CN110901961A - Landing vibration-damping attachment mechanism for asteroid probe - Google Patents
Landing vibration-damping attachment mechanism for asteroid probe Download PDFInfo
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- CN110901961A CN110901961A CN201911284917.8A CN201911284917A CN110901961A CN 110901961 A CN110901961 A CN 110901961A CN 201911284917 A CN201911284917 A CN 201911284917A CN 110901961 A CN110901961 A CN 110901961A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
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Abstract
The invention belongs to the field of surface landing of asteroids in deep space exploration, and particularly relates to a landing vibration reduction attachment mechanism for a asteroid probe, wherein an adapter is of a barrel-shaped structure with one open end and the other closed end, a cabin door is arranged at the open end, one side of the cabin door is hinged with the open end of the adapter through a flat hinge, and the other side of the cabin door is in a closed state before the asteroid is released; the outer surface of the small satellite is provided with a buffering attachment mechanism, a spring is arranged between the small satellite and the inner surface of the bottom plate at the closed end of the adapter, one end of the spring is fixed on the adapter, and the other end of the spring is abutted against the small satellite or the buffering attachment mechanism arranged on the outer side surface of the small satellite and is compressed by the small satellite before being released. The invention can provide carrying and releasing functions for the small satellite, and can ensure high reliability of carrying and releasing; the buffer attachment mechanism has high impact absorption capacity, can realize landing buffer in any direction and attitude, and can effectively protect the small satellite detector and scientific loads thereof.
Description
Technical Field
The invention belongs to the field of surface landing of asteroids in deep space exploration, and particularly relates to a landing vibration reduction attachment mechanism of a asteroid probe.
Background
Asteroids generally refer to celestial bodies within the solar system that orbit the sun or other planets, which are generally much smaller in volume and mass than planets. To date, humans have found over 100 million asteroids in the solar system, with the actual number being much greater than that found. The asteroid is generally considered by scientists as a small celestial body formed by accumulating residual substances condensed from original solar star clouds after a solar system is formed, and original solar system information is probably kept; the asteroid detection is carried out, so that breakthrough of basic scientific problems such as solar system origin, planet evolution and life origin can be promoted, and valuable information is provided for researching the evolution process and the evolution history of the solar system and the planet by human beings.
The appearance of the small satellite is similar to a cuboid shape, and the small satellite has the outstanding characteristics of low threshold, low cost, strong expansibility, short manufacturing and launching period and the like. At present, the small satellite is in a vigorous development trend, gradually shows a trend of expanding from earth observation to a deep space exploration field, and becomes a big bright point in the deep space exploration field. The application potential of the small satellite in the deep space exploration field is highly valued abroad, the small satellite can be used as a secondary aircraft for flying, can be deployed at a destination for executing tasks and is communicated with the earth directly or through a carrier, the convenient condition of low-cost exploration is provided for scientists, and the new application that cannot be realized by a large satellite can be completed.
China will perform 469219 kamo' oalewa (2016HO3) asteroid exploration for the first time after 2020, and it is observed that its diameter is only 40m to 100 m. The surface of the asteroid is weakly gravitational (gravity level about 10) due to its small volume and mass-1g～10-3g) The escape speed is low, and the star surface landing is very difficult to realize.
The small satellite is carried on the main detector through an adapter, and the on-orbit release function is provided through the adapter. The attachment mechanism is mainly used for absorbing impact energy generated by the microsatellite detector in the process of landing impact on the surface of the asteroid, ensuring that the overload coefficients of an attachment structure and a carrying instrument are reduced to be within a range required by system design, and preventing the attachment structure from being damaged under high impact acceleration; and the detector is prevented from escaping due to overlarge rebound speed in the attachment process, and the detector is ensured to be firmly attached to the surface of the asteroid. The detector contacts and collides with the asteroid for the first time at a certain speed and posture, and under the environment of weak gravitation, the buffer mechanism of the detector and the surface of the asteroid can not completely absorb impact energy, so that the detector can bounce off the asteroid after collision, and can stop on the surface of the asteroid after multiple landing rebounds and collisions. Therefore, it is required that the probe can meet any attitude for passive buffer landing. The prior landing mode of the extraterrestrial celestial sphere surface detector mainly adopts passive attachment mechanisms such as an active reverse-thrust rocket or an air bag buffer device and a deployable or non-deployable leg type, but the conventional attachment system cannot be adopted by a small satellite landing device due to the limited mass and launching space.
