CN105628303B - Cube centroid of satellite measurement method - Google Patents
Cube centroid of satellite measurement method Download PDFInfo
- Publication number
- CN105628303B CN105628303B CN201510997940.7A CN201510997940A CN105628303B CN 105628303 B CN105628303 B CN 105628303B CN 201510997940 A CN201510997940 A CN 201510997940A CN 105628303 B CN105628303 B CN 105628303B
- Authority
- CN
- China
- Prior art keywords
- cube
- satellite
- centroid
- measurement method
- reading
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/12—Static balancing; Determining position of centre of gravity
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Balance (AREA)
Abstract
The invention discloses a kind of cube centroid of satellite measurement methods, and the setting of the four direction of a side on the outside of the main structural frame of cube satellite and a bottom surface surrounds rectangular support respectively first, and in support bottom setting electronic scale to read reading；Then the sum of two electronic scales ipsilateral on the same face reading is read with the electronic scale of the other side two and multilevel iudge mass center is biased to direction；Finally according to principle of moment balance, the specific location of mass center is determined；Measurement method operation of the invention is easy, and required equipment is also extremely simple, therefore measurement cost is cheap；And measurement method adaptability of the invention is high, cube star suitable for any unit.
Description
Technical field
The invention belongs to a cube star technical field, especially a kind of cube centroid of satellite measurement method.
Background technique
In recent years, along with the fast development of the science and technology such as communication, photoelectric cell, material, sensor, applicating fluid, cube
The development of star technology is substantially speeded up, and is remotely measured using cube star, tests and be possibly realized.Cheap cost has promoted world's model
Cube star research plan emerges in large numbers in enclosing.
Centroid of satellite has a significant impact to attitude of satellite tool, and centroid motion will cause the fluctuation of celestial body posture, celestial body posture wave
The dynamic influence for mainly having several aspects to satellite:
1, attitude of satellite precision is reduced, to reduce military service quality；
2, when gesture stability is Active control, additional fluctuation increases attitude control energy consumption；
3, when posture executing agency uses flywheel mechanism, fluctuation will make flywheel bearing bear periodical dynamic loading, reduce
The runnability of support and service life；
4, when attitude control actuator is jet thrust device, when fluctuation will increase thruster on-off times and open
Between, it is additional to increase working medium consumption, to reduce satellite service life.
Therefore, the position that centroid of satellite can be all paid special attention in satellite master-plan carries out necessary counterweight process, keeps away
Exempt from centroid motion and has a negative impact to satellite.Cube design of satellites specification (Cubesat Design
Specifications) clear stipulaties cube star mass center need to be fallen within 2 centimetres of spheres of centroid.And the premise of satellite counterweight
Work is exactly the measurement of mass center.
Patent of invention 201410691004.9 discloses a kind of centroid measurement method: outstanding with object under free suspension state
Line crosses the basic principle of center of gravity, passes through the measurement to suspension wire, testee geometric space shape under different free suspension states
And computer modeling, it is fitted testee contour model, center of gravity plumb line intersection point is resolved, finds object position of centre of gravity.This method
It is usually used in the centroid measurement of the non-homogeneous irregular large satellite of shape, but cube star shape rule, and outer dimension is small, is difficult to be arranged
Hitch point, therefore unusable this method carries out centroid measurement.
Summary of the invention
Simple, the high cube centroid of satellite measurement method of measurement accuracy is used the purpose of the present invention is to provide a kind of.
The technical solution for realizing the aim of the invention is as follows:
A kind of cube centroid of satellite measurement method, comprising the following steps:
Step 1: four sides of the side and a bottom surface on the outside of the main structural frame of cube satellite respectively
Rectangular support is surrounded to setting, and in support bottom setting electronic scale to read reading；
Step 2: by two electronic scale readings in sum and the other side of two electronic scales ipsilateral on the same face reading and compared with
Judge that mass center is biased to direction；
Step 3: according to principle of moment balance, the specific location of mass center is determined.
Compared with prior art, the present invention its remarkable advantage:
(1) cube centroid of satellite measurement method of the invention operation is easy, and required equipment is also extremely simple, therefore is surveyed
It measures low in cost.
(2) cube centroid of satellite measurement method adaptability of the invention is high, cube star suitable for any unit.
Present invention is further described in detail with reference to the accompanying drawing.
Detailed description of the invention
Fig. 1 is that the coordinate system of cube centroid of satellite measurement method of the present invention determines figure.
Fig. 2 is the schematic diagram of aperture on cube centroid of satellite measurement method main structural frame of the present invention.
Fig. 3 is the used structural plan of cube centroid of satellite measurement method of the present invention.
Fig. 4 is the used structural plan of cube centroid of satellite measurement method of the present invention.
