CN115072010B - Space satellite-borne extensible turntable mechanism and method for testing delay time thereof - Google Patents

Abstract

The invention relates to a turntable mechanism for a space satellite-borne optical imaging load, in particular to a space satellite-borne extensible turntable mechanism and a method for testing the delay time of the space satellite-borne extensible turntable mechanism, which are used for solving the defects that the existing space satellite-borne turntable mechanism is small in load or cannot effectively reduce the mechanical vibration and impact quantity of the optical imaging load. The space satellite-borne extensible turntable mechanism comprises a first rotating arm, a second rotating arm, an extensible driving mechanism and a mechanical locking mechanism, wherein an azimuth shaft and a pitching shaft which are used for supporting an optical imaging load are respectively arranged on the first rotating arm and the second rotating arm, the supporting mechanism is in a folded state before being launched into the orbit, and is converted into an extended state after being launched into the orbit, so that the mechanical vibration and the impact quantity of the optical imaging load are effectively reduced, and the load ratio and the launching reliability are further improved. Meanwhile, the invention discloses a method for testing the delay time of the space satellite-borne deployable turntable mechanism.

Description

A test method for a space-borne deployable turntable mechanism and its lag time

technical field

The invention relates to a turntable mechanism used for a space satellite-borne optical imaging load, in particular to a space satellite-borne expandable turntable mechanism and a test method for its lag time.

Background technique

In recent years, space-borne optoelectronic imaging and measurement technology has developed rapidly. Among them, the turntable mechanism is an important part of the drive and support of space optical imaging loads, and the stability of its mechanism has a great impact on imaging and measurement accuracy.

Due to the existence of the turntable mechanism, the optical imaging load has a certain height difference relative to the installation surface, so when the vibration and impact of the star are transmitted to the optical imaging load by the turntable mechanism, it is magnified by 10-20 times. Most of the existing turntable mechanisms adopt a U-shaped structure or an L-shaped structure composed of an azimuth axis and a pitch axis. The U-shaped structure has relatively stable mechanical properties, but its weight is relatively small, and the load is relatively small. Although the L-shaped structure is lighter in weight, the load The ratio is larger, but its stiffness and strength are poor, which cannot effectively reduce the mechanical vibration and impact of the optical imaging load.

Contents of the invention

The purpose of the present invention is to solve the shortcomings of the existing space star-borne turntable mechanism, or the load is relatively small, or the inability to effectively reduce the mechanical vibration and impact of the optical imaging load, and provide a space star-borne deployable Test method for turntable mechanism and its dead time.

In order to solve the deficiencies in the above-mentioned prior art, the present invention provides the following technical solutions:

A space star-borne expandable turntable mechanism, which is special in that it includes a base and a support mechanism arranged on the base, and the support mechanism includes a first rotating arm, a second rotating arm, an unfolding drive mechanism and a mechanical locking mechanism ;

The first rotating arm is arranged on the base, the rotating axis of the first rotating arm is perpendicular to the surface of the base, the first rotating arm can rotate ±170° around its rotating axis relative to the preset original position, and is intended to support the azimuth axis of the optical imaging load Coincident with the axis of rotation of the first rotating arm;

One end of the second rotating arm is hinged to the end of the first rotating arm through the unfolding drive mechanism, and the other end is connected to the optical imaging load to be supported, and is provided with a pitch axis intended to support the optical imaging load; the unfolding drive mechanism includes Mounting shaft, motor arranged at one end of the mounting shaft, the rotating shaft of the second rotating arm coincides with the axis of the mounting shaft, and the second rotating arm can rotate 90° around its rotating shaft; the pitch axis is perpendicular to the second rotating arm and the axis of rotation of the second rotating arm;

The mechanical locking mechanism includes a position detection component, a first locking component and a second locking component; the position detection component is used to detect the angle between the second rotating arm and the first rotating arm, and is used to output The signal is sent to the second locking component; the second locking component is used to fix the position of the second rotating arm according to the in-position signal; the first locking component is used to temporarily fix the second locking component before the second locking component is fixed. the position of the swivel arm;

The support mechanism is provided with a folded state and an unfolded state; the support mechanism is in the folded state, the angle between the second rotating arm and the first rotating arm is 0°, and the optical imaging load to be supported is located on the second rotating arm Below, and the optical imaging load to be supported is connected to the base; or, the support mechanism is in an unfolded state, the angle between the second rotating arm and the first rotating arm is 90°, and the optical imaging load to be supported is separated from the base , the second locking component fixes the position of the second rotating arm.

