CN111959834A - Satellite semi-physical simulation test bed - Google Patents
Satellite semi-physical simulation test bed Download PDFInfo
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- CN111959834A CN111959834A CN202010905656.3A CN202010905656A CN111959834A CN 111959834 A CN111959834 A CN 111959834A CN 202010905656 A CN202010905656 A CN 202010905656A CN 111959834 A CN111959834 A CN 111959834A
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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
Abstract
The invention discloses a satellite semi-physical simulation test bed, which comprises: a test table; the test table comprises: a frame and at least two layers of table tops; each desktop is arranged on the frame and used for fixing a stand-alone unit to be tested and/or a testing device of the stand-alone unit to be tested; all the table tops are connected through wires so that the electric potentials of all the table tops are equal. The invention effectively saves the test field and provides a reliable equipotential environment for the stand-alone to be tested, and can construct any installation position and installation direction for the stand-alone to be tested so as to simulate the whole satellite structure environment; the invention can also measure the polarity of the sensitive angular velocity single machine and the rotation actuating mechanism single machine and make the polarity measurement more convenient.
Description
Technical Field
The invention relates to the technical field of satellite attitude and orbit control subsystem simulation tests, in particular to a multifunctional satellite semi-physical simulation test bed for simulating a whole satellite structure.
Background
The satellite semi-physical simulation test bed provides a necessary hardware test environment for the semi-physical simulation test of the satellite attitude and orbit control subsystem. Through the satellite semi-physical simulation test bed, the polarity test of each single machine of the attitude and orbit control subsystem and the interface butt joint among the single machines, the open-loop performance test, the closed-loop performance test and other function tests of the attitude and orbit control subsystem can be carried out, and meanwhile, part of whole satellite test items can be verified.
However, the traditional satellite semi-physical simulation test bed has certain limitations. For example, in a traditional satellite semi-physical simulation test bed, each single machine is tiled on a plurality of test tables, so that a test field cannot be effectively utilized, and different test tables cannot provide a reliable equipotential environment for different single machines. For some situations that the single computers interfere with each other due to factors such as installation distance, installation position or installation direction when the whole satellite is arranged, the conventional satellite semi-physical simulation test bed cannot verify whether interference or interference magnitude exists between the single computers in advance. When the polarity of the sensitive angular velocity single machine is measured, the complexity of the test process is increased by means of large-scale special equipment such as a rotary table, or the single machine is manually rotated, so that the risk of damage to the single machine caused by the rotation process is increased. The traditional satellite semi-physical simulation test bed cannot intuitively measure the polarity of a single machine (such as a reaction flywheel) of a rotation executing mechanism; there is no general fixing method for a single machine (such as a control moment gyro) which generates moment to cause position movement when working; prevent that static bracelet earthing device exposes and install in the test bench, have the hook risk.
Disclosure of Invention
The invention aims to provide a satellite semi-physical simulation test bed, which overcomes the limitation of the traditional satellite semi-physical simulation test bed and enables the test of each single machine of an attitude and orbit control subsystem to be more convenient and reliable.
In order to achieve the purpose, the invention is realized by the following technical scheme:
a satellite semi-physical simulation test bed comprises: a test table; the test table comprises: a frame and at least two layers of table tops.
Each desktop is arranged on the framework and used for fixing the stand-alone unit to be tested and/or the testing device of the stand-alone unit to be tested.
All the table tops are connected through wires so that the electric potentials of all the table tops are equal.
Preferably, each desktop is provided with a plurality of first through holes, and the stand-alone unit to be tested and/or the test device are/is fixed on each desktop through the first through holes;
all the table tops are arranged at intervals in the vertical direction, and any two table tops are parallel;
the frame is made of aluminum alloy; all the table tops are made of aluminum.
Preferably, the satellite semi-physical simulation test bed further includes: a honeycomb panel assembly; the honeycomb plate assembly is arranged on any one desktop and used for fixing the stand-alone unit to be tested;
the honeycomb panel assembly comprises a plurality of honeycomb panels, wherein any two honeycomb panels are fixedly connected at any angle, so that the stand-alone to be tested is fixed on the desktop at any angle to simulate the whole satellite structure environment.
Preferably, each of the honeycomb panels comprises: a panel and a mounting plate connected at an angle to one end of the panel;
the panel is provided with a plurality of second through holes, and the stand-alone unit to be tested is fixed on the panel through the second through holes;
the mounting panel is equipped with the first through-hole groove of a plurality of, just the mounting panel passes through first through-hole groove with arbitrary the desktop carries out fixed connection.
