CN113044251A - Space fixed point rotating dynamics simulation device - Google Patents
Space fixed point rotating dynamics simulation device Download PDFInfo
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- CN113044251A CN113044251A CN202110342948.5A CN202110342948A CN113044251A CN 113044251 A CN113044251 A CN 113044251A CN 202110342948 A CN202110342948 A CN 202110342948A CN 113044251 A CN113044251 A CN 113044251A
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- 238000004088 simulation Methods 0.000 title claims abstract description 19
- 238000012360 testing method Methods 0.000 claims abstract description 21
- 238000005094 computer simulation Methods 0.000 claims description 6
- 229920003023 plastic Polymers 0.000 claims description 3
- 239000004033 plastic Substances 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 3
- 230000007717 exclusion Effects 0.000 abstract description 3
- BGPVFRJUHWVFKM-UHFFFAOYSA-N N1=C2C=CC=CC2=[N+]([O-])C1(CC1)CCC21N=C1C=CC=CC1=[N+]2[O-] Chemical compound N1=C2C=CC=CC2=[N+]([O-])C1(CC1)CCC21N=C1C=CC=CC1=[N+]2[O-] BGPVFRJUHWVFKM-UHFFFAOYSA-N 0.000 description 4
- 238000002474 experimental method Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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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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- Magnetic Bearings And Hydrostatic Bearings (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a space fixed-point rotation dynamics simulation device, and relates to the technical field of mechanics and machinery. The invention comprises a fixing mechanism, a functional mechanism, a supporting shaft mechanism and a bearing mechanism, wherein the supporting shaft mechanism is fixedly arranged above the fixing mechanism, the bearing mechanism is fixedly arranged above the supporting shaft mechanism, and the functional mechanism is fixedly arranged on one surface of the supporting shaft mechanism. According to the invention, through arranging the supporting shaft and the like, the opening at the end part of the shaft is provided with the thin air film formed by high-pressure air, the air floating platform is supported, the aircraft dynamics simulation can be realized, the attitude motion state of the aircraft in the space weightless environment can be simulated, and then the attitude control dynamics test can be carried out. Through setting up automatically controlled magnet etc. two magnets of design, can accomplish small volume and low weight, especially based on mutual exclusion magnetic force produces bearing structure clearance, replaces the gas film to hold up the platform, does not have gas to gush out, is fit for working in the vacuum tank.
Description
Technical Field
The invention belongs to the technical field of mechanics and machinery, and particularly relates to a space fixed-point rotation dynamics simulation device.
Background
Fixed point rotation of a rigid body in engineering mostly occurs in the occasions rotating around intersecting axes, such as a grinder, a radar antenna, a three-axis simulation platform, a mechanical arm and the like, and a motion equation can be established and solved by using a momentum moment theorem or an Euler kinetic equation. The approximate theory of the gyroscope can be used for researching the working principle, the principle error and the error compensation problem of the gyroscope and can also be used for researching the gyroscope effect in a rotor system. For free-moving projectiles, aircrafts, seaplanes, spacecraft and even celestial bodies, the fixed-point motion theory is an important tool for researching the motion around the mass center and the attitude, for example, after a cannon is popped out of a chamber, in order to prevent a tumbling bucket, the cannon is enabled to spin around a symmetry axis at a high speed, the stability condition of an inverted spinning gyro is used for determining the lower limit of the self-selection angular speed of the cannon, and rifling is designed according to the lower limit. If a point of the rigid body is always kept still in the motion process (the point may be on the rigid body or not), the motion is called fixed point rotation of the rigid body. The rigid body has three degrees of freedom when rotating at fixed points. The Euler angle is commonly used as a dynamic variable for describing fixed point rotation of a rigid body, and the fixed point rotation of the rigid body is the superposition of precession, nutation and autorotation. In a ground simulation experiment of attitude control of a space craft, attitude motion under a space weightless environment is often required to be simulated, and an experimental device mainly comprises a three-axis mechanical electric turntable and an air floating table, wherein the mechanical electric turntable is a test device capable of providing reference data and cannot simulate the physical dynamics process of the craft; the core device of air supporting platform is a ball bearing, and the tip trompil of axle forms the thin gas film by high-pressure gas, holds up the air supporting platform, can realize aircraft dynamics simulation, but in spacecraft attitude control ground analogue test, need establish special device and environment for the space environment that is equivalent to the attitude motion, for example: weightlessness, no air, high cost and high test cost.