Further, the second locking assembly includes a second locking fixing part arranged at the end of the first rotating arm and close to the deployment driving mechanism, and a second locking moving part arranged on the second rotating arm, the The included angle between the second locking fixed part and the top surface of the first rotating arm is 90°, one end of the second locking moving part is hinged to the second rotating arm, and the other end can rotate around the hinge, and is positioned on the support mechanism In the unfolded state, that is, when the angle between the second rotating arm and the first rotating arm is 90°, it engages with the second locking and fixing part.

Further, the position detection assembly includes a Hall switch arranged on the side of the second locking and fixing part close to the second rotating arm, and a Hall magnet corresponding to the Hall switch arranged on the second rotating arm; The Hall switch outputs an in-position signal when the second rotating arm rotates to an angle of 90° with the first rotating arm; The first electromagnet on one side of the arm, and the second electromagnet corresponding to the first electromagnet arranged on the second rotating arm can temporarily fix the position of the second rotating arm by the attraction force of the two electromagnets.

Further, the rotating end of the second locking and moving part is provided with a first connecting piece, and the second rotating arm is provided with a second connecting piece that can engage with the first connecting piece, and the second locking and moving part closes When the in-position signal is received, the first connecting part is separated from the second connecting part.

Further, the end of the first rotating arm is provided with a U-shaped hinge, and both ends of the U-shaped hinge are provided with first through holes; the end of the first rotating arm has a hole that fits the opening of the U-shaped hinge A protruding part, the protruding part is provided with a second through hole; the other end of the installation shaft is provided with a torsion spring, and the installation shaft includes a first transfer shaft connected to the motor through a coupling and a second through shaft connected to the torsion spring. Two transfer shafts, the first transfer shaft passes through the first through hole at one end of the U-shaped hinge, the second transfer shaft passes through the first through hole at the other end of the U-shaped hinge, the first transfer shaft and the second The transfer shaft is butted in the second through hole of the protrusion; angular contact bearings are arranged between the first transfer shaft, the second transfer shaft and the first through holes at both ends of the U-shaped hinge, and the inner ring of the angular contact bearing An inner pressure plate is provided, and an outer pressure plate is provided on the outer ring; both the motor and the torsion spring are used to provide driving force for the movement of the second rotating arm, and the existence of the torsion spring can reduce the output torque of the motor.

Further, the base is provided with a fixing piece, and the fixing piece is used to fix the optical imaging load to be supported on the base through the fixing hole on the optical imaging load to be supported in the folded state, so as to reduce the optical imaging load before launching into orbit. The amount of mechanical vibration and impact the load is subjected to.

A method for testing the lag time of a space satellite-borne expandable turntable mechanism, which is special in that it is used for the above-mentioned space satellite-borne expandable turntable mechanism, including the following steps:

Step 1. Fix the space starborne expandable turntable mechanism on the micro-vibration test platform, make the support mechanism in the unfolded state, and clean up the objects that generate vibration and noise around the micro-vibration test platform;

Step 2. After connecting the micro-vibration test platform and the micro-vibration host computer system, start the micro-vibration host computer system;

Step 3, setting the motion form of the space starborne expandable turntable mechanism;

The exercise forms include the following three types:

； The first type of motion is only the motion of the pitch axis, and the optical imaging load to be supported rotates around its pitch axis several times at a preset speed, and the time for each rotation is

;

； The second type of movement is only the movement of the azimuth axis. The optical imaging load to be supported rotates around its azimuth axis several times at a preset speed, and the time for each rotation is

;

； The third movement form is the linkage between the azimuth axis and the pitch axis. The optical imaging load to be supported rotates around its azimuth axis and the pitch axis multiple times at the preset speed at the same time. The time for each rotation of the optical imaging load to be supported is

;

，则输出时间

旋转时间

之差即为该次旋转迟滞时间。 Step 4. Control the space starborne expandable turntable mechanism to move according to the movement form described in step 3, sense the movement through the micro-vibration test platform, output the induction signal, and record the output time of the induction signal for each rotation of each movement form

, then the output time

rotation time

The difference is the rotation delay time.

Further, in step 3, the first form of motion is specifically: the optical imaging load to be supported rotates 12 times around its pitch axis at a preset speed, each rotation is 10°, and each rotation time is 2.5s. The preset speed is 4°/s.

Further, in step 3, the second movement form is specifically: the optical imaging load to be supported rotates 34 times around its azimuth axis at a preset speed, each rotation is 10°, and each rotation time is 2.5s. The preset speed is 4°/s.

Further, in step 3, the third movement form is specifically: the load to be supported for optical imaging is rotated 12 times around its azimuth axis and pitch axis at a preset speed, each rotation is 10°, and the load to be supported for optical imaging is rotated 12 times at a preset speed. The first rotation time is 2.5s, and the preset speed is 4°/s.