Preferably, the satellite semi-physical simulation test bed further includes: briquetting; the briquette comprises: the pressing block comprises a pressing block body, a first fixing piece and a second fixing piece;
a third through hole and a second through hole groove are formed in the pressing block body; the utility model discloses a honeycomb board, including the honeycomb board, the mounting panel crimping of briquetting body, first mounting runs through the third through-hole will the second end of briquetting body with the desktop butt, the second mounting runs through the second through-hole groove will the briquetting body with the desktop carries out fixed connection, in order will the honeycomb board is fixed in arbitrary angle arbitrary on the desktop, and then will the unit that awaits measuring is fixed in arbitrary with arbitrary angle on the desktop to simulate whole star structure environment.
Preferably, the testing device of the stand-alone device under test comprises: the three-degree-of-freedom test desk is arranged on any desktop and used for fixing the sensitive angular velocity single machine in the single machine to be tested so as to measure the polarity of the sensitive angular velocity single machine;
and the single-degree-of-freedom test bench is arranged on any one of the desktops and is used for fixing the single rotating execution mechanism in the single machine to be tested so as to measure the polarity of the single rotating execution mechanism.
Preferably, the three-degree-of-freedom test bench comprises: the table comprises a first table top, a second table top, a third table top and a first base;
the first table top is arranged on the second table top and is connected with the second table top through a first hinge; the first table top is provided with a plurality of fourth through holes, and the sensitive angular velocity single machine is fixed on the first table top through the fourth through holes;
the second table top is arranged on the third table top and is connected with the third table top through a second hinge, and the vector direction of the second hinge is orthogonal to the vector direction of the first hinge;
the third table top is movably connected with the first base through a first bearing;
the first base is fixedly connected with any one of the table tops so as to fix the sensitive angular speed single machine on the table top.
Preferably, the three-degree-of-freedom test bench further comprises:
the first transmission mechanism is arranged opposite to the first hinge, one end of the first transmission mechanism is arranged on the first table-board, and the other end of the first transmission mechanism is arranged on the second table-board; the first transmission mechanism reciprocates along the vertical direction to drive the first table top to circumferentially move by taking the first hinge as a center;
the second transmission mechanism is arranged opposite to the second hinge, one end of the second transmission mechanism is arranged on the second table-board, and the other end of the second transmission mechanism is arranged on the first base; the second transmission mechanism reciprocates along the vertical direction to drive the second table top and the first table top to move circumferentially by taking the second hinge as a center;
one end of the third transmission mechanism is arranged on the third table-board, and the other end of the third transmission mechanism is arranged on the first base; the third transmission mechanism moves circumferentially to drive the third table top, the second table top and the first table top to move circumferentially with the first bearing as the center;
the first transmission mechanism, the second transmission mechanism and the third transmission mechanism drive any one or more of the first table board to the third table board to move, so that the sensitive angular velocity single machine fixed on the first table board is externally excited to measure the polarity of the sensitive angular velocity single machine.
Preferably, the single degree of freedom test bench comprises: the concave surface and the second base are rotated;
the rotating concave surface is movably connected with the second base through a second bearing and is used for placing the single rotating executing mechanism;
the second base is fixedly connected with any one desktop so as to fix the single rotary executing mechanism on the desktop;
the rotating concave surface carries out external excitation on the single rotating executing mechanism through circumferential motion so as to measure the polarity of the single rotating executing mechanism.
Preferably, the satellite semi-physical simulation test bed further includes: an anti-static bracelet grounding device;
prevent static bracelet earthing device set up in the test table on the frame, its one end is connected with earth ground stake through the wire, and the other end is connected with the antistatic bracelet of wearing on the human body to release human static.
Compared with the prior art, the invention has at least one of the following advantages:
according to the satellite semi-physical simulation test bed provided by the invention, the test table is provided with at least two layers of table tops, so that the test field is effectively saved; meanwhile, the frame of the test table is made of aluminum alloy, all the table tops are made of aluminum and are connected through copper wires, so that the potentials of all the table tops are equal, an equipotential environment is provided for each single machine to be tested, and the risk of floating the ground is reduced.
According to the invention, the honeycomb plate assembly is formed by freely combining a plurality of honeycomb plates, any installation position and installation direction can be established for each stand-alone machine to be tested on a test table, the whole satellite structure environment can be simulated, and whether the stand-alone machines to be tested have mutual interference at different installation positions can be verified in advance.
The three-degree-of-freedom test bench can provide external excitation for the sensitive angular velocity single machine, so that the polarity of the sensitive angular velocity single machine is measured, and the measurement method of the polarity of the sensitive angular velocity single machine is greatly simplified.
The single-degree-of-freedom test bench can provide external excitation for the single machine of the rotary actuating mechanism and visually test the polarity of the single machine of the rotary actuating mechanism.
The pressing block can install each stand-alone unit to be tested or other devices (such as a honeycomb panel, a three-degree-of-freedom test bench, a single-degree-of-freedom test bench and the like) on the desktop of the test bench and can adjust the installation position at will.
According to the invention, the anti-static bracelet grounding device is embedded into different positions of the test table frame, so that the anti-static bracelet grounding device is conveniently connected with the anti-static bracelet worn by an operator, and can prevent hooking.