Specific embodiment
In conjunction with FIG. 1 to FIG. 4:
A kind of cube centroid of satellite measurement method of the present invention, comprising the following steps:
Step 1: four sides of the side and a bottom surface on the outside of the main structural frame of cube satellite respectively
Rectangular support is surrounded to setting, and in support bottom setting electronic scale to read reading；
Step 2: by two electronic scale readings in sum and the other side of two electronic scales ipsilateral on the same face reading and compared with
Judge that mass center is biased to direction；
Step 3: according to principle of moment balance, the specific location of mass center is determined.
Wherein, step 1 the following steps are included:
Step 1: being respectively set and enclose on the side and a bottom surface on the outside of the main structural frame of cube satellite
Four rectangular holes；
Step 2: supporting four holes on one of face with four thimbles respectively；
Step 3: electronic scale being set simultaneously respectively in the bottom of each thimble, and reads electronic scale reading.
Embodiment:
A kind of cube centroid of satellite measurement method is specific as follows:
(1) as shown in Figure 1, the heading for setting up cube satellite is the direction+x, the opposite direction of flight is the direction-x, is stood
Cube satellite is+z to day direction, and direction is-z over the ground, determines+y and the direction-y by screw law；
(2) as shown in Fig. 2, the direction+y on the outside of the main structural frame of cube satellite pair face and the direction-x institute
Pair face on four holes for surrounding rectangle are respectively set；
(3) four holes on one of face are supported with four thimbles respectively；
(4) electronic scale is set simultaneously respectively in the bottom of each thimble, and reads electronic scale reading；
(5) centroid position is set as (x0, y0, z0), pass through the structure arrangement obtained direction support+y institutes as shown in Figure 3 more
Pair face obtain four electronic scales reading, if the reading of four electronic scales is respectively m1、m2、m3、m4, then the gross mass m of cube star
For m=m1+m2+m3+m4；If m1、m2In-x to m3、m4In+x to, by comparing m1+m2 and m3+m4 size i.e. can determine whether
Mass center x-axis deviation,
If m1+m2> m3+m4, then x0Deviation-x；
If m1+m2< m3+m4, then x0Deviation+x.
According to principle of moment balance, square is taken to oz axis in plane xoz, x can be obtained0Are as follows:
As mass center deviation-x, above formula takes positive sign；
As mass center deviation+x, above formula takes negative sign.
(6) by the structure arrangement obtained directions support-x as shown in Figure 4 more pair face obtain four electronics reads
Number, using the method for such as step (5), takes square to can determine y axis oy, oz respectively0、z0。
Claims (1)
1. a kind of cube centroid of satellite measurement method, it is characterised in that: the following steps are included:
Step (1): the heading for setting up cube satellite is the direction+x, and the opposite direction of flight is the direction-x, cube satellite
Be+z to day direction, direction is-z over the ground, passes through screw law and determines+y and the direction-y；
Step (2): the direction+y on the outside of the main structural frame of cube satellite pair face and the direction-x pair face on
Four holes for surrounding rectangle are respectively set；
Step (3): four holes on one of face are supported with four thimbles respectively；
Step (4): electronic scale is set simultaneously respectively in the bottom of each thimble, and reads electronic scale reading；
Step (5): centroid position is set as (x0, y0, z0), the direction support+y pair face obtain four electronic scales reading and be respectively
m1、m2、m3、m4, then the gross mass m of cube star is m=m1+m2+m3+m4If m1、m2In-x to m3、m4In+x to, according to
Principle of moment balance takes square to oz axis in plane xoz, can obtain x0Are as follows:
If m1+m2> m3+m4, then x0Deviation-x, above formula take positive sign, if m1+m2< m3+m4, then x0Deviation+x, above formula take negative sign；
Step (6): the direction-x that is supported by the way of step (3) and (4) pair face four electronic scales reading, use
The method of step (5) takes square to determine z axis oy, oz respectively0、y0。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510997940.7A CN105628303B (en) | 2015-12-25 | 2015-12-25 | Cube centroid of satellite measurement method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510997940.7A CN105628303B (en) | 2015-12-25 | 2015-12-25 | Cube centroid of satellite measurement method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105628303A CN105628303A (en) | 2016-06-01 |
| CN105628303B true CN105628303B (en) | 2019-11-15 |
Family
ID=56043442
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510997940.7A Active CN105628303B (en) | 2015-12-25 | 2015-12-25 | Cube centroid of satellite measurement method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105628303B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110146319B (en) * | 2019-05-30 | 2021-07-09 | 西北工业大学 | Cube-carried structure health monitoring experimental device and method |