Compared with prior art, the beneficial effect of the present invention is:

(1) A space starborne expandable turntable mechanism of the present invention includes a first rotating arm, a second rotating arm, an unfolding drive mechanism and a mechanical locking mechanism. The azimuth axis and pitch axis of the imaging payload, the support mechanism is in a folded state before launching into orbit, and it is converted into an unfolded state after entering orbit, which effectively reduces the mechanical vibration and impact of the optical imaging payload, thereby improving the load ratio and launch reliability. .

(2) The mechanical locking mechanism adopted by a space starborne expandable turntable mechanism of the present invention includes a position detection component, a first locking component and a second locking component. When the angle between the first rotating arms is 90°, it will output the in-position signal to the second locking assembly, and the second locking assembly will fix the position of the second rotating arm after receiving the in-position signal, in order to ensure that the second locking assembly When the second locking moving part and the second locking fixed part are clamped, the angle between the second rotating arm and the first rotating arm is still 90°, and the present invention is provided with a first locking assembly for the second rotating The position of the arm is temporarily fixed.

(3) A method for testing the hysteresis time of a space-borne expandable turntable mechanism in the present invention is to test the hysteresis time of the space-borne expandable turntable mechanism on the micro-vibration test platform and the micro-vibration host computer system, and by reducing the drive The step size of the motor drive is used to obtain higher-precision micro-jitter delay time measurement results. Through this test method, the system tracking delay time can be obtained before the photoelectric imaging system is debugged, which can effectively improve the speed of photoelectric system installation and adjustment.

Description of drawings

Figure 1 is a schematic structural view of an embodiment of a space-borne expandable turntable mechanism of the present invention (the support mechanism is in a folded state);

Fig. 2 is a schematic structural view of the support mechanism in the unfolded state in the embodiment of the present invention;

Fig. 3 is a sectional view of the unfolding drive mechanism in Fig. 2;

Fig. 4 is the enlarged schematic diagram of the structure of the mechanical locking mechanism in Fig. 1;

Fig. 5 is a schematic structural diagram of a space-borne expandable turntable mechanism when the support mechanism is in the unfolded state in an embodiment of the present invention;

6 is a schematic diagram of the characteristic sinusoidal scanning vibration test results when the support mechanism is in a folded state in an embodiment of the present invention;

Fig. 7 is a schematic diagram of the characteristic sinusoidal scanning vibration test results when the supporting mechanism is in the unfolded state in the embodiment of the present invention.

The reference signs are explained as follows:

01-to be supported by optical imaging load; 02-fixing hole;

1-base; 2-fixer; 3-support mechanism, 31-first rotating arm, 311-U-shaped hinge, 32-second rotating arm, 321-protruding part,

33-expansion drive mechanism, 331-installation shaft, 332-motor, 333-torsion spring, 334-angular contact bearing, 335-inner pressure plate, 336-outer pressure plate,

34-Mechanical locking mechanism, 341-Position detection component, 3411-Hall switch, 3412-Hall magnet, 342-First locking component, 3421-First electromagnet, 3422-Second electromagnet, 343- The second locking component, 3431 - the second locking fixing part, 3432 - the second locking moving part, 3433 - the first connecting part, 3434 - the second connecting part.

detailed description

The present invention will be further described below in conjunction with the accompanying drawings and exemplary embodiments.

Referring to Figures 1 to 4, a space starborne expandable turntable mechanism includes a base 1, a fixing member 2 and a support mechanism 3 arranged on the base 1, and the support mechanism 3 includes a first rotating arm 31, a second A rotating arm 32 , an unfolding drive mechanism 33 and a mechanical locking mechanism 34 .

The first rotating arm 31 is arranged on the base 1, the rotating axis of the first rotating arm 31 is perpendicular to the surface of the base 1, the first rotating arm 31 can rotate ±170° around its rotating axis relative to the preset original position, and is intended to support the optical The azimuth axis of the imaging load 01 coincides with the rotation axis of the first rotating arm 31 .

One end of the second rotating arm 32 is hinged to the end of the first rotating arm 31 through the unfolding drive mechanism 33 , and the other end is provided with a pitch axis intended to support the optical imaging load 01 and is provided with the optical imaging load 01 .

The unfolding drive mechanism 33 includes a mounting shaft 331, a motor 332 and a torsion spring 333 respectively arranged at both ends of the mounting shaft 331, a U-shaped hinge 311 is provided at the end of the first rotating arm 31, and both ends of the U-shaped hinge 311 are provided with There is a first through hole, the end of the first rotating arm 31 has a protruding part 321 adapted to the opening of the U-shaped hinge part 311, the protruding part 321 is provided with a second through hole, the mounting shaft 331 includes a shaft coupling and The first transfer shaft connected to the motor 332 and the second transfer shaft connected to the torsion spring 333, the first transfer shaft passes through the first through hole at one end of the U-shaped hinge part 311, and the second transfer shaft passes through the U-shaped joint. The first through hole at the other end of the hinge part 311, the first transfer shaft and the second transfer shaft are butted in the second through hole of the protruding part 321, the first transfer shaft, the second transfer shaft and the U-shaped hinge Angular contact bearings 334 are arranged between the first through holes of the portion 311 , the inner ring of the angular contact bearings 334 is provided with an inner pressure plate 335 , and the outer ring of the angular contact bearings 334 is provided with an outer pressure plate 336 .