The invention can also accurately measure the length of part of cables on the satellite.
Drawings
FIG. 1 is a perspective view of a satellite semi-physical simulation test bed according to an embodiment of the present invention;
FIG. 2 is a perspective view of a frame of a test table of a satellite semi-physical simulation test bed according to an embodiment of the present invention;
FIG. 3 is a perspective view of a cellular rice of a satellite semi-physical simulation test bed according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of two cellular boards of a satellite simulation test bed according to an embodiment of the present invention;
FIG. 5 is a perspective view of a compact of a satellite semi-physical simulation test bed according to an embodiment of the present invention;
FIG. 6 is a partial cross-sectional view of a three-degree-of-freedom test bed of a satellite semi-physical simulation test bed according to an embodiment of the present invention;
FIG. 7 is a partial cross-sectional view of a single degree of freedom test bed of a satellite semi-physical simulation test bed according to an embodiment of the present invention;
fig. 8 is an installation schematic diagram of an anti-static bracelet grounding device of a satellite semi-physical simulation test bed according to an embodiment of the invention.
Detailed Description
The satellite semi-physical simulation test bed provided by the invention is further described in detail with reference to the accompanying drawings and the detailed description. The advantages and features of the present invention will become more apparent from the following description. It is to be noted that the drawings are in a very simplified form and are all used in a non-precise scale for the purpose of facilitating and distinctly aiding in the description of the embodiments of the present invention. To make the objects, features and advantages of the present invention comprehensible, reference is made to the accompanying drawings. It should be understood that the structures, ratios, sizes, and the like shown in the drawings and described in the specification are only used for matching with the disclosure of the specification, so as to be understood and read by those skilled in the art, and are not used to limit the implementation conditions of the present invention, so that the present invention has no technical significance, and any structural modification, ratio relationship change or size adjustment should still fall within the scope of the present invention without affecting the efficacy and the achievable purpose of the present invention.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
With reference to fig. 1 to 8, the present embodiment provides a satellite semi-physical simulation test bed, including: a test table 10; the test table 10 comprises: a frame 101 and at least two layers of table tops 102; each desktop 102 is arranged on the frame 101 and used for fixing a stand-alone unit to be tested and/or a testing device of the stand-alone unit to be tested; all the tabletop 102 are connected through a wire, so that the potential of all the tabletop 102 is equal.
Referring to fig. 1 and fig. 2, each of the desktop 102 has a plurality of first through holes 1021, and the stand-alone device to be tested and/or the test apparatus are fixed on each of the desktop 102 through the first through holes 1021; all the table tops 102 are arranged at intervals in the vertical direction, and any two table tops 102 are parallel; the frame 101 is made of aluminum alloy; all of the tabletop 102 is made of aluminum.
Specifically, the frame 101 is a three-dimensional structure, and the cross section of the frame is L-shaped; the frame 101 may be formed by assembling a plurality of support rods 1011, and each of the support rods 1011 is made of an aluminum alloy. The first through hole 1021 arranged on each desktop 102 may be a threaded through hole, and a steel wire swivel nut is embedded in the threaded through hole, so that the stand-alone unit to be tested and the testing device (e.g., the three-degree-of-freedom testing platform, the single-degree-of-freedom testing platform, etc.) may be fixed on the desktop 102 by a fastener (e.g., a screw, a bolt, etc.); the tabletop 102 is made of aluminum, and all the tabletops 102 are connected through a lead, so that the potentials of all the tabletop 102 are the same, and the test table 10 is ensured to provide a reliable equipotential environment for the stand-alone machine to be tested; the conducting wire may be a copper wire, but the invention is not limited thereto.
In this embodiment, the test table 10 includes two layers of the table top 102, so that the test field can be effectively saved; the areas of all the desktops 102 can be different, and each desktop 102 is reserved with a hole 1022 with a concave arc cross section for cable routing of the satellite semi-physical simulation test bed, so that the cable can be connected to the stand-alone to be tested and the test device, the stand-alone to be tested and the test device can work normally, and meanwhile, the length of part of cables on the satellite can be determined by accurately measuring the length of the cable; the holes 1022 are also provided with fastening devices therein for securing the cables.
In this embodiment, the test table 10 is further provided with a storage layer 103, the storage layer 103 is disposed on the frame 101, and the storage layer 103 is located between the bottom of the frame 101 and the table top 102 closest to the bottom of the frame 101; the storage layer 103 may be used to store the stand-alone unit to be tested and the test device, etc. More specifically, the storage layer 103 is provided with a cabinet door, and the horizontal installation position of the cabinet door is retracted 50 mm-80 mm from the edge of the desktop 102, so that an operator can conveniently stand to operate the satellite semi-physical simulation test bed; a reserved space with the height of 15 mm-20 mm is formed between the vertical installation position of the cabinet door and the desktop 102, so that the cabinet door can be opened and closed conveniently.
