CN112727975A - Space micro-impact butt joint vibration reduction device and method - Google Patents
Space micro-impact butt joint vibration reduction device and method Download PDFInfo
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- CN112727975A CN112727975A CN202011521396.6A CN202011521396A CN112727975A CN 112727975 A CN112727975 A CN 112727975A CN 202011521396 A CN202011521396 A CN 202011521396A CN 112727975 A CN112727975 A CN 112727975A
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- butt joint
- driver
- rubber block
- feedback controller
- pressure sensor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F7/00—Vibration-dampers; Shock-absorbers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/002—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion characterised by the control method or circuitry
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/06—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a spatial micro-impact butt joint vibration damping device and a spatial micro-impact butt joint vibration damping method. The damping device is an active space butt joint damping device consisting of a high-precision pressure sensor, a metal rubber block, a butt joint port, a driver and a feedback controller. In the device, a high-precision pressure sensor, a metal rubber block and a driver are distributed in an angle mode, the metal rubber block is used as a damping part, the high-precision pressure sensor is used for testing the stress condition in the butt joint process, and a feedback controller is used for motion control and the driver executes motion actions. The damping system has smaller structure size, lighter weight and adjustable damping force, so that the space docking speed is higher, the applicable impact range is wider, the influence on tasks caused by overlarge or undersize damping force in the docking process can be avoided, and the spacecraft can be quickly separated after the space docking is finished.
Description
Technical Field
The invention belongs to the field of butt joint of spacecraft, and particularly relates to a space micro-impact butt joint vibration damping device and method.
Background
With the steady advance of moon exploration project plans in China, a large screen of deep space exploration in China is uncovered. In deep space exploration such as moon, mars, space station supply and the like, on-orbit butt joint is required to be completed, and material, transmission supply and information interaction are carried out. The difficulty of the butt joint process is mainly embodied in three aspects, namely, initial deviation is overcome and comprises attitude and position deviation, relative speed is eliminated, and the butt joint process is prevented from colliding due to the fact that the butt joint process needs to be coordinated and matched with a control system.
The space butt joint vibration damper mainly plays a role in eliminating space butt joint speed deviation, the mode of eliminating the space butt joint speed deviation is mainly completed through a passive buffer damping system with a spring at present, however, the passive buffer damping system has the problems of large structural size, heavy weight, nonadjustable damping in the butt joint process, slow butt joint speed and complex emergency separation structure.
Disclosure of Invention
The invention provides a space micro-impact butt joint damping device and method, aiming at solving the problems of a space butt joint passive buffering damping system in the prior art.
The technical scheme of the space micro-impact butt joint damping device comprises the following steps: a spatial micro-impact butt joint vibration damper comprises: the high-precision pressure sensor, the metal rubber block and the driver are sequentially arranged at the butt joint, the feedback controller is arranged at the butt joint, and the high-precision pressure sensor and the driver are in circuit connection with the feedback controller; the butt joint interface is a butt joint matching interface, the metal rubber block is used as a damping part, the high-precision pressure sensor is used for detecting pressure change in the butt joint process, and the feedback controller controls the driver to move according to the pressure change.
Further, the driver drives the metal rubber block to do linear motion.
Furthermore, the high-precision pressure sensor, the metal rubber block and the driver are distributed in an angle mode.
Furthermore, the butt joint port adopts a conical butt joint port, so that the butt joint forced guiding function is realized.
Further, the driver adjusts the rigidity of the metal rubber block.
Furthermore, the feedback controller receives pressure data of the high-precision pressure sensor and processes the data, and meanwhile, the feedback controller issues an action instruction to control the action of the driver, so that closed-loop control is realized.
The invention also provides a space micro-impact butt joint vibration damping method, which comprises the following steps:
step one, sequentially installing a high-precision pressure sensor, a metal rubber block and a driver on a butt joint;
step two, mounting a feedback controller on the interface;
thirdly, connecting the circuits of the high-precision pressure sensor, the driver and the feedback controller;
step four, extruding the high-precision pressure sensor by the contact surface in the butt joint process, and feeding back the pressure value to the feedback controller;
step five, the feedback controller sends an action signal to drive the driver to act, and the rigidity of the metal rubber block is adjusted in the tiny displacement;
step six, the active end and the passive end gradually approach to complete micro-impact butt joint;
step seven, the feedback controller sends out an action signal to the driver to move and compress the metal rubber block;
and step eight, after the butt joint is completed, the locking mechanism is unlocked, and the metal rubber block provides power for automatically separating the driving end from the driven end.
Has the advantages that:
(1) the damper has smaller structural size and lighter weight;
(2) the displacement of the damping action in the butt joint process is small, the spatial butt joint guidance performance is good, and the butt joint speed is high;
(3) the rigidity of the metal rubber damper can be greatly adjusted by small-displacement motion of the driver, and the range of impact adaptation of the spacecraft during butt joint is wider;
(4) the magnitude of the damping force can realize closed-loop control, micro-impact butt joint can be guaranteed in the butt joint process, and the butt joint impact force can be guaranteed not to influence the internal equipment and flight attitude of the aircraft; after the space butt joint is completed, the rapid separation of the active end and the passive end can be ensured.
Drawings
Fig. 1 is a structural composition diagram of a spatial micro-impact butting vibration damping device according to the invention.
In the figure: 1-high precision pressure sensor, 2-metal rubber block, 3-interface, 4-driver, 5-feedback controller.