The rotation axis of the second rotation arm 32 coincides with the axis of the installation shaft 331, and the second rotation arm 32 can rotate 90° around its rotation axis; the pitch axis to support the optical imaging load 01 is perpendicular to the second rotation arm 32 and the second rotation arm 32. The rotation axis of the rotation arm 32 is shown by the dotted line in FIG. 5 .

The mechanical locking mechanism 34 includes a position detection component 341, a first locking component 342 and a second locking component 343; the second locking component 343 is used to fix the position of the second rotating arm 32 according to the in-position signal , the second locking assembly 343 includes a second locking fixing part 3431 disposed at the end of the first rotating arm 31 and close to the deployment driving mechanism 33 , and a second locking moving part 3432 disposed on the second rotating arm 32 , The included angle between the second locking fixed part 3431 and the top surface of the first rotating arm 31 is 90°, one end of the second locking moving part 3432 is hinged to the second rotating arm 32, and the other end can rotate around the hinge. Rotate, and engage with the second locking and fixing part 3431 when the support mechanism 3 is in the unfolded state, that is, the angle between the second rotating arm 32 and the first rotating arm 31 is 90°; the position detection assembly 341 is used for Detect the angle between the second rotating arm 32 and the first rotating arm 31, and output the in-position signal to the second locking assembly 343. The position detection assembly 341 includes Hall switch 3411 on one side of 32, and Hall magnet 3412 arranged on the second rotating arm 32; the first locking component 342 is used to temporarily fix the second rotating arm before the second locking component 343 is fixed. The position of the arm 32, the first locking assembly 342 includes the first electromagnet 3421 arranged on the side of the second locking and fixing part 3431 close to the second rotating arm 32, and the first electromagnet 3421 arranged on the second rotating arm 32 and the first electromagnet The iron 3421 corresponds to the second electromagnet 3422 .

The rotating end of the second locking moving part 3432 is provided with a first connecting part 3433, and the second rotating arm 32 is provided with a second connecting part 3434 that can engage with the first connecting part 3433. The second locking moving part When 3432 receives the in-position signal, the first connecting part 3433 is separated from the second connecting part 3434 .

The supporting mechanism 3 is provided with a folded state and an unfolded state; referring to Fig. 1 and Fig. 2, the supporting mechanism 3 is in the folded state, and the angle between the second rotating arm 32 and the first rotating arm 31 is 0°, which intends to support the optical The imaging load 01 is located below the second rotating arm 32, and the fixing hole 02 on the optical imaging load 01 to be supported is connected to the base 1 through the fixing piece 2, and the first connecting piece 3433 is clamped with the second connecting piece 3434; or, refer to FIG. 5 , the supporting mechanism 3 is in the unfolded state, the angle between the second rotating arm 32 and the first rotating arm 31 is 90°, the fixing hole 02 on the optical imaging load 01 to be supported is separated from the fixing member 2, and the second locking movement The part 3432 engages with the second locking and fixing part 3431 .

Working process of the present invention is as follows:

The support mechanism 3 is in a folded state before launching into the rail, and the support mechanism 3 is converted into an unfolded state after entering the rail; when converting, firstly, the fixing part 2 is separated from the fixing hole 02 on the optical imaging load 01 to be supported, and the motor 332 is started. Under the auxiliary drive of the torsion spring 333, the second rotating arm 32 rotates around the installation shaft 331 until the angle between the second rotating arm 32 and the first rotating arm 31 is 90°, and the Hall switch 3411 senses the Hall magnet Steel 3412, the Hall switch 3411 outputs the in-position signal to the second locking assembly 343, and the first locking assembly 342 temporarily fixes the position of the second rotating arm 32, and the second locking assembly 343 makes the first locking assembly 343 receive the in-position signal. The connecting part 3433 is separated from the second connecting part 3434, and after the second locking moving part 3432 is engaged with the second locking fixing part 3431, the first locking component 342 stops working, that is, the conversion is completed.

In this embodiment, the supporting mechanism 3 is in a folded state, and the distance between the center of mass of the optical imaging load 01 to be supported and the surface of the base 1 is 63.5 mm; The distance between them is 351mm.

The characteristic sinusoidal scanning vibration test is carried out on the space starborne expandable turntable mechanism and the whole machine to support the optical imaging load 01, the