At present, no precedent for using the small satellite to carry out the surface soft landing of the extraterrestrial star exists at home and abroad, so that no case for applying a small satellite buffering landing attachment mechanism exists.
Disclosure of Invention
In order to solve the problem that the small satellite lands on the small planet, the invention aims to provide a landing vibration-damping attachment mechanism of the small planet detector.
The purpose of the invention is realized by the following technical scheme:
the invention comprises an adapter arranged on a main detector and a moonlet positioned in the adapter, wherein the adapter is of a barrel-shaped structure with one open end and the other closed end, the open end is provided with a cabin door, one side of the cabin door is hinged with the open end of the adapter through a flat hinge, the other side of the cabin door is in a closed state before the moonlet is released, and the flat hinge provides a rotating fulcrum and a buffering effect for the cabin door when the moonlet is released; the outer surface of the small satellite is provided with a buffering attachment mechanism, a spring is arranged between the small satellite and the inner surface of the bottom plate of the closed end of the adapter, one end of the spring is fixed on the inner surface of the bottom plate of the closed end of the adapter, the other end of the spring is abutted to the buffering attachment mechanism arranged on the outer side surface of the small satellite or the small satellite and is compressed by the small satellite before being released, the spring is reset from the compression state when the small satellite is released, the elastic potential energy of the spring is converted into the kinetic energy of the small satellite, and the initial releasing speed along the axis direction of the small satellite is provided for the small satellite.
Wherein: the buffer attachment mechanism comprises an attachment pad and honeycomb plates, the honeycomb plates are fixedly connected to six outer side surfaces of the cuboid-shaped moonlet, and the attachment pad is mounted on the outer surface of each honeycomb plate; the other end of the spring is abutted with an adhesion pad arranged on the outer side surface of the bottom of the minisatellite.
The buffering attachment mechanism is foam aluminum plate, namely, foam aluminum plate is installed on the surface of six outer sides of the rectangular small satellite, and the other end of the spring is abutted to the foam aluminum plate installed on the surface of the outer side of the bottom of the small satellite.
The utility model discloses a little satellite, including the body, buffering attachment mechanism, acupuncture attachment mechanism, bottom connecting plate, foam buffering ball, bracing piece and bottom connecting plate, buffering attachment mechanism is acupuncture attachment mechanism, all is equipped with acupuncture attachment mechanism on six outside surfaces of the little satellite of cuboid shape, and this acupuncture attachment mechanism includes foam buffering ball, bracing piece and bottom connecting plate, the bottom connecting plate is installed on the outside surface of little satellite, the one end of bracing piece links to each other with this bottom connecting plate, and the other end is equipped with foam buffering ball.
One end of the spring is fixed in the middle of the inner surface of the bottom plate at the closed end of the adapter.
