8-inner shell, 9-outer shell rear end cover, 10-antenna cup nylon, 11-antenna cup, 12-antenna cup nylon cover, 13-press ring, 14-buffer material, 15-inner shell front end cover, 16-inner shell rear end cover, 17-first overload sensor, 18-acquisition control module, 19-battery, 20-antenna module, 21-fixed nylon, 22-antenna, 23-inner shell antenna cable outlet hole, 24-inner shell control cable outlet hole, 25-second overload sensor outlet hole, 26-control cable outlet hole, 27-control cable wiring hole, 28-antenna cable outlet hole, 29-antenna cable wiring hole and 30-S type wiring groove.
Detailed Description
In order that those skilled in the art will better understand the present invention, a more complete and complete description of the present invention is provided below in conjunction with the accompanying drawings and embodiments. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
As shown in fig. 1 to 6, a deep space exploration impact overload test and data wireless transmission measuring device comprises an outer shell 1, wherein the outer shell 1 is cylindrical, the front end of the outer shell 1 is closed, and the rear end of the outer shell is open, an outward-expanding front end bell mouth 2 is arranged on the front end periphery of the outer shell 1 in a forward extending manner, and the rear end opening of the outer shell 1 is designed to be an outward-expanding rear end bell mouth 3; the diameter of the cylindrical part in the middle of the outer shell 1 is 80mm, and the wall thickness of the outer shell 1 is 8 mm.
A sensor thread mounting hole 4 with M5 thread is arranged in a concave surface formed by the front end bell mouth 2 of the outer shell 1, and a second overload sensor 5 is arranged in the sensor thread mounting hole 4; the outer wall of the rear end bell mouth 3 of the outer shell 1 is provided with an external thread 6 with a thread of M106, and the external thread 6 is used for being connected with a carrier.
The preceding terminal surface in the inner chamber of shell body 1 is provided with blotter 7, installs interior casing 8, shell body rear end cap 9, antenna cup nylon 10, antenna cup 11, antenna cup nylon lid 12 and clamping ring 13 by blotter 7 to rear end horn mouth 3 in proper order in the inner chamber of shell body 1 to be provided with buffer material 14 between shell body rear end cap 9 and antenna cup nylon 10.
An inner shell front end cover 15 is arranged at the front end of the inner shell 8, and an inner shell rear end cover 16 is arranged at the rear end of the inner shell 8; a sensor thread mounting hole 4 with a thread of M5, an acquisition control module mounting cavity, a battery mounting cavity and an antenna module mounting cavity are arranged in the inner cavity of the inner shell 8, a first overload sensor 17 is mounted in the sensor thread mounting hole 4, an acquisition control module 18 is mounted in the acquisition control module mounting cavity, a battery 19 is mounted in the battery mounting cavity, an antenna module 20 is mounted in the antenna module mounting cavity, and the acquisition control module 18 and the antenna module 20 are both mounted and fixed through fixing nylon 21; the inner shell 8 and the outer shell 1 are assembled in a close fit mode through arranging buffer materials 14, namely the buffer materials 14 are filled between the inner shell 8 and the buffer pad 7, between the inner shell and the wall of the outer shell 1 and between the inner shell and the rear end cover 9 of the outer shell.
An antenna 22 is mounted in the antenna cup 11, the antenna 22 is mounted and fixed by fixing nylon 21, and a gap between the antenna 22 and the antenna cup 11 is filled with a buffer material 14.
An inner shell antenna cable outlet hole 23 and an inner shell control cable outlet hole 24 are formed in the shell wall of the inner shell 8, a second overload sensor outlet hole 25, a control cable outlet hole 26, a control cable wiring hole 27, an antenna cable outlet hole 28 and an antenna cable wiring hole 29 are formed in the shell wall of the outer shell 1, an S-shaped wiring groove 30 is formed in the shell wall of the outer shell 1, and the second overload sensor outlet hole 25, the control cable outlet hole 26, the control cable wiring hole 27, the antenna cable outlet hole 28 and the antenna cable wiring hole 29 are all formed in the S-shaped wiring groove 30.
The battery 19 in the inner shell 8 is connected with the acquisition control module 18, the acquisition control module 18 is connected with the antenna module 20, and the antenna module 20 sequentially passes through the antenna cable outlet hole 23, the antenna cable outlet hole 28 and the antenna cable wiring hole 29 of the inner shell through a cable and then is connected with the antenna 22; the second overload sensor 5 on the outer shell 1 sequentially passes through a second overload sensor wire outlet hole 25, a control cable wire outlet hole 26 and an inner shell control cable wire outlet hole 24 through cables and then is connected with the acquisition control module 18; the first overload sensor 17 in the inner housing 8 is connected directly to the acquisition control module 18.