Disclosure of Invention
The invention aims to provide a space fixed-point rotation dynamics simulation device, which solves the existing problems: however, in the spacecraft attitude control ground simulation test, special devices and environments need to be constructed for being equivalent to the space environment of attitude motion, such as: weightlessness, no air, high cost and high test cost.
In order to solve the technical problems, the invention is realized by the following technical scheme:
the invention relates to a space fixed-point rotation dynamics simulation device which comprises a fixing mechanism, a functional mechanism, a support shaft mechanism and a bearing mechanism, wherein the support shaft mechanism is fixedly arranged above the fixing mechanism, the bearing mechanism is fixedly arranged above the support shaft mechanism, and the functional mechanism is fixedly arranged on one surface of the support shaft mechanism.
Further, fixed establishment includes a plurality of supporting pad, base and support column, a plurality of supporting pad top fixed mounting has the base, base top fixed mounting has the support column.
Further, the support shaft mechanism comprises a support shaft, a permanent magnet and a sliding bearing, wherein the sliding bearing is fixedly mounted above the support shaft, and the permanent magnet is fixedly mounted on one surface of the sliding bearing.
Further, the functional mechanism comprises a south pole electric control magnet, a north pole electric control magnet and a device switch key, wherein the south pole electric control magnet is fixedly installed on one side far away from the device switch key, and the north pole electric control magnet is fixedly installed above the south pole electric control magnet.
Further, the bearing mechanism comprises a test piece bearing device, an attitude controller and an attitude sensor, wherein the attitude sensor is fixedly installed on one side far away from the attitude controller, and the test piece bearing device is fixedly installed above the attitude sensor.
Further, a supporting shaft is fixedly mounted above the fixing mechanism, a south pole electric control magnet is fixedly mounted on one surface of the supporting shaft, a sliding bearing is fixedly mounted above the south pole electric control magnet and is fixedly mounted on the other surface of the supporting shaft, a test piece bearing device is fixedly mounted on the sliding bearing, and a device switch key is fixedly mounted below the test piece bearing device.
Furthermore, the supporting pad, the base and the supporting column are all made of metal.
Further, the supporting pad is closely attached to the base, and the supporting pad is connected with the base in a welding mode.
Furthermore, the attitude controller and the switch key are in active connection with the base, and the attitude controller and the switch key are made of plastics.
The invention has the following beneficial effects:
1. according to the invention, through arranging the support shaft and the like, the opening at the end part of the shaft is provided with the thin air film formed by high-pressure air, and the air floating platform is supported, so that the aircraft dynamics simulation can be realized, the attitude motion state of the aircraft in a space weightless environment can be simulated, then the attitude control dynamics test can be carried out, the cost is low, and the friction force is eliminated.
2. The invention designs two magnets by arranging the electric control magnets and the like, can achieve small volume and low weight, particularly generates a bearing structure gap based on mutual repulsion magnetic force, replaces an air film to support a platform, has no air burst, is suitable for working in a vacuum tank, and improves the efficiency of the whole experiment.
Of course, it is not necessary for any product in which the invention is practiced to achieve all of the above-described advantages at the same time.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a partial schematic structural view of the present invention;
FIG. 3 is a schematic side view of the present invention.
In the drawings, the components represented by the respective reference numerals are listed below:
1. a support pad; 2. a base; 3. a support pillar; 4. a support shaft; 5. a south pole electrically controlled magnet; 6. a north pole electrically controlled magnet; 7. a permanent magnet; 8. a sliding bearing; 9. a test piece carrying device; 10. an attitude controller; 11. a device switch button; 12. and (4) an attitude sensor.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and 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.
Referring to fig. 1-3, the present invention is a dynamic simulation apparatus for fixed-point rotation in space, which includes a fixing mechanism, a functional mechanism, a supporting shaft mechanism and a bearing mechanism, wherein the supporting shaft mechanism is fixedly installed above the fixing mechanism, the bearing mechanism is fixedly installed above the supporting shaft mechanism, and the functional mechanism is fixedly installed on one side of the supporting shaft mechanism, so that the dynamic simulation apparatus has the advantages of simple structure, small volume, low processing cost and low test cost.