Referring to fig. 1 and fig. 3, the satellite semi-physical simulation test bed further includes: a honeycomb panel assembly; the honeycomb panel assembly is arranged on any one desktop 102 and used for fixing the stand-alone unit to be tested; the cellular board assembly comprises a plurality of cellular boards 20, and any two of the cellular boards 20 are fixedly connected at any angle so as to fix the stand-alone unit to be tested on the desktop 102 at any angle, so as to simulate the whole star structure environment.
With continued reference to fig. 3, each of the cellular boards 20 includes: a panel 201 and a mounting plate 202 connected to one end of the panel 201 at an angle; the panel 201 is provided with a plurality of second through holes 2011, and the stand-alone unit to be tested is fixed on the panel 201 through the second through holes 2011; the mounting plate 202 is provided with a plurality of first through-hole grooves 2021, and the mounting plate 202 is fixedly connected to any one of the table tops 102 through the first through-hole grooves 2021.
Specifically, in the present embodiment, the panel 201 of each cellular board 20 is vertically connected to the mounting plate 202, and the cross section of each cellular board 20 is in an inverted T shape; the faceplate 201 and the mounting plate 202 may be integrally provided. The second through hole 2011 of the panel 201 may be a threaded through hole, and a steel wire thread insert is embedded in the threaded through hole, so that the stand-alone unit to be tested may be fixed to the panel 201 through a fastening member (e.g., a screw, a bolt, etc.). The mounting plate 202 of the cellular board 20 may be disposed on any one of the tabletop 102, and if the first through hole groove 2021 of the mounting plate 201 may be aligned with the first through hole 1021 of the tabletop 102, the cellular board 20 may be fixed on the tabletop 102 by fastening members (e.g., screws, bolts, etc.) penetrating through the first through hole groove 2021 and the first through hole 1021, so as to fix the single machine fixed on the cellular board 20 on the tabletop 102, but the invention is not limited thereto.
Referring to fig. 1, fig. 4 and fig. 5, the satellite semi-physical simulation test bed further includes: pressing blocks 50; the briquette 50 includes: a press block body, a first fixing member 501 and a second fixing member 502; a third through hole 503 and a second through hole groove 504 are formed in the pressing block body; the first end of the pressing block body is in compression joint with the mounting plate 202 of the cellular board 20, the first fixing piece 501 penetrates through the third through hole 503 to enable the second end of the pressing block body to be abutted against the desktop 102, the second fixing piece 502 penetrates through the second through hole groove 504 to enable the pressing block body to be fixedly connected with the desktop 102, the cellular board 20 is fixed on any desktop 102 at any angle, and then the stand-alone to be tested is fixed on any desktop 102 at any angle to simulate the whole star structure environment.
Specifically, the mounting plate 202 of the cellular board 20 is disposed on any one of the table tops 102, and if the first through hole 2021 of the mounting plate 202 is not aligned with the first through hole 1021 of the table top 102, the cellular board 20 needs to be fixed on the table top 102 by the pressing block 50, so that the single machine fixed on the cellular board 20 is fixed on any one of the table tops 102 at any angle without being limited by the first through hole 1021 of the table top 102, thereby facilitating simulation of a whole star structure environment, but the invention is not limited thereto.
In this embodiment, the second through-hole slot 504 is disposed between the first end and the second end of the pressing block body, and is used in cooperation with the second fixing member 502; the third through hole 503 is disposed at the second end of the pressing block body, and is used in cooperation with the first fixing member 501; the first fixing member 501 and the third through hole 503 are matched to adjust the height between the pressing block body and the table top 102, so that the pressing block 50 can fix the cellular board 20 on the table top 102 more firmly, the third through hole 503 can be a threaded through hole, and the first fixing member 501 can be a bolt.
Specifically, any two of the cellular boards 20, namely, the first cellular board 21 and the second cellular board 22, may be fixedly connected through the first through hole groove 2021 or the pressing block 50; when the first through hole groove 2021 of the first cellular board 21 can be aligned with the second through hole 2011 of the second cellular board 22, the first cellular board 21 can be fixed to the second cellular board 22 by a fastener (e.g., a screw, a bolt, etc.) penetrating through the first through hole groove 2021 and the second through hole 2011, and the second cellular board 22 can be fixed to the table top 102 at any angle; when the first through hole groove 2021 of the first cellular board 21 cannot be aligned with the second through hole 2011 of the second cellular board 22, the first cellular board 21 may be fixed to the second cellular board 22 by the press block 50, at this time, the first end of the press block body is pressed against the mounting plate 202 of the first cellular board 21, the second end of the press block body is abutted against the panel 201 of the second cellular board 22 by the first fixing member 501, the press block body is fixedly connected to the panel 201 of the second cellular board 22 by the second fixing member 502, so that the first cellular board 21 is fixed to the second cellular board 22, and the second cellular board 22 may be fixed to the table top 102 at any angle. By fixing the first cellular board 21 on the second cellular board 22 in the above manner, any two cellular boards 20 can be fixedly connected at any angle, that is, a free combination of any two cellular boards 20 is realized; the honeycomb panel assembly formed by freely combining a plurality of honeycomb panels 20 can be used for constructing any installation position and installation direction for the single machine to be tested in space, so as to simulate the whole satellite structure environment, but the invention is not limited thereto.
