CN102494842B - Satellite attitude conversion device - Google Patents
Satellite attitude conversion device Download PDFInfo
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- CN102494842B CN102494842B CN201110362474.7A CN201110362474A CN102494842B CN 102494842 B CN102494842 B CN 102494842B CN 201110362474 A CN201110362474 A CN 201110362474A CN 102494842 B CN102494842 B CN 102494842B
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Abstract
The invention relates to a satellite attitude conversion device which comprises an L beam, a right-angle bracket, a vertical tool and a counter weight, wherein the vertical tool is used for installing a satellite and can be used for carrying out X-direction and Y-direction barycenter tests and a Jz-direction rotational inertia test on the satellite; after the vertical tool equipped with the satellite is installed on a rotating mechanism on the L beam, a Z-direction barycenter test and Jx-direction, Jy-direction and Jx-y(theta)-direction rotational inertia tests on the satellite so that the satellite can rotate around a Z axle; the right-angle bracket is L-shaped, the bottom of the right-angle bracket is connected with the bottom of the vertical tool and the upper part of the right-angle bracket is connected with the rotating mechanism in the L beam; the L beam, the right-angle bracket and the vertical tool are assembled to be used for Jz-x(theta)-direction and Jz-y(theta)-direction rotational inertia tests so that the installed satellite can rotate around an X axle or a Y axle; and the counter block is used for carrying out weight balance on the satellite attitude conversion device. The satellite attitude conversion device has the advantages of light weight, simple structure and capabilities of hoisting and overturning.
Description
Technical field
The present invention relates to satellite mass characteristic test, particularly a kind of satellite attitude conversion device.
Background technology
In the development process of satellite, need to carry out mass property test to satellite, comprise barycenter measurement, rotation inerttia and counterweight compensation, make the mass property of whole star meet the demand of delivery and rail control system, and verify the calculated value of whole star mass property.
Barycenter test is used barycenter test board to test, and comprises the test of X, Y, tri-directions of Z, as measured not meet the demands, need carry out counterweight.As shown in Figure 1, when doing X, the test of Y-direction barycenter, need to use vertical frock that satellite is vertically tested to being placed on barycenter test board, as shown in Figure 2, when doing the test of Z-direction barycenter, need usage level frock satellite to be stood up to 90 ° of levels and test to being placed on barycenter test board.
Moment of inertia test is used moment of inertia test board to test, comprise Jx, Jy, Jz, Jx-y θ, Jz-x θ, Jz-y θ to test, wherein Jx-y θ represents that satellite rotates counterclockwise the moment of inertia at θ angle around Z axis, Jz-x θ represents that satellite rotates counterclockwise the moment of inertia at θ angle around Y-axis, and Jz-y θ represents that satellite rotates counterclockwise the moment of inertia at θ angle around X-axis.
As shown in Figure 3, Jz is to use vertical frock that satellite is vertically tested to being placed on moment of inertia test board to moment of inertia test; As shown in Figure 4, Jx, Jy, Jx-y θ are that usage level frock (I) is stood up 90 ° of levels by satellite and tested to being placed on moment of inertia test board to moment of inertia test, and during test, satellite need to rotate counterclockwise θ angle; As shown in Figure 5, Jz-x θ, Jz-y θ are that usage level frock (I), horizontal frock (II) are vertically tested satellite to being placed on moment of inertia test board to moment of inertia test, and during test, satellite need to rotate counterclockwise θ angle.
From the foregoing description to satellite mass characteristic test process, when doing mass property test, except the devices such as needs barycenter test board, moment of inertia test board, also need to be useful on the device that the attitude of satellite is adjusted, as as described in vertical frock, horizontal frock (I), horizontal frock (II) etc., the device of this type is also referred to as satellite attitude conversion device.Although also there is in the prior art satellite attitude conversion device, these devices all have complex structure, and weight is large, are difficult to do lifting and stand up, and are unfavorable for the defects such as operation.
Summary of the invention
The object of the invention is to overcome existing apparatus complex structure, weight is large, is difficult to do lifting and stands up, and is unfavorable for the defects such as operation, thereby a kind of satellite attitude conversion device of simple in structure, easy operating is provided.