The invention has the advantages and positive effects that:
the invention can provide carrying and releasing functions for the small satellite, and can ensure high reliability of carrying and releasing; the buffer attachment mechanism has high impact absorption capacity, can realize landing buffer in any direction and posture, has the outstanding advantages of light weight, small volume, strong weather resistance, low power consumption and the like, and can effectively protect the small satellite detector and the scientific load thereof.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a structural cross-sectional view of the present invention;
FIG. 3 is an exploded view of a buffer attachment mechanism according to a first embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a second embodiment of a buffer attachment mechanism according to the present invention;
FIG. 5 is a second schematic structural view of a second buffer attachment mechanism according to a second embodiment of the present invention;
FIG. 6 is a schematic structural diagram of a third embodiment of a buffer attachment mechanism of the present invention;
wherein: 1 is an adapter, 2 is a moonlet, 3 is a buffer attachment mechanism, 3101 is a bottom adhesive pad, 3102 is a bottom cellular board, 3103 is a right side adhesive pad, 3104 is a right side cellular board, 3105 is a rear cellular board, 3106 is a rear adhesive pad, 3107 is a top cellular board, 3108 is a top adhesive pad, 3109 is a left side cellular board, 3110 is a left side adhesive pad, 3111 is a front adhesive pad, 3112 is a front cellular board, 3201 is a top foamed aluminum board, 3202 is a front foamed aluminum board, 3203 is a right side foamed aluminum board, 3204 is a left side foamed aluminum board, 3205 is a rear foamed aluminum board, 3206 is a bottom foamed aluminum board, 4 is a hatch door, 5 is a flat hinge, 6 is a spring, 7 is an M5 hexagon socket head screw, 8 is a needle-punched attachment mechanism, 801 is a damping buffer ball, 802 is a flexible support rod, 803 is a base.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1 and 2, the present invention includes an adapter 1 mounted on a main detector and a moonlet 2 located inside the adapter 1, where the adapter 1 is a barrel structure with one open end and the other closed end, the adapter 1 of the present embodiment is a square barrel shape with one open end, the open end is provided with a hatch 4, one side of the hatch 4 is hinged to the open end of the adapter 1 through a flat hinge 5, the other side of the hatch 4 is in a closed state before the moonlet 2 is released, and the flat hinge 5 provides a pivot and a buffer effect for the hatch 4 to rotate when the moonlet 2 is released. The other side of the hatch 4 of this embodiment is connected to the open end of the adapter 1 by means of explosive bolts, by means of which the moonlet 2 is fixed inside the adapter 1.
The outer surface of the minisatellite 2 is provided with a buffering attachment mechanism 3 which provides a landing buffering function for the minisatellite 2 in any direction and attitude. A spring 6 is arranged between the minisatellite 2 and the inner surface of the bottom plate at the closed end of the adapter 1, one end of the spring 6 is fixed on the inner surface of the bottom plate at the closed end of the adapter 1, and the other end of the spring 6 is abutted against a buffering attachment mechanism 3 arranged on the outer side surface of the minisatellite 2 and is pressed by the minisatellite 2 before being released to be in a compression state; one end of the spring 6 of this embodiment is fixed to the middle of the inner surface of the bottom plate at the closed end of the adapter 1. When the small satellite 2 is released, the spring 6 is reset from a compressed state to a free extension state, the elastic potential energy of the spring 6 is converted into the kinetic energy of the small satellite 2, and the initial release speed along the axis direction of the small satellite 2 is provided for the small satellite 2.
Example one
As shown in fig. 1 to 3, the buffering and attaching mechanism 3 of the present embodiment is a buffering and energy absorbing honeycomb panel and a carbon nanotube adhesive pad attaching mechanism, and includes an adhesive pad (the adhesive pad of the present embodiment is a carbon nanotube adhesive pad) and a honeycomb panel, wherein the honeycomb panel is fixedly connected to six outer side surfaces of a cuboid-shaped moonlet 2, and the adhesive pad is mounted on an outer surface of each honeycomb panel. The other end of the spring 6 abuts against an adhesive pad mounted on the outer surface of the bottom of the moonlet 2. The pads of this embodiment are divided into a bottom pad 3101, a right pad 3103, a rear pad 3106, a top pad 3108, a left pad 3110 and a front pad 3111; the honeycomb panel of this embodiment is divided into a bottom honeycomb panel 3102, a right honeycomb panel 3104, a rear honeycomb panel 3105, a top honeycomb panel 3107, a left honeycomb panel 3109, and a front honeycomb panel 3112; the bottom honeycomb plate 3102, the right honeycomb plate 3104, the rear honeycomb plate 3105, the top honeycomb plate 3107, the left honeycomb plate 3109 and the front honeycomb plate 3112 are fixed to six outer side surfaces of the small satellite 2 by screws, respectively, and the bottom adhesive pad 3101, the right adhesive pad 3103, the rear adhesive pad 3106, the top adhesive pad 3108, the left adhesive pad 3110 and the front adhesive pad 3111 are adhered to the outer side surfaces of the bottom honeycomb plate 3102, the right honeycomb plate 3104, the rear honeycomb plate 3105, the top honeycomb plate 3107, the left honeycomb plate 3109 and the front honeycomb plate 3112 by glue, respectively. The other end of the spring 6 abuts on the middle position of the bottom adhesive pad 3101.