In this embodiment, the whole satellite structure environment of the small satellite can be simulated, and because the structural layout of the small satellite is relatively compact, the installation position between the single machines to be measured is relatively close, for example, the installation position between the magnetometer 70 (for measuring the magnetic field strength) and the magnetic torquer 71 (for generating the interaction torque between the magnetic field and the geomagnetic field); and the installation position of each stand-alone to be tested is relatively close and the condition of mutual interference in working can possibly occur, and the size of mutual influence in working of each stand-alone to be tested can be measured in advance by simulating the whole satellite structure environment through the satellite semi-physical simulation test bed.
Referring to fig. 6 and 7, the testing apparatus of the stand-alone device under test includes: the three-degree-of-freedom test bench 30 is arranged on any one of the desktops 102 and is used for fixing the sensitive angular velocity single machine 72 in the single machine to be tested so as to measure the polarity of the sensitive angular velocity single machine 72; the single-degree-of-freedom test bench 40 is arranged on any one of the table tops 102 and is used for fixing the single rotating execution mechanism 73 in the single machine to be tested so as to measure the polarity of the single rotating execution mechanism 73.
Referring to fig. 6, the three-degree-of-freedom testing platform 30 includes: a first table top 301, a second table top 302, a third table top 303, and a first base 304; the first table top 301 is arranged on the second table top 302 and connected with the second table top 302 through a first hinge 3011; the first table board 301 is provided with a plurality of fourth through holes 3012, and the sensitive angular velocity single machine 72 is fixed on the first table board 301 through the fourth through holes 3012; the second table top 302 is disposed on the third table top 303 and connected to the third table top 303 through a second hinge 3021, and the second hinge 3021 is orthogonal to the vector direction of the first hinge 3011; the third table-board 303 is movably connected with the first base 304 through a first bearing 3031; the first base 304 is fixedly connected to any one of the tables 102 to fix the single unit 72 to the table 102.
It is understood that, in some other embodiments, the three-degree-of-freedom test platform 30 further comprises: a first transmission mechanism 305 disposed opposite to the first hinge 3011, wherein one end of the first transmission mechanism 305 is disposed on the first table 301, and the other end is disposed on the second table 302; the first transmission mechanism 305 reciprocates in the vertical direction to drive the first table 301 to move circumferentially around the first hinge 3011; a second transmission mechanism 306 disposed opposite to the second hinge 3021, wherein one end of the second transmission mechanism 306 is disposed on the second table 302, and the other end is disposed on the first base 304; the second transmission mechanism 306 reciprocates in the vertical direction to drive the second table top 302 and the first table top 301 to move circumferentially around the second hinge 3021; a third transmission mechanism 307, one end of which is disposed on the third table 303, and the other end of which is disposed on the first base 304; the third transmission mechanism 307 performs circumferential motion to drive the third table-board 303, the second table-board 302 and the first table-board 301 to perform circumferential motion by taking the first bearing 3031 as a center; the first transmission mechanism 305, the second transmission mechanism 306 and the third transmission mechanism 307 drive any one or more of the first table 301 to the third table 303 to move, so as to externally excite the sensitive angular velocity single machine 72 fixed on the first table 301, and measure the polarity of the sensitive angular velocity single machine 72.
Specifically, the fourth through hole 3012 of the first platform 301 may be a threaded through hole, and a steel wire swivel nut is embedded in the threaded through hole, so that the sensitive angular velocity single machine 72 (e.g., a fiber optic gyroscope, a hemispherical resonator gyroscope, etc.) may be fixed to the first platform 301 through a fastener (e.g., a screw, a bolt, etc.). One end of the first hinge 3011 is fixed on the first end surface of the first table 301, and the other end is fixed on the first end surface of the second table 302. The first transmission mechanism 305 is disposed opposite to the first hinge 3011, and the first transmission mechanism 305 may adopt a rack transmission mechanism; the rack part in the first transmission mechanism 305 can be fixed on the second end surface of the first table-board 301, and the motor part in the first transmission mechanism 305 can be fixed on the side wall of the second table-board 302; the first transmission mechanism 305 reciprocates in the vertical direction to drive the first table 301 to move circumferentially around the first hinge 3011, so that the single sensitive angular velocity machine 73 fixed on the first table 301 moves circumferentially around the first hinge 3011, but the invention is not limited thereto.