To achieve these goals, the invention provides a kind of satellite attitude conversion device, comprise L beam, right angle rack, vertical frock and balancing weight; Wherein,
Described vertical frock is used for installing described satellite, can be X, the test of Y-direction barycenter and Jz to described satellite test to moment of inertia by described vertical frock;
Described L beam comprises agent structure, clutch disk, travel mechanism, rotating mechanism, support system and hoisting and overturning system; Described agent structure is L-shaped, and its inner hollow is used for installing described rotating mechanism, hoisting and overturning system, travel mechanism and balancing weight; Described clutch disk is positioned at described agent structure bottom, for described L beam is connected to outside barycenter test board or moment of inertia test board; Described travel mechanism is arranged in described agent structure near the position of bottom, and it is connected with described clutch disk, for described agent structure is seesawed on described clutch disk; Described support system is installed on the crossbeam of described agent structure, is used for supporting the bearing of described rotating mechanism; Described hoisting and overturning system is for lifting and stand up operation to satellite; The vertical frock that satellite is installed is installed to after the rotating mechanism on L beam, can does the test of Z-direction barycenter and Jx, Jy, Jx-y θ test to moment of inertia to satellite, can make satellite rotate around Z axis;
Described right angle rack becomes L shaped, and the bottom of described right angle rack is connected with the bottom of described vertical frock, and the top of described right angle rack is connected with the rotating mechanism in described L beam; After described L beam, right angle rack, vertical tooling combination, for Jz-x θ, Jz-y θ, to moment of inertia, test, can make the satellite being mounted thereon around X-axis or Y-axis rotation;
Described balancing weight is for carrying out counterweight to satellite attitude conversion device.
In technique scheme, described vertical frock by ZALSi9Mg monoblock cast, shape, and through surface chill anodization.
In technique scheme, the agent structure of described L beam is shaped by ZALSi9Mg casting.
In technique scheme, described travel mechanism is a set of ball screw assembly.
In technique scheme, described rotating mechanism comprises turning axle, bearing, rotating circular disk, turbine and worm mechanism.
In technique scheme, described support system comprises support bar and roller.
In technique scheme, described hoisting and overturning system comprises four lifting arms, two secondary single pole suspenders, and wherein said two width single pole suspenders are arranged on respectively the top and bottom of described L beam agent structure.
The invention has the advantages that:
That satellite attitude conversion device of the present invention has is lightweight, simple in structure, can lift the feature of standing up, and can meet the requirement of satellite mass characteristic test.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the invention will be further described, wherein:
Fig. 1 is X, Y-direction barycenter test schematic diagram;
Fig. 2 is Z-direction barycenter test schematic diagram;
Fig. 3 is that Jz tests schematic diagram to moment of inertia;
Fig. 4 is that Jx, Jy, Jx-y θ test schematic diagram to moment of inertia;
Fig. 5 is that Jz-x θ, Jz-y θ test to moment of inertia;
Fig. 6 is that satellite attitude conversion device is always schemed;
Fig. 7 is the subassembly schematic diagram of L beam, vertical frock;
Fig. 8 is vertical frock schematic diagram;
Fig. 9 is L beam schematic diagram;
Figure 10 is right angle rack schematic diagram.
Embodiment
With reference to figure 6, in one embodiment, satellite attitude conversion device of the present invention comprises L beam, right angle rack, vertical frock and balancing weight; Wherein, described vertical frock is tested to moment of inertia for X, the test of Y-direction barycenter and Jz; After described L beam, vertical tooling combination, for the test of Z-direction barycenter and Jx, Jy, Jx-y θ, to moment of inertia, test, and can make the satellite being mounted thereon rotate around Z axis; After described L beam, right angle rack, vertical tooling combination, for Jz-x θ, Jz-y θ, to moment of inertia, test, can make satellite around X-axis or Y-axis rotation; Described balancing weight, for satellite attitude conversion device is carried out to counterweight, is positioned on barycenter test board, moment of inertia test board central axis the barycenter of this device, reduces the impact of frock on satellite mass characteristic measuring accuracy.
Below the mechanism of these parts and process how to utilize these parts to carry out satellite mass characteristic test are described.
One, vertical frock
Vertical frock is tested to moment of inertia for X, the test of Y-direction barycenter and Jz, is the frock being connected with satellite in a whole set of posture converting device simultaneously.
For reducing the impact of vertical frock weight on satellite moment of inertia measuring accuracy, vertical frock needs light-weight design; For meeting the demand that supports satellite, vertical frock need to have enough rigidity and hardness.In order to meet above-mentioned requirements, the vertical frock in the present invention is an one-piece construction, it by ZALSi9Mg monoblock cast, shape, and through surface chill anodization.
For meeting the requirement of measuring accuracy, vertical frock should have higher flatness, the depth of parallelism and right alignment, and as shown in Figure 8, in one embodiment, the flatness on vertical frock surface is 0.1, and the depth of parallelism on up surface is 0.1, and the right alignment of through hole is 0.06.Vertical frock needs through dynamic and static balance correction after final shaping.