The fixing mechanism comprises a plurality of supporting pads 1, a base 2 and supporting columns 3, the base 2 is fixedly mounted above the plurality of supporting pads 1, the supporting columns 3 are fixedly mounted above the base 2, the organism is guaranteed not to shake in the experiment process, the structure of the organism is stabilized and strengthened, and the accuracy of the experiment result is improved. The supporting shaft mechanism comprises a supporting shaft 4, a permanent magnet 7 and a sliding bearing 8, the sliding bearing 8 is fixedly mounted above the supporting shaft 4, the permanent magnet 7 is fixedly mounted on one surface of the sliding bearing 8, a thin air film is formed by high-pressure air through an opening in the end of the shaft, the air bearing table is supported, aircraft dynamics simulation can be achieved, the attitude motion state of the aircraft in a space weightless environment is simulated, and then an attitude control dynamics test can be carried out. The functional mechanism comprises a south pole electric control magnet 5, a north pole electric control magnet 6 and a device switch key 11, wherein the south pole electric control magnet 5 is fixedly installed on one side of the device switch key 11, the north pole electric control magnet 6 is fixedly installed above the south pole electric control magnet 5, and the two magnets are designed, so that the small volume and the low weight can be realized, a bearing structure gap is generated based on mutual exclusion magnetic force, a gas film is replaced to support the platform, no gas is gushed out, and the vacuum tank vacuum pump is suitable for working in a vacuum tank. The bearing mechanism comprises a test piece bearing device 9, an attitude controller 10 and an attitude sensor 12, wherein the attitude sensor 12 is fixedly arranged on one side far away from the attitude controller 10, and the test piece bearing device 9 is fixedly arranged above the attitude sensor 12. The dynamic simulation device is characterized in that the supporting pad 1, the base 2 and the supporting column 3 are made of metal materials, the supporting pad 1 is tightly attached to the base 2, the supporting pad 1 is welded to the base 2, the attitude controller 10 and the switch key 11 are in active connection with the base 2, and the attitude controller 10 and the switch key 11 are made of plastic.
One specific application of this embodiment is: when the device is used, the sliding bearing 8 is fixedly installed above the supporting shaft 4, the permanent magnet 7 is fixedly installed on one surface of the sliding bearing 8, a thin air film is formed by high-pressure air through an opening at the end part of the shaft, the air floating platform is supported, aircraft dynamics simulation can be achieved, the attitude motion state of the aircraft in a space weightless environment can be simulated, and then an attitude control dynamics test can be carried out. Keep away from device switch button 11 one side fixed mounting have south pole automatically controlled magnet 5, the automatically controlled magnet of 5 tops fixed mounting of south pole have north pole automatically controlled magnet 6 of telling, design two magnets, can accomplish small volume and low weight, especially produce bearing structure clearance based on mutual exclusion magnetic force, replace the gas film to hold up the platform, do not have gas to gush out, be fit for working in the vacuum tank.
In the description herein, references to the description of "one embodiment," "an example," "a specific example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The preferred embodiments of the invention disclosed above are intended to be illustrative only. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (9)
1. The utility model provides a pivoted dynamics analogue means is fixed a point in space, includes fixed establishment, functional mechanism, back shaft mechanism and bears the weight of the mechanism, its characterized in that, fixed establishment top fixed mounting has back shaft mechanism, back shaft mechanism top fixed mounting bears the weight of the mechanism, just back shaft mechanism one side fixed mounting has functional mechanism.
2. The dynamic simulation device for fixed-point rotation in space according to claim 1, wherein the fixing mechanism comprises a plurality of supporting pads (1), a base (2), and supporting pillars (3), the base (2) is fixedly installed above the plurality of supporting pads (1), and the supporting pillars (3) are fixedly installed above the base (2).
3. A spatial fixed point rotation dynamics simulation device according to claim 1, wherein the supporting shaft mechanism comprises a supporting shaft (4), a permanent magnet (7) and a sliding bearing (8), the sliding bearing (8) is fixedly installed above the supporting shaft (4), and the permanent magnet (7) is fixedly installed on one side of the sliding bearing (8).
4. The spatial fixed-point rotation dynamics simulation device according to claim 1, wherein the functional mechanism comprises a south pole electrically controlled magnet (5), a north pole electrically controlled magnet (6) and a device switch button (11), the south pole electrically controlled magnet (5) is fixedly installed on the side away from the device switch button (11), and the north pole electrically controlled magnet (6) is fixedly installed above the south pole electrically controlled magnet (5).