Specifically, one end of the second hinge 3021 is fixed to the first end surface of the second table top 302, and the other end of the second hinge 3021 is fixed to the first end surface of the third table top 303; the second transmission mechanism 306 is disposed opposite to the second hinge 3021, and the second transmission mechanism 306 may adopt a rack transmission mechanism; the rack portion of the second transmission mechanism 306 can be fixed on the second end surface of the second table 302, and the motor portion of the second transmission mechanism 306 can be fixed on the sidewall of the first base 304; the second transmission mechanism 306 reciprocates in the vertical direction to drive the second table top 302 to move circumferentially around the second hinge 3021, so as to drive the first table top 301 disposed on the second table top 302 to move circumferentially, and further drive the single sensitive angular velocity unit 72 fixed on the first table top 301 to move circumferentially around the second hinge 3021, but the invention is not limited thereto.
Specifically, the third transmission mechanism 307 may adopt a gear transmission mechanism, a gear part in the third transmission mechanism 307 is disposed on the third table 303, and a motor part in the third transmission mechanism 307 is fixed on the first base 304; the third transmission mechanism 307 performs a circumferential motion around its axis, and may drive the third table top 303 to perform a circumferential motion around the first bearing 3031, so as to drive the second table top 302 and the first table top 301 disposed on the third table top 303 to perform a circumferential motion, and further drive the sensitive angular velocity single machine 72 fixed on the first table top 301 to perform a circumferential motion around the first bearing 3031, but the invention is not limited thereto.
In this embodiment, the circumferential movement of the sensitive angular velocity stand-alone 72 around the first hinge 3011 may represent the rotation thereof in the rolling direction, the circumferential movement around the second hinge 3021 may represent the rotation thereof in the pitching direction, and the circumferential movement around the first bearing 3031 may represent the rolling thereof in the yawing direction. The three-degree-of-freedom test bench 30 can drive any one or more of the first table 301 to the third table 303 to rotate in the three orthogonal directions of rolling, pitching and yawing through the movement of the first transmission mechanism 305, the second transmission mechanism 306 and the third transmission mechanism 307, so as to provide the rotation in the three orthogonal directions of rolling, pitching and yawing for the sensitive angular velocity single machine 72 fixed on the first table 301, so as to externally excite the sensitive angular velocity single machine 72, and facilitate the measurement of the polarity of the sensitive angular velocity single machine 72. More specifically, in the present embodiment, the rotation range of the sensitive angular velocity single machine 72 in the rolling direction is 0 to 15 °, the rotation range in the pitching direction is also 0 to 15 °, and the rotation range in the yawing direction is 0 to 360 °. The first base 304 may be fixed to any of the table tops 102 by fasteners (e.g., screws, bolts, etc.) or the pressing block 50.
With continued reference to fig. 7, the single-degree-of-freedom testing station 40 includes: a concave rotating surface 401 and a second base 402; the rotating concave surface 401 is movably connected with the second base 402 through a second bearing 4011, and the rotating concave surface 401 is used for placing the rotating execution mechanism single machine 73; the second base 402 is fixedly connected with any one of the table tops 102, so as to fix the single rotary actuator 73 on the table top 102; the concave rotating surface 401 externally excites the single rotary actuator 73 by circumferential motion to measure the polarity of the single rotary actuator 73.
Specifically, in this embodiment, the rotation concave surface 401 may perform circumferential rotation motion through the second bearing 4011, so as to drive the rotation executing mechanism single machine 73 placed in the rotation concave surface 401 to perform circumferential rotation motion, and provide external excitation for the rotation executing mechanism single machine 73, so as to measure the polarity of the rotation executing mechanism single machine 73. The second bearing 4011 may be a ball bearing, which ensures that the rotational friction torque when the rotation concave surface 401 rotates is sufficiently small. The inner surface of the concave rotating surface 401 can be further pasted with a layer of soft material 4012, so that the surface of the single rotating actuator 73 is prevented from being scratched in the rotating process of the concave rotating surface 401. The second base 402 can be fixed on any one of the table tops 102 by a fastener (e.g., a screw, a bolt, etc.) or the pressing block 50, but the invention is not limited thereto.
Referring to fig. 8, the satellite semi-physical simulation test bed further includes: an anti-static bracelet grounding device 60; prevent static bracelet earthing device 60 set up in test table 10 on the frame 101, its one end is connected with earth ground stake through the wire, and the other end is connected with the prevent static bracelet of wearing on the human body to release human static.
Specifically, the anti-static bracelet grounding device 60 is embedded and can be embedded into the support rod 1011 of the frame 101; the wire connecting the anti-static bracelet grounding device 60 and the earth ground pile may be a copper wire, but the invention is not limited thereto.