During use, vertical frock is connected with barycenter test board or moment of inertia test board by a register pin, then satellite is fixed in vertical frock, thereby carries out X, the test of Y-direction barycenter and Jz to the test of moment of inertia.
Two, L beam
The horizontal frock (I) of mentioning in background technology before the effect that L beam in the present invention plays is equivalent to, with reference to figure 7, it uses with after vertical frock assembling, for the test of Z-direction barycenter and Jx, Jy, Jx-y θ, to moment of inertia, tests, and can make satellite rotate around Z axis.
As shown in Figure 9, L beam comprises agent structure, clutch disk, travel mechanism, rotating mechanism, support system, hoisting and overturning system.Below the function of these parts, structure and mutual matching relationship are described further.
In order to reduce frock weight, L beam body junction forms L shaped, and it is shaped by ZALSi9Mg casting, and this inside configuration hollow, can be used to install the parts such as rotating mechanism, hoisting and overturning system, travel mechanism and balancing weight.
Clutch disk is positioned at the bottom of described L beam agent structure, and for L beam being connected to barycenter test board or moment of inertia test board, this connection realizes by a register pin, and it is shaped by wrought aluminium, has higher flatness, right alignment.
Travel mechanism is arranged in L beam agent structure near the position of bottom, it is connected with described clutch disk, be used for making L beam agent structure to seesaw on clutch disk, to regulate its position on barycenter test board, moment of inertia test board, thereby making centroid of satellite is a set of ball screw assembly, in the main body of test board central axis Shang， travel mechanism.
Rotating mechanism is positioned at the top of described L beam agent structure, and it realizes the attitude conversion of different angles for satellite is rotated around turning axle, and it is mainly comprised of turning axle, bearing, rotating circular disk, turbine and worm mechanism.
Described support system is installed on the crossbeam of L beam agent structure, is used for the annulus that is connected with satellite in support rotary mechanism, reduces the power that rotating mechanism bearing bears, and mainly support bar and roller, consists of.
Hoisting and overturning system is used for the lifting of satellite attitude conversion device and stands up operation, by four lifting arms, two secondary single pole suspenders, formed, two width single pole suspenders are arranged on respectively the top and bottom of described L beam agent structure, by double hook, lift, realize the lifting of this satellite attitude conversion device and stand up 90 ° of operations.
In use, first according to the design centroid position of satellite, centroid position when calculating satellite and being arranged on satellite attitude conversion device, regulates clutch disk position by the travel mechanism in L beam, makes dowel hole center on clutch disk and design of satellites barycenter on same vertical axis; Then vertical frock and L beam are connected and fixed, form a satellite attitude conversion device, integral hoisting is to barycenter test board, test the barycenter of this satellite attitude conversion device, in balancing weight I position, carry out counterweight, make the barycenter of satellite attitude conversion device, the dowel hole center on clutch disk, design of satellites barycenter, barycenter test board center on same vertical axis, record balance weight and position.Afterwards by satellite attitude conversion device integral hoisting to moment of inertia test board, test satellite attitude conversion device moment of inertia value.By above step, the debugging of satellite attitude conversion device oneself state is complete, can carry out the mass property test of satellite.
Counterweight on the complete satellite attitude conversion device of debugging is taken off, and lifting is stood up counterclockwise 90 °, and satellite lifting is upper fixing to this device, then lifts and stand up clockwise 90 °, now state and accompanying drawing 7 state consistencies.Then by this device and satellite integral hoisting to barycenter test board, counterweight is put back to original position, carries out barycenter test, by calculating the Z-direction center of mass values of satellite.Integral hoisting is carried out moment of inertia test to moment of inertia test board again, uses rotating mechanism rotation θ angle, by calculating Jx, Jy, the Jx-y θ moment of inertia value of satellite during test.
Three, right angle rack
The horizontal frock (II) that right angle rack role in the present invention is equivalent to mention in background technology, with reference to figure 6, right angle rack need to can be used with after L beam, the assembling of vertical frock, for Jz-x θ, Jz-y θ, to moment of inertia, tests, and can make satellite around X-axis or Y-axis rotation.
As shown in figure 10, it is L shaped that right angle rack becomes, and has a disk with mounting hole in L shaped bottom, for being connected with the bottom of vertical frock, also has a disk with mounting hole on L shaped top, for being connected with the rotating mechanism of L beam.Top at right angle rack also includes a fixed weight, and leaves moving counterweight fixed interface.The height of center of mass that need to consider satellite during right angle rack design, while making satellite be mounted on this satellite attitude conversion device, barycenter is positioned on rotation.Right angle rack agent structure is shaped by ZALSi9Mg casting.
