CN103693213B - Magnetic tape type satellite mass center regulating mechanism - Google Patents
Magnetic tape type satellite mass center regulating mechanism Download PDFInfo
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- CN103693213B CN103693213B CN201310658861.4A CN201310658861A CN103693213B CN 103693213 B CN103693213 B CN 103693213B CN 201310658861 A CN201310658861 A CN 201310658861A CN 103693213 B CN103693213 B CN 103693213B
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Abstract
The invention discloses a magnetic tape type satellite mass center regulating mechanism, which comprises an electric motor, a coil spring, a mass tape, a first tape winding wheel, a second tape winding wheel, a base, an upper cover and an electric motor, wherein the electric motor and the coil spring are all fixedly arranged on the upper cover, the mass tape is positioned between the base and the upper cover, a first hole and a second hole are formed in the mass tape, the first tape winding wheel is positioned in the first hole, the second tape winding wheel is positioned in the second hole, and the mass tape is wound on the first belt winding wheel and the second belt winding wheel. The magnetic tape type satellite mass center regulating mechanism has the advantages that the satellite mass characteristic parameters can be precisely controlled, and the satellite mass center can be regulated according to the satellite flight tasks and the attitude and orbit control indexes.
Description
Technical field
The present invention relates to a kind of adjusting mechanism, particularly relate to a kind of magnetic tape type centroid of satellite adjusting mechanism.
Background technology
Satellite mass characteristic comprises barycenter, quality, rotor inertia and the product of inertia etc., it is the important parameter of satellite general design, directly having influence on dynamics and the rail control characteristic of satellite, is also simultaneously the important basis of the mechanical test of satellite, satellite launch, the aspect such as in orbit.
Centroid of satellite is the importance of satellite mass characteristic, relevant with the quality of each unit on star, parts and distributing position, calculates by following formula (1):
Time on the ground, because design misaligns misaligning of causing with making and installation precision, all can cause the skew of centroid of satellite.When satellite flies in-orbit, due to consumption of fuel, structural distortion, the reasons such as gravity release can cause the drift of centroid of satellite.
Be subject to gravitational main arrow and main carpenter square when satellite flies in-orbit relevant with satellite mass characteristic, centroid position can affect universal gravitation square.According to Dynamical Attitude Equations, the change of centroid of satellite and the change of gravitation square all can change the state of kinematic motion of satellite.Satellite attitude determines it is that barycenter off-design position causes attitude determination error with the barycenter of satellite to geocentric inertial coordinate system right ascension declination location.The parameters such as the PID in attitude controller algorithm are relevant with satellite mass characteristic, and centroid motion can cause controller output with the control torque signal of error.The output torque of flywheel is relevant with satellite mass characteristic with space environment moment, and the gentle kinetic moment of solar light pressure moment in environmental torque is relevant with centroid position, and therefore centroid motion causes flywheel output torque error.Thruster moment take centroid position as benchmark, and centroid motion causes each single shaft thruster moment all to produce error along three direction of principal axis.
In a word, barycenter deviation can reduce satellite attitude precision, increases the appearance control energy and propellant expenditure, and causes attitude to determine to produce deviation with Controller gain variations parameter, thus makes satellite attitude produce systematic error.
Summary of the invention
Technical matters to be solved by this invention is to provide a kind of magnetic tape type centroid of satellite adjusting mechanism, and it controls satellite mass characteristic parameter exactly, according to aerial mission and the rail control index request of satellite, adjusts centroid of satellite.
The present invention solves above-mentioned technical matters by following technical proposals: a kind of magnetic tape type centroid of satellite adjusting mechanism, it is characterized in that, it comprises electrical motor, wind spring, quality band, the first strip winding wheel, the second strip winding wheel, base, upper cover, electrical motor, wind spring are all fixed on and cover, quality band is between base and upper cover, quality band is provided with the first hole and the second hole, first strip winding wheel is positioned at the first hole, second strip winding wheel is positioned at the second hole, and quality band is wound around on the first strip winding wheel, on the second strip winding wheel.