Detailed Description
Referring to fig. 1, a spatial micro-impact butt joint vibration damping device: the device comprises a high-precision pressure sensor 1, a metal rubber block 2, a butt joint port 3, a driver 4 and a feedback controller 5, wherein the high-precision pressure sensor 1, the metal rubber block 2 and the driver 4 are sequentially arranged at the butt joint port 3, the feedback controller 5 is arranged at the butt joint port 3, and the high-precision pressure sensor 1 and the driver 4 are in circuit connection with the feedback controller 5; the butt joint port 3 is a butt joint matching port, the metal rubber block 2 is used as a damping part, the high-precision pressure sensor 1 is used for detecting pressure change in the butt joint process, and the feedback controller 5 controls the driver to move according to the pressure change.
Further, the driver 4 drives the metal rubber block 2 to perform a linear motion.
Further, the high-precision pressure sensor 1, the metal rubber block 2 and the driver 4 are distributed in an angle mode.
Furthermore, the butt joint port 3 adopts a conical butt joint port, so that the butt joint forced guiding function is realized.
Further, the driver 4 adjusts the rigidity of the metal rubber block.
Further, the feedback controller 5 receives the pressure data of the high-precision pressure sensor 1 and processes the data, and simultaneously issues an action instruction to control the action of the driver, so that closed-loop control is realized.
The invention also provides a space micro-impact butt joint vibration damping method,
firstly, a high-precision pressure sensor 1, a metal rubber block 2 and a driver 4 are sequentially arranged on a butt joint port 3;
step two, mounting a feedback controller 5 on the interface 3;
step three, connecting the circuits of the high-precision pressure sensor 1, the driver 4 and the feedback controller 5;
step four, extruding the high-precision pressure sensor 1 by the contact surface in the butt joint process, and feeding the pressure value back to the feedback controller 5;
step five, the feedback controller 5 sends an action signal to the driver 4 to act, and the rigidity of the metal rubber block is adjusted in the micro displacement;
step six, the active end and the passive end gradually approach to complete micro-impact butt joint;
step seven, the feedback controller 5 sends out an action signal to drive the driver 4 to move and press the metal rubber block 2 tightly;
and step eight, after the butt joint is completed, the locking mechanism is unlocked, and the metal rubber block provides power for automatically separating the driving end from the driven end.
By adopting the damping device, the damper has smaller structural size and lighter weight; the displacement of the damping action in the butt joint process is small, the spatial butt joint guidance performance is good, and the butt joint speed is high; the rigidity of the metal rubber damper can be greatly adjusted by small-displacement motion of the driver, and the range of impact adaptation of the spacecraft during butt joint is wider; the magnitude of the damping force can realize closed-loop control, micro-impact butt joint can be guaranteed in the butt joint process, and the butt joint impact force can be guaranteed not to influence the internal equipment and flight attitude of the aircraft; after the space butt joint is completed, the rapid separation of the active end and the passive end can be ensured.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides a little impact butt joint damping device in space which characterized in that: the damping device comprises a high-precision pressure sensor, a metal rubber block, a butt joint port, a driver and a feedback controller, wherein the high-precision pressure sensor, the metal rubber block and the driver are sequentially arranged at the butt joint port, and the feedback controller is arranged at the butt joint port; the high-precision pressure sensor and the driver are connected with a feedback controller circuit; the butt joint interface is a butt joint matching interface, the metal rubber block is used as a damping part, the high-precision pressure sensor is used for detecting pressure change in the butt joint process, and the feedback controller controls the driver to move according to the pressure change.
2. The spatial micro-impact butt joint vibration damping device according to claim 1, characterized in that: the driver drives the metal rubber block to do linear motion.
3. The spatial micro-impact butt joint vibration damping device according to claim 1, characterized in that: the high-precision pressure sensor, the metal rubber block and the driver are distributed in an angle mode.
4. The spatial micro-impact butt joint vibration damping device according to claim 1, characterized in that: the butt joint port adopts a conical butt joint port, so that the butt joint forced guiding function is realized.
5. The spatial micro-impact butt joint vibration damping device according to claim 1, characterized in that: the driver adjusts the rigidity of the metal rubber block.
6. The spatial micro-impact butt joint vibration damping device according to claim 1, characterized in that: the feedback controller receives pressure data of the high-precision pressure sensor and processes the data, and meanwhile, the feedback controller issues an action instruction to control the action of the driver, so that closed-loop control is realized.
A space micro-impact butt joint vibration damping method is characterized in that: comprises the following steps:
step one, sequentially installing a high-precision pressure sensor, a metal rubber block and a driver on a butt joint;
step two, mounting a feedback controller on the interface;
thirdly, connecting the circuits of the high-precision pressure sensor, the driver and the feedback controller;
step four, extruding the high-precision pressure sensor by the contact surface in the butt joint process, and feeding back the pressure value to the feedback controller;
step five, the feedback controller sends an action signal to drive the driver to act, and the rigidity of the metal rubber block is adjusted in the tiny displacement;
step six, the active end and the passive end gradually approach to complete micro-impact butt joint;
step seven, the feedback controller sends out an action signal to the driver to move and compress the metal rubber block;
and step eight, after the butt joint is completed, the locking mechanism is unlocked, and the metal rubber block provides power for automatically separating the driving end from the driven end.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011521396.6A CN112727975B (en) | 2020-12-21 | 2020-12-21 | Space micro-impact butt joint vibration reduction device and method |
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| CN202011521396.6A CN112727975B (en) | 2020-12-21 | 2020-12-21 | Space micro-impact butt joint vibration reduction device and method |
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| CN112727975A true CN112727975A (en) | 2021-04-30 |
| CN112727975B CN112727975B (en) | 2022-12-23 |
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2020
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