In use, first press accompanying drawing 6 assembling right angle racks, L beam, vertical frock, form a satellite attitude conversion device, the travel mechanism by L beam regulates clutch disk position, makes dowel hole center on described clutch disk and design of satellites barycenter on same vertical axis.Then by the integral hoisting of this device to barycenter test board, test the barycenter of this device, in balancing weight I position, balancing weight II position carries out counterweight, need to use the rotating mechanism in L beam to make right angle frock rotation θ angle simultaneously, make the barycenter of this device, the dowel hole center on clutch disk, design of satellites barycenter, barycenter test board center on same vertical axis, record balance weight and position.Afterwards by the integral hoisting of this device to moment of inertia test board, test the moment of inertia value of this device; Use rotating mechanism to make right angle frock rotation θ angle, test moment of inertia value.By above step, the debugging of this satellite attitude conversion device oneself state is complete, has obtained necessary test value, can carry out the mass property test of satellite.
Counterweight on the complete satellite attitude conversion device of debugging is taken off, and lifting is to assembling station, and satellite lifting is upper fixing to this device, now state and accompanying drawing 6 state consistencies.Then this device and satellite integral hoisting are carried out to moment of inertia test to moment of inertia test board, counterweight is put back to original position, uses rotating mechanism rotation θ angle, by calculating the Jz-x θ moment of inertia value of satellite during test.Lifting satellite, makes satellite around vertical axes half-twist, is again connected with this device, carries out moment of inertia test, uses rotating mechanism rotation θ angle, by calculating the Jz-y θ moment of inertia value of satellite during test.
Satellite attitude conversion device of the present invention can make satellite rotate around turning axle by rotating mechanism, realizes attitude conversion; Can regulate the position of this device on test board by travel mechanism, make centroid of satellite on test board central axis; Can realize the lifting of this device and stand up operation by hoisting and overturning system, facilitate that the assembling of this device self, satellite are mounted to this device, this device is mounted to test board; Can by counterweight, regulate the centroid position of this device, make the barycenter of this device and the barycenter of satellite, test board center on same axis, reduce the impact of frock on satellite mass characteristic measuring accuracy.
Claims (7)
1. a satellite attitude conversion device, is characterized in that, comprises L beam, right angle rack, vertical frock and balancing weight; Wherein,
Described vertical frock is used for installing described satellite, is connected can does the test of X, Y-direction barycenter and Jz tests to moment of inertia to described satellite by described vertical frock with barycenter test board or moment of inertia test board;
Described L beam comprises agent structure, clutch disk, travel mechanism, rotating mechanism, support system and hoisting and overturning system; Described agent structure is L-shaped, and its inner hollow is used for installing described rotating mechanism, hoisting and overturning system, travel mechanism and balancing weight; Described clutch disk is positioned at described agent structure bottom, for described L beam is connected to outside barycenter test board or moment of inertia test board; Described travel mechanism is arranged in described agent structure near the position of bottom, and it is connected with described clutch disk, for making the side-to-side movement on described clutch disk of described agent structure; Described support system is installed on the crossbeam of described agent structure, is used for supporting the bearing of described rotating mechanism; Described hoisting and overturning system is for lifting and stand up operation to satellite; The vertical frock that satellite is installed is installed to after the rotating mechanism on L beam, can does the test of Z-direction barycenter and Jx, Jy, Jx-y θ test to moment of inertia to satellite, can make satellite rotate around Z axis;
Described right angle rack is L-shaped, and the bottom of described right angle rack is connected with the bottom of described vertical frock, and the top of described right angle rack is connected with the rotating mechanism in described L beam; After described L beam, right angle rack, vertical tooling combination, for Jz-x θ, Jz-y θ, to moment of inertia, test, can make the satellite being mounted thereon around X-axis or Y-axis rotation;
Described balancing weight is for carrying out counterweight to satellite attitude conversion device.
2. satellite attitude conversion device according to claim 1, is characterized in that, described vertical frock by ZALSi9Mg monoblock cast, shape, and through surface chill anodization.
3. satellite attitude conversion device according to claim 1, is characterized in that, the agent structure of described L beam is shaped by ZALSi9Mg casting.
4. satellite attitude conversion device according to claim 1, is characterized in that, described travel mechanism is a set of ball screw assembly.
5. satellite attitude conversion device according to claim 1, is characterized in that, described rotating mechanism comprises turning axle, bearing, rotating circular disk, turbine and worm mechanism.
6. satellite attitude conversion device according to claim 1, is characterized in that, described support system comprises support bar and roller.
7. satellite attitude conversion device according to claim 1, is characterized in that, described hoisting and overturning system comprises four lifting arms, two secondary single pole suspenders, and wherein said two width single pole suspenders are arranged on respectively the top and bottom of described L beam agent structure.
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