Preferably, described firm banking and a plate nut are fixed, and a screw is fixed by the 3rd hole and plate nut.
Positive progressive effect of the present invention is: the present invention controls satellite mass characteristic parameter exactly, according to aerial mission and the rail control index request of satellite, adjusts centroid of satellite.
Accompanying drawing explanation
Fig. 1 is the decomposition texture schematic diagram of magnetic tape type centroid of satellite adjusting mechanism of the present invention.
Plan sketch when Fig. 2 is magnetic tape type centroid of satellite adjusting mechanism of the present invention assembling.
Fig. 3 is the structural representation after magnetic tape type centroid of satellite adjusting mechanism of the present invention assembling.
Detailed description of the invention
Present pre-ferred embodiments is provided, to describe technical scheme of the present invention in detail below in conjunction with accompanying drawing.
As shown in Figure 1 to Figure 3, magnetic tape type centroid of satellite adjusting mechanism of the present invention comprises electrical motor 1, wind spring 2, quality band 3, first strip winding wheel 4, second strip winding wheel 5, base 8, upper cover 9, electrical motor 1, wind spring 2 are all fixed on upper cover 9, quality band 3 is between base 8 and upper cover 9, quality band 3 is provided with the first hole 31 and the second hole 32, first strip winding wheel 4 is positioned at the first hole 31, second strip winding wheel 5 and is positioned at the second hole 32, and quality band 3 is wound around on the first strip winding wheel 4, on the second strip winding wheel 5.Firm banking 8 and a plate nut 7 are fixed, and a screw 6 is fixed with plate nut 7.
Electrical motor 1 rotarily drives the first strip winding wheel 4 and rotates, thus drives quality band 3, and quality band 3 drives the second strip winding wheel 5, second strip winding wheel 5 to roll tightly wind spring 2.It is driving wheels that the first strip winding be connected with electrical motor 1 takes turns 4, and it is flower wheels that the second strip winding be connected with wind spring 2 takes turns 5.Wind spring 2 band 3 of can ensuring the quality of products is in tensioning state all the time.
The principle of work of magnetic tape type centroid of satellite adjusting mechanism of the present invention: electrical motor is according to input instruction forward or reverse, electrical motor and driving wheel are assembled together, electrical motor rotates thus drives driving wheel to rotate, quality band is taken turns at the first strip winding, the second strip winding is taken turns and is wound around, side belt wheel improves quality to be with increases (number of turns that namely quality band is wound around on this is taken turns adds), and opposite side belt wheel is improved quality to be with and reduced (number of turns that namely quality band is wound around on this is taken turns decreases).Taken turns the change of band of improving quality by the first strip winding wheel, the second strip winding, realize the redistribution of quality in both sides, thus reach the object of adjustment barycenter.For ensureing that, under below-G conditions, motion is delivered to flower wheel from driving wheel by quality band smoothly, quality band must be allowed to be in tensioning state all the time, so assemble wind spring on the driven wheel.The density of quality band, width and thickness can careful design, and turning to of belt wheel can accurately control with angular transposition, therefore, it is possible to carry out high precision adjustment to barycenter.
Magnetic tape type centroid of satellite adjusting mechanism of the present invention is a kind of dynamic conditioning mode, and barycenter can in certain interval change.Magnetic tape type centroid of satellite adjusting mechanism of the present invention adopts a kind of high-precision adjustment mode, and the thickness of quality band, width, density can careful design, and turning to of belt wheel can accurately control with angular transposition, realizes the high precision adjustment of barycenter.The present invention not only can use when ground test, the more important thing is and can be used in-orbit by programming control in telecommand or star.The present invention not only changes the position of barycenter in face, and can not have an impact by centroid position outside opposite, combinationally uses the independence that can realize barycenter three-dimensional coordinate adjust by multiple stage.Magnetic tape type centroid of satellite adjusting mechanism of the present invention is compact, reasonable, and whole mechanism profile is approximately flat cuboid, and geometric properties rule, provides good attachment face, be convenient to layout in celestial body.Move outside the face that the present invention adopts base and upper cover to carry out limiting mechanism, and utilize wind spring tensioning quality band, reduce the impact of mechanical vibration and impact with this, improve functional reliability.