When the device is used for verification test, a 125 smoothbore cannon is used for simulation test, a 125mm smoothbore cannon is used as a carrier, and the device is connected and fixed with the carrier cannon through the external thread 6 on the outer wall of the rear end bell mouth 3. The high overload environment is generated instantly when the cannonball is targeted to simulate the hard landing process of the detector. The method specifically comprises the following steps: produce high overload at the shell in-process of targeting, second overload sensor 5 on the concave surface of shell body 1 measures the overload signal and passes through the cable and send the signal to the collection control module 18 in the interior casing 8, the overload signal that first overload sensor 17 measured directly sends the signal to collection control module 18 through internal connection, collection control module 18 carries out signal conditioning and gathers the storage, reach the process and end through antenna 22 with data transmission to ground receiving terminal, the overload signal shows after the host computer is handled can.
The technical solutions in the embodiments of the present invention are clearly and completely described above, and the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Claims (5)
1. The utility model provides a deep space exploration striking overload test and data wireless transmission measuring device which characterized in that: the outer shell is cylindrical, the front end of the outer shell is closed, the rear end of the outer shell is open, an outward-expanding front end bell mouth is arranged on the periphery of the front end of the outer shell in an extending mode, and the rear end of the outer shell is designed to be an outward-expanding rear end bell mouth; a second overload sensor is arranged in a concave surface formed by the horn mouth at the front end of the outer shell, and an external thread is arranged on the outer wall of the horn mouth at the rear end of the outer shell; a buffer cushion is arranged on the front end face in the inner cavity of the outer shell, the inner shell, the outer shell rear end cover, the antenna cup nylon, the antenna cup nylon cover and the compression ring are sequentially arranged in the inner cavity of the outer shell from the front end face to the rear end bell mouth, and a buffer material is arranged between the outer shell rear end cover and the antenna cup nylon; the front end of the inner shell is provided with an inner shell front end cover, and the rear end of the inner shell is provided with an inner shell rear end cover; a first overload sensor, an acquisition control module, a battery and an antenna module are arranged in the inner cavity of the inner shell; the inner shell and the outer shell are tightly matched and assembled by arranging a buffer material; an antenna is arranged in the antenna cup, and a buffer material is filled in a gap between the antenna and the antenna cup; the shell wall of the inner shell is provided with an inner shell antenna cable outlet hole and an inner shell control cable outlet hole, and the shell wall of the outer shell is provided with a second overload sensor outlet hole, a control cable wiring hole, an antenna cable outlet hole and an antenna cable wiring hole; the battery is connected with the acquisition control module, the acquisition control module is connected with the antenna module, and the antenna module sequentially penetrates through the antenna cable outlet hole, the antenna cable outlet hole and the antenna cable wiring hole of the inner shell through cables and then is connected with the antenna; the second overload sensor is connected with the acquisition control module after sequentially passing through the second overload sensor wire outlet hole, the control cable wire outlet hole and the inner shell control cable wire outlet hole through cables, and the first overload sensor is connected with the acquisition control module through cables.
2. The deep space exploration impact overload test and data wireless transmission measuring device according to claim 1, wherein: an S-shaped wiring groove is formed in the shell wall of the shell body, and a second overload sensor wire outlet hole, a control cable wire outlet hole, an antenna cable wire outlet hole and an antenna cable wire outlet hole are formed in the S-shaped wiring groove.
3. The deep space exploration impact overload test and data wireless transmission measuring device according to claim 1 or 2, wherein: the first overload sensor and the second overload sensor are installed and fixed through sensor thread installation holes.
4. The deep space exploration impact overload test and data wireless transmission measuring device according to claim 1 or 2, wherein: the acquisition control module, the antenna module and the antenna are all installed and fixed through fixed nylon.
5. The deep space exploration impact overload test and data wireless transmission measuring device according to claim 1 or 2, wherein: the hardness of the cushion pad is higher than the hardness of the cushioning material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010054234.XA CN111169663B (en) | 2020-01-17 | 2020-01-17 | Deep space detection impact overload test and data wireless transmission measuring device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010054234.XA CN111169663B (en) | 2020-01-17 | 2020-01-17 | Deep space detection impact overload test and data wireless transmission measuring device |
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| CN111169663A true CN111169663A (en) | 2020-05-19 |
| CN111169663B CN111169663B (en) | 2021-09-14 |
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| CN202010054234.XA Active CN111169663B (en) | 2020-01-17 | 2020-01-17 | Deep space detection impact overload test and data wireless transmission measuring device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111661367A (en) * | 2020-07-31 | 2020-09-15 | 北京控制与电子技术研究所 | Autonomous navigation flight control system for deep space impact |
| CN111731511A (en) * | 2020-07-31 | 2020-10-02 | 北京控制与电子技术研究所 | Data rescue system applied to extraterrestrial celestial body detector |
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| CN111731511A (en) * | 2020-07-31 | 2020-10-02 | 北京控制与电子技术研究所 | Data rescue system applied to extraterrestrial celestial body detector |
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| CN111169663B (en) | 2021-09-14 |
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