Example two
As shown in fig. 1 and 2, and fig. 4 and 5, the cushion attachment mechanism 3 of the present embodiment is an aluminum foam plate, that is, an aluminum foam plate is attached to all of six outer surfaces of the rectangular parallelepiped microsatellite 2. The other end of the spring 6 abuts against a foamed aluminum plate mounted on the outer surface of the bottom of the moonlet 2. The foamed aluminum plate of the present embodiment is divided into a top foamed aluminum plate 3201, a front foamed aluminum plate 3202, a right foamed aluminum plate 3203, a left foamed aluminum plate 3204, a rear foamed aluminum plate 3205, and a bottom foamed aluminum plate 3206, and the top foamed aluminum plate 3201, the front foamed aluminum plate 3202, the right foamed aluminum plate 3203, the left foamed aluminum plate 3204, the rear foamed aluminum plate 3205, and the bottom foamed aluminum plate 3206 are each fixed to six outer side surfaces of the moonlet 2 by nine M5 hexagon socket head screws 7. The other end of the spring 6 abuts against the middle position of the bottom aluminum foam plate 3206.
EXAMPLE III
As shown in fig. 1, 2 and 6, the cushion attachment mechanism 3 of the present embodiment is a needling attachment mechanism 8, the needling attachment mechanism 8 is provided on six outer surfaces of the rectangular parallelepiped-shaped small satellite 2, the needling attachment mechanism 8 includes a foam cushion ball 801, a support rod 802 and a bottom connection plate 803, the bottom connection plate 803 is mounted on the outer surface of the small satellite 2, one end of the support rod 802 is connected to the bottom connection plate 803, and the other end is provided with the foam cushion ball 801. In the present embodiment, four needling attachment mechanisms 8 are fixed to the four corners of the top and the four corners of the bottom of the minisatellite 2, and six needling attachment mechanisms 8 are fixed to the four outer surfaces of the remaining front, rear, left, and right sides, respectively, and these six needling attachment mechanisms 8 are distributed at the four corners and the middle positions on both sides in the longitudinal direction. The other end of the spring 6 abuts against the middle position of the bottom outer surface of the minisatellite 2.
The working principle of the invention is as follows:
the adapter 1, the cabin door 4, the flat hinge 5 and the spring 6 form a carrying release mechanism, and the carrying release mechanism and the buffering attachment mechanism 3 are designed to meet the requirement that the structural rigidity of a detection system is enough to bear corresponding dynamic load and dynamic stress, so that the reliability of the whole satellite is ensured, the mass is reduced as much as possible, and the light weight design is realized.
The adapter 1 is fixed to the main detector, and during launch and flight, the spring 6 is in compression and the hatch 4 is closed. When the moonlet 2 is released and the adapter 1 receives a command, the explosion bolt on the cabin door 4 is broken, the cabin door 4 is opened, and the flat hinge 5 provides a rotating fulcrum and a buffering effect for the cabin door 4; the explosion bolt on the minisatellite 2 is broken, the hatch door 4 is opened, the spring 6 is recovered to a free extension state from a compression state, the elastic potential energy of the spring 6 is converted into the kinetic energy of the minisatellite 2, and the initial release speed along the axial direction of the minisatellite 2 is provided.