The present invention is different from traditional mode at satellite ad-hoc location configuration quality block, and quality band, by electric machine rotation, belt wheel is wound around, realizes the redistribution of quality by magnetic tape type barycenter adjusting mechanism, reaches the object of adjustment barycenter.
The present invention due to the thickness of quality band, width and density can careful design, the turning to of belt wheel, angular transposition can accurately control, and therefore magnetic tape type centroid of satellite adjusting mechanism can carry out high precision adjustment according to mass property control overflow to barycenter.The present invention not only can use in the satellite ground test set-up stage, can also be used in-orbit by programming control in telecommand or star.The present invention only changes the position of barycenter in face, and can not have an impact by centroid position outside opposite, thus realizes adjusting the independence of barycenter three-dimensional coordinate.
Those skilled in the art can carry out various remodeling and change to the present invention.Therefore, present invention covers the various remodeling in the scope falling into appending claims and equivalent thereof and change.
Claims (2)
1. a magnetic tape type centroid of satellite adjusting mechanism, it is characterized in that, it comprises electrical motor, wind spring, quality band, the first strip winding wheel, the second strip winding wheel, base, upper cover, electrical motor, wind spring are all fixed on and cover, quality band is between base and upper cover, and quality band is provided with the first hole and the second hole, and the first strip winding wheel is positioned at the first hole, second strip winding wheel is positioned at the second hole, and quality band is wound around on the first strip winding wheel, on the second strip winding wheel.
2. magnetic tape type centroid of satellite adjusting mechanism as claimed in claim 1, it is characterized in that, described firm banking and a plate nut are fixed, and a screw is fixed by the 3rd hole and plate nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310658861.4A CN103693213B (en) | 2013-12-06 | 2013-12-06 | Magnetic tape type satellite mass center regulating mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310658861.4A CN103693213B (en) | 2013-12-06 | 2013-12-06 | Magnetic tape type satellite mass center regulating mechanism |
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| CN103693213A CN103693213A (en) | 2014-04-02 |
| CN103693213B true CN103693213B (en) | 2015-07-15 |
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| CN201310658861.4A Active CN103693213B (en) | 2013-12-06 | 2013-12-06 | Magnetic tape type satellite mass center regulating mechanism |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106249749B (en) * | 2016-09-08 | 2019-01-18 | 上海卫星工程研究所 | The non-contact double super satellite platform Moving Variable inertia attitude control systems of principal and subordinate |
| CN106542114B (en) * | 2016-11-03 | 2019-05-03 | 上海卫星工程研究所 | Lateral mass center high-precision ensuring method of the parallel connection tiling tank satellite in the AIT stage |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1760617A (en) * | 2005-11-16 | 2006-04-19 | 邢台钢铁有限责任公司 | Method for adjusting center of gravity of cooler trough, and reduction of wandering and gnawing track of cartwheel |
| CN102616355A (en) * | 2012-04-06 | 2012-08-01 | 西北工业大学 | Centroid-variable adjustment device for multi-load remote autonomous underwater vehicle |
| CN103235598A (en) * | 2013-05-14 | 2013-08-07 | 北京理工大学 | Method for regulating propeller direction to point to combined-body spacecraft centroid |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7967257B2 (en) * | 2007-10-30 | 2011-06-28 | Raytheon Company | Space object deployment system and method |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1760617A (en) * | 2005-11-16 | 2006-04-19 | 邢台钢铁有限责任公司 | Method for adjusting center of gravity of cooler trough, and reduction of wandering and gnawing track of cartwheel |
| CN102616355A (en) * | 2012-04-06 | 2012-08-01 | 西北工业大学 | Centroid-variable adjustment device for multi-load remote autonomous underwater vehicle |
| CN103235598A (en) * | 2013-05-14 | 2013-08-07 | 北京理工大学 | Method for regulating propeller direction to point to combined-body spacecraft centroid |
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