In this embodiment, the quantity of preventing static bracelet earthing device 60 is 10, imbed respectively in the different positions of bracing piece 1011 to operating personnel will wear in the position of difference prevent the static bracelet with prevent that static bracelet earthing device 60 connects, thereby release human static, avoid human static to the measuring result of the unit that awaits measuring causes the influence.
In summary, according to the satellite semi-physical simulation test bed provided by the embodiment, the test table has at least two layers of table tops, so that the test field can be effectively saved; meanwhile, the frame of the test table is made of aluminum alloy, all the table tops are made of aluminum, and the two layers of the table tops are connected by copper wires, so that an equipotential environment is provided for each single machine to be tested; the honeycomb plate assemblies formed by freely combining the plurality of honeycomb plates can construct any installation position for each single machine to be tested on the test table so as to simulate the whole satellite structure environment and verify whether the single machines to be tested can interfere with each other at different installation positions in advance; the three-degree-of-freedom test bench and the single-degree-of-freedom test bench can respectively provide external excitation for the sensitive angular velocity single machine and the rotation executing mechanism single machine, so that the polarities of the sensitive angular velocity single machine and the rotation executing mechanism single machine are measured. The application of the satellite semi-physical simulation test bed provided by the embodiment overcomes the limitation of the traditional satellite semi-physical simulation test bed, and makes the test of each single machine of the attitude and orbit control subsystem more convenient and reliable.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.
Claims (10)
1. A satellite semi-physical simulation test bed is characterized by comprising: a test table (10); the test table (10) comprises: a frame (101) and at least two layers of table tops (102);
each desktop (102) is arranged on the frame (101) and is used for fixing a stand-alone to be tested and/or a testing device of the stand-alone to be tested;
all the table tops (102) are connected through wires, so that the potentials of all the table tops (102) are equal.
2. The satellite semi-physical simulation test stand of claim 1,
each desktop (102) is provided with a plurality of first through holes (1021), and the stand-alone unit to be tested and/or the test device are/is fixed on each desktop (102) through the first through holes (1021);
all the table tops (102) are arranged at intervals along the vertical direction, and any two table tops (102) are parallel;
the frame (101) is made of aluminum alloy; all the table tops (102) are made of aluminum.
3. The satellite semi-physical simulation test bed of claim 1, further comprising: a honeycomb panel assembly; the honeycomb panel assembly is arranged on any one desktop (102) and used for fixing the stand-alone unit to be tested;
the honeycomb panel assembly comprises a plurality of honeycomb panels (20), and any two honeycomb panels (20) are fixedly connected at any angle so as to fix the stand-alone to be tested on the desktop (102) at any angle to simulate the whole star structure environment.
4. The satellite semi-physical simulation test bed of claim 3, wherein each of the cellular boards (20) comprises: a panel (201) and a mounting plate (202) connected at an angle to one end of the panel (201);
the panel (201) is provided with a plurality of second through holes (2011), and the stand-alone unit to be tested is fixed on the panel (201) through the second through holes (2011);
the mounting plate (202) is provided with a plurality of first through hole grooves (2021), and the mounting plate (202) is fixedly connected with any one of the table tops (102) through the first through hole grooves (2021).
5. The satellite semi-physical simulation test bed of claim 4, further comprising: a briquette (50); the compact (50) comprises: the pressing block comprises a pressing block body, a first fixing piece (501) and a second fixing piece (502);
a third through hole (503) and a second through hole groove (504) are formed in the pressing block body; the first end of the pressing block body is in compression joint with the mounting plate (202) of the honeycomb plate (20), the first fixing piece (501) penetrates through the third through hole (503) to enable the second end of the pressing block body to be abutted to the desktop (102), the second fixing piece (502) penetrates through the second through hole groove (504) to enable the pressing block body to be fixedly connected with the desktop (102), the honeycomb plate (20) is fixed to any desktop (102) at any angle, and then the stand-alone unit to be tested is fixed to any desktop (102) at any angle to simulate the whole star structure environment.
6. The satellite semi-physical simulation test bed of claim 1, wherein the testing device of the stand-alone under test comprises:
the three-degree-of-freedom test bench (30) is arranged on any desktop (102) and is used for fixing the sensitive angular velocity single machine (72) in the single machine to be tested so as to measure the polarity of the sensitive angular velocity single machine (72);
the single-degree-of-freedom test bench (40) is arranged on any one of the table tops (102) and used for fixing the single rotating execution mechanism (73) in the single machine to be tested so as to measure the polarity of the single rotating execution mechanism (73).
7. The satellite semi-physical simulation test bed according to claim 6, wherein the three-degree-of-freedom test bed (30) comprises: a first table top (301), a second table top (302), a third table top (303) and a first base (304);
the first table top (301) is arranged on the second table top (302) and is connected with the second table top (302) through a first hinge (3011); the first table board (301) is provided with a plurality of fourth through holes (3012), and the sensitive angular velocity single machine (72) is fixed on the first table board (301) through the fourth through holes (3012);
the second table top (302) is arranged on the third table top (303) and is connected with the third table top (303) through a second hinge (3021), and the vector direction of the second hinge (3021) is orthogonal to the vector direction of the first hinge (3011);
the third table top (303) is movably connected with the first base (304) through a first bearing (3031);
the first pedestal (304) is fixedly connected with any one of the table tops (102) so as to fix the single machine (72) with sensitive angular velocity on the table top (102).