According to the release speed of the small satellite 2 from the adapter 1, one of the three embodiments of the buffer attachment mechanism 3 is selected, so that the effect of relieving impact is realized, and the small satellite detector and the internal scientific load are protected. The method specifically comprises the following steps:
if the microsatellite 2 is released from the adapter 1 at a relatively low velocity (e.g.. ltoreq.1 m/s), the microsatellite 2 will land on its surface at an approximately constant velocity with respect to the target asteroid. The microsatellite 2 is small in mass and speed, so that impacts have a relatively small effect on it, and how quickly to reduce the speed of the detector and prevent bounce escape becomes a major consideration. In the first embodiment, an adhesion mechanism based on van der waals force is adopted to cover the adhesion pad on the outer surface of the honeycomb plate, so that the stable adhesion property of the adhesion pad is exerted, the adhesion pad is adhered to rocks, fragments and other objects on the surface of the asteroid during landing, the friction coefficient is increased, and the sliding resistance and the rebound resistance are increased, so that the detector is quickly and stably attached to the surface of the asteroid.
If the minisatellite 2 is released from the main probe at a relatively high speed (e.g. > 1m/s), the impact of rock fragments on the surface of the minisatellite may cause damage to the probe and internal scientific loads if not protected by the cushioning energy absorbing material. And a honeycomb plate is additionally arranged between the outermost adhesion pad and the outer shell of the minisatellite 2 for buffering and energy absorption, or the second embodiment or the third embodiment is adopted for converting the landing impact energy into the deformation energy of the honeycomb plate, the foamed aluminum plate or the needling adhesion mechanism, so that the absorption of larger landing impact energy is realized.
Claims (5)
1. The landing vibration-damping attachment mechanism for the asteroid probe comprises an adapter installed on a main probe and a moonlet located inside the adapter, and is characterized in that: the adapter (1) is of a barrel-shaped structure with one open end and the other closed end, a cabin door (4) is arranged at the open end, one side of the cabin door (4) is hinged with the open end of the adapter (1) through a flat hinge (5), the other side of the cabin door (4) is in a closed state before the moonlet (2) is released, and the flat hinge (5) provides a rotating fulcrum and a buffering effect for the cabin door (4) when the moonlet (2) is released; the outer surface of the small satellite (2) is provided with a buffering attachment mechanism (3), a spring (6) is arranged between the small satellite (2) and the inner surface of the bottom plate of the closed end of the adapter (1), one end of the spring (6) is fixed on the inner surface of the bottom plate of the closed end of the adapter (1), the other end of the spring is abutted to the buffering attachment mechanism (3) installed on the outer side surface of the small satellite (2) or the small satellite (2), the spring (6) is compressed by the small satellite (2) before being released and is in a compression state, the spring (6) is reset by the compression state when the small satellite (2) is released, the elastic potential energy of the spring (6) is converted into the kinetic energy of the small satellite (2), and the initial release speed along the axis direction of the small satellite (2) is provided for.
2. The asteroid probe landing vibration damping attachment mechanism of claim 1, characterized in that: the buffer attachment mechanism (3) comprises an attachment pad and cellular boards, the cellular boards are fixedly connected to six outer side surfaces of the cuboid-shaped moonlet (2), and the attachment pad is mounted on the outer surface of each cellular board; the other end of the spring (6) is abutted with an adhesion pad arranged on the outer surface of the bottom of the minisatellite (2).