5. The dynamic simulation device for the fixed-point rotation in space of claim 1, wherein the carrying mechanism comprises a test piece carrying device (9), an attitude controller (10) and an attitude sensor (12), the attitude sensor (12) is fixedly installed on the side far away from the attitude controller (10), and the test piece carrying device (9) is fixedly installed on the side far away from the attitude sensor (12).
6. The dynamic simulation device for fixed-point rotation in space according to claim 1, wherein a supporting shaft (4) is fixedly installed above the fixing mechanism, a south-pole electrically controlled magnet (5) is fixedly installed on one side of the supporting shaft (4), a sliding bearing (8) is fixedly installed above the side far away from the south-pole electrically controlled magnet (5), a test piece bearing device (9) is fixedly installed on the sliding bearing (8), and a device switch button (11) is fixedly installed below the side far away from the test piece bearing device (9).
7. A spatial fixed point rotation dynamics simulation apparatus according to claim 2, wherein the support pad (1), the base (2), and the support post (3) are made of metal.
8. A spatial fixed-point rotation dynamics simulation device according to claim 2, wherein the support pad (1) is tightly attached to the base (2), and the support pad (1) is welded to the base (2).
9. A spatial fixed point rotation dynamics simulation apparatus according to claim 5, wherein the attitude controller (10) and the switch button (11) are actively connected to the base (2), and the attitude controller (10) and the switch button (11) are made of plastic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110342948.5A CN113044251A (en) | 2021-03-30 | 2021-03-30 | Space fixed point rotating dynamics simulation device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110342948.5A CN113044251A (en) | 2021-03-30 | 2021-03-30 | Space fixed point rotating dynamics simulation device |
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| CN113044251A true CN113044251A (en) | 2021-06-29 |
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| CN202110342948.5A Pending CN113044251A (en) | 2021-03-30 | 2021-03-30 | Space fixed point rotating dynamics simulation device |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4908558A (en) * | 1988-04-22 | 1990-03-13 | Contraves Goerz Corporation | Spherical motion simulator |
| JP2007083895A (en) * | 2005-09-22 | 2007-04-05 | Mitsubishi Electric Corp | Spacecraft movement simulator |
| US20130125667A1 (en) * | 2010-07-14 | 2013-05-23 | University Of Florida Research Foundation, Inc. | System and method for assessing the performance of an attitude control system for small satellites |
| CN103496450A (en) * | 2013-09-28 | 2014-01-08 | 哈尔滨工业大学 | Micro-disturbance-torque environment simulation device suitable for spacecraft simulated test |
| CN106516182A (en) * | 2016-11-23 | 2017-03-22 | 上海卫星工程研究所 | Double five-degrees-of-freedom air bearing and master-slave non-contact double-super satellite ground principle verification system |
| CN110683080A (en) * | 2019-08-30 | 2020-01-14 | 北京航空航天大学 | Magnetic suspension ball bowl bearing device |
| CN211519904U (en) * | 2019-12-06 | 2020-09-18 | 天津航天机电设备研究所 | Magnetic suspension joint multi-degree-of-freedom dynamic control test system |
-
2021
- 2021-03-30 CN CN202110342948.5A patent/CN113044251A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4908558A (en) * | 1988-04-22 | 1990-03-13 | Contraves Goerz Corporation | Spherical motion simulator |
| JP2007083895A (en) * | 2005-09-22 | 2007-04-05 | Mitsubishi Electric Corp | Spacecraft movement simulator |
| US20130125667A1 (en) * | 2010-07-14 | 2013-05-23 | University Of Florida Research Foundation, Inc. | System and method for assessing the performance of an attitude control system for small satellites |
| CN103496450A (en) * | 2013-09-28 | 2014-01-08 | 哈尔滨工业大学 | Micro-disturbance-torque environment simulation device suitable for spacecraft simulated test |
| CN106516182A (en) * | 2016-11-23 | 2017-03-22 | 上海卫星工程研究所 | Double five-degrees-of-freedom air bearing and master-slave non-contact double-super satellite ground principle verification system |
| CN110683080A (en) * | 2019-08-30 | 2020-01-14 | 北京航空航天大学 | Magnetic suspension ball bowl bearing device |
| CN211519904U (en) * | 2019-12-06 | 2020-09-18 | 天津航天机电设备研究所 | Magnetic suspension joint multi-degree-of-freedom dynamic control test system |
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Application publication date: 20210629 |