8. The satellite semi-physical simulation test bed according to claim 7, wherein the three-degree-of-freedom test bed (30) further comprises:
the first transmission mechanism (305) is arranged opposite to the first hinge (3011), one end of the first transmission mechanism (305) is arranged on the first table board (301), and the other end of the first transmission mechanism (305) is arranged on the second table board (302); the first transmission mechanism (305) reciprocates along the vertical direction to drive the first table top (301) to move circumferentially by taking the first hinge (3011) as the center;
a second transmission mechanism (306) disposed opposite to the second hinge (3021), wherein one end of the second transmission mechanism (306) is disposed on the second table top (302), and the other end is disposed on the first base (304); the second transmission mechanism (306) reciprocates along the vertical direction to drive the second table top (302) and the first table top (301) to move circumferentially by taking the second hinge (3021) as a center;
a third transmission mechanism (307), one end of which is arranged on the third table top (303), and the other end of which is arranged on the first base (304); the third transmission mechanism (307) moves circumferentially to drive the third table top (303), the second table top (302) and the first table top (301) to move circumferentially with the first bearing (3031) as the center;
the first transmission mechanism (305), the second transmission mechanism (306) and the third transmission mechanism (307) drive any one or more of the first table board (301) to the third table board (303) to move, and the sensitive angular speed single machine (72) fixed on the first table board (301) is externally excited to measure the polarity of the sensitive angular speed single machine (72).
9. The satellite semi-physical simulation test bed according to claim 6, wherein the single degree of freedom test bed (40) comprises: a rotating concave surface (401) and a second base (402);
the rotating concave surface (401) is movably connected with the second base (402) through a second bearing (4011), and the rotating concave surface (401) is used for placing the rotating execution mechanism single machine (73);
the second base (402) is fixedly connected with any one of the table tops (102) so as to fix the rotating executing mechanism single machine (73) on the table top (102);
the rotating concave surface (401) externally excites the rotating actuator single machine (73) through circumferential motion so as to measure the polarity of the rotating actuator single machine (73).
10. The satellite semi-physical simulation test bed of claim 1, further comprising: an anti-static bracelet grounding device (60);
prevent static bracelet earthing device (60) set up in test table (10) on frame (101), its one end is connected with earth ground stake through the wire, and the other end is connected with the antistatic bracelet of wearing on the human body to release human static.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2001097224A2 (en) * | 2000-06-09 | 2001-12-20 | Iomega Corporation | Method and apparatus for storing data in a removable cartridge |
| WO2006075158A1 (en) * | 2005-01-11 | 2006-07-20 | Isis Innovation Limited | Evaluation of the performance of systems |
| CN102081360A (en) * | 2011-02-25 | 2011-06-01 | 哈尔滨工业大学 | Inertial astronomical combined navigational semi-physical experimental system |
| CN206920554U (en) * | 2017-05-05 | 2018-01-23 | 北京经纬恒润科技有限公司 | A kind of hardware-in―the-loop test system of car body controller |
| CN110161879A (en) * | 2019-05-17 | 2019-08-23 | 南京航空航天大学 | A kind of semi physical experiment simulation platform of satellite in orbit |
| CN110174851A (en) * | 2019-05-31 | 2019-08-27 | 西北工业大学 | A kind of ground Hardware-in-loop Simulation Experimentation device of Space Rotating tether system |
-
2020
- 2020-09-01 CN CN202010905656.3A patent/CN111959834B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2001097224A2 (en) * | 2000-06-09 | 2001-12-20 | Iomega Corporation | Method and apparatus for storing data in a removable cartridge |
| WO2006075158A1 (en) * | 2005-01-11 | 2006-07-20 | Isis Innovation Limited | Evaluation of the performance of systems |
| CN102081360A (en) * | 2011-02-25 | 2011-06-01 | 哈尔滨工业大学 | Inertial astronomical combined navigational semi-physical experimental system |
| CN206920554U (en) * | 2017-05-05 | 2018-01-23 | 北京经纬恒润科技有限公司 | A kind of hardware-in―the-loop test system of car body controller |
| CN110161879A (en) * | 2019-05-17 | 2019-08-23 | 南京航空航天大学 | A kind of semi physical experiment simulation platform of satellite in orbit |
| CN110174851A (en) * | 2019-05-31 | 2019-08-27 | 西北工业大学 | A kind of ground Hardware-in-loop Simulation Experimentation device of Space Rotating tether system |
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|---|---|
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