3. The asteroid probe landing vibration damping attachment mechanism of claim 1, characterized in that: the buffering attachment mechanism (3) is a foamed aluminum plate, namely, the foamed aluminum plates are arranged on the surfaces of six outer sides of the microsatellite (2) in a cuboid shape, and the other end of the spring (6) is abutted to the foamed aluminum plate arranged on the surface of the outer side of the bottom of the microsatellite (2).
4. The asteroid probe landing vibration damping attachment mechanism of claim 1, characterized in that: buffering attachment mechanism (3) are acupuncture attachment mechanism (8), all are equipped with acupuncture attachment mechanism (8) on six outside surfaces of the minisatellite (2) of cuboid shape, and this acupuncture attachment mechanism (8) are including foam buffering ball (801), bracing piece (802) and bottom connecting plate (803), install on the outside surface of minisatellite (2) bottom connecting plate (803), the one end of bracing piece (802) links to each other with this bottom connecting plate (803), and the other end is equipped with foam buffering ball (801).
5. The asteroid probe landing vibration damping attachment mechanism of claim 1, characterized in that: one end of the spring (6) is fixed in the middle of the inner surface of the bottom plate at the closed end of the adapter (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201911284917.8A CN110901961A (en) | 2019-12-13 | 2019-12-13 | Landing vibration-damping attachment mechanism for asteroid probe |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911284917.8A CN110901961A (en) | 2019-12-13 | 2019-12-13 | Landing vibration-damping attachment mechanism for asteroid probe |
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| CN110901961A true CN110901961A (en) | 2020-03-24 |
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| CN201911284917.8A Pending CN110901961A (en) | 2019-12-13 | 2019-12-13 | Landing vibration-damping attachment mechanism for asteroid probe |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112269390A (en) * | 2020-10-15 | 2021-01-26 | 北京理工大学 | Small celestial body surface fixed-point attachment trajectory planning method considering bounce |
| CN113933887A (en) * | 2021-11-04 | 2022-01-14 | 北京卫星环境工程研究所 | Method and device for detecting composition of asteroid substances |
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| CN105659758B (en) * | 2009-09-08 | 2013-05-08 | 北京空间飞行器总体设计部 | One detector Landing Buffer mechanism |
| US20140131521A1 (en) * | 2012-05-07 | 2014-05-15 | The Johns Hopkins University | Adaptor System for Deploying Small Satellites |
| CN104627390A (en) * | 2014-12-18 | 2015-05-20 | 北京空间机电研究所 | Mars exploration landing buffer device |
| US20170369191A1 (en) * | 2016-06-28 | 2017-12-28 | University Of Southern California | Instrument Lander Utilizing a CubeSat Platform for In Situ Exploration of Asteroids and Comets |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH02180192A (en) * | 1988-12-23 | 1990-07-13 | Showa Aircraft Ind Co Ltd | Buffer device for box-like structure to be transported |
| CN105659758B (en) * | 2009-09-08 | 2013-05-08 | 北京空间飞行器总体设计部 | One detector Landing Buffer mechanism |
| US20140131521A1 (en) * | 2012-05-07 | 2014-05-15 | The Johns Hopkins University | Adaptor System for Deploying Small Satellites |
| CN104627390A (en) * | 2014-12-18 | 2015-05-20 | 北京空间机电研究所 | Mars exploration landing buffer device |
| US20170369191A1 (en) * | 2016-06-28 | 2017-12-28 | University Of Southern California | Instrument Lander Utilizing a CubeSat Platform for In Situ Exploration of Asteroids and Comets |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112269390A (en) * | 2020-10-15 | 2021-01-26 | 北京理工大学 | Small celestial body surface fixed-point attachment trajectory planning method considering bounce |
| CN112269390B (en) * | 2020-10-15 | 2021-09-21 | 北京理工大学 | Small celestial body surface fixed-point attachment trajectory planning method considering bounce |
| CN113933887A (en) * | 2021-11-04 | 2022-01-14 | 北京卫星环境工程研究所 | Method and device for detecting composition of asteroid substances |
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Application publication date: 20200324 |