| CN110595687B (en) * | 2019-08-15 | 2021-01-26 | 南京理工大学 | Cube star two-dimensional centroid adjusting method |
| CN111664995B (en) * | 2020-07-08 | 2022-04-05 | 福州大学 | Satellite three-dimensional rotation quantity testing device and testing method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009031218A (en) * | 2007-07-30 | 2009-02-12 | Katsuzo Kawanishi | Method for calculating center-of-gravity position, lifting/weighing device, and weight acquisition method |
| CN101450767A (en) * | 2007-12-05 | 2009-06-10 | 中国科学院自动化研究所 | Polar coordinate mode horizontal automatic regulating cargo sling and method |
| CN102941928A (en) * | 2012-11-27 | 2013-02-27 | 中国人民解放军国防科学技术大学 | Method for optimizing error of micro-nano satellite separation angular velocity |
| CN103868648A (en) * | 2014-04-01 | 2014-06-18 | 哈尔滨工业大学 | Barycenter measuring method for three-axis air floatation simulation experiment platform |
| CN203949788U (en) * | 2014-01-17 | 2014-11-19 | 北京航天试验技术研究所 | The device that a kind of satellite or rocket Upper Stage propulsion subsystem barycenter are measured and weighed |
| CN104163251A (en) * | 2014-08-06 | 2014-11-26 | 上海卫星工程研究所 | Eight-rod connecting type non-contact satellite platform load pose adjusting device and method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104142209B (en) * | 2013-05-08 | 2016-12-28 | 上海微电子装备有限公司 | Mass cg measurement apparatus and method |
-
2015
- 2015-12-25 CN CN201510997940.7A patent/CN105628303B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009031218A (en) * | 2007-07-30 | 2009-02-12 | Katsuzo Kawanishi | Method for calculating center-of-gravity position, lifting/weighing device, and weight acquisition method |
| CN101450767A (en) * | 2007-12-05 | 2009-06-10 | 中国科学院自动化研究所 | Polar coordinate mode horizontal automatic regulating cargo sling and method |
| CN102941928A (en) * | 2012-11-27 | 2013-02-27 | 中国人民解放军国防科学技术大学 | Method for optimizing error of micro-nano satellite separation angular velocity |
| CN203949788U (en) * | 2014-01-17 | 2014-11-19 | 北京航天试验技术研究所 | The device that a kind of satellite or rocket Upper Stage propulsion subsystem barycenter are measured and weighed |
| CN103868648A (en) * | 2014-04-01 | 2014-06-18 | 哈尔滨工业大学 | Barycenter measuring method for three-axis air floatation simulation experiment platform |
| CN104163251A (en) * | 2014-08-06 | 2014-11-26 | 上海卫星工程研究所 | Eight-rod connecting type non-contact satellite platform load pose adjusting device and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105628303A (en) | 2016-06-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103018066B (en) | The autonomous GNC semi-physical simulation test system of survey of deep space small feature loss attaching process | |
| CN105628303B (en) | Cube centroid of satellite measurement method | |
| CN104266649B (en) | Method based on gyrotheodolite measuring basis prism square attitude angle | |
| CN108225370B (en) | Data fusion and calculation method of motion attitude sensor | |
| CN105091746B (en) | The space coordinates scaling method docked applied to spacecraft bay section ground | |
| CN102155887A (en) | Method for measuring flexibility of mass centre | |
| CN102929295A (en) | Automatic leveling control device based on single chip microcomputer (SCM) | |
| CN106768634B (en) | A kind of submarine navigation device centre of buoyancy measurement method | |
| CN109459121A (en) | A kind of bird weight center of gravity measurement method | |
| CN106767671B (en) | Geologic structure face occurrence calculation method based on three-dimensional electronic compass | |
| CN103868648A (en) | Barycenter measuring method for three-axis air floatation simulation experiment platform | |
| CN108021138B (en) | Simplified design method of geomagnetic field model | |
| CN104931046A (en) | Miniature inertial measurement system | |
| CN106500940A (en) | Six-degree of freedom vibration acceleration measurement device | |
| CN202471077U (en) | Mining digital geologic compass | |
| CN109633541B (en) | Magnetic source positioning device and magnetic source positioning method | |
| CN104931047A (en) | Micro-inertial measurement system based on voltage-stabilizing circuit | |
| CN105738964A (en) | Marine gravimeter table body stabilization device and method | |
| CN104931053A (en) | Micro-inertial measurement system with power supply optimization function | |
| CN105890831B (en) | The measuring device and its measurement method of high precision control moment gyroscopic couple output | |
| CN104197931A (en) | Three-dimensional display device of miniature navigation attitude system based on FPGA (Field Programmable Gate Array) | |
| CN105758422B (en) | A kind of test method of integration type closed-loop fiber optic gyroscope | |
| CN106840241A (en) | The calibration method and calibration system of a kind of axle sensor products of built-in MEMS six | |
| CN107255480B (en) | Light cavity-divided high-strength optical fiber inertial measurement unit for carrier rocket | |
| CN111829704B (en) | Spacecraft residual torque residual angular momentum measurement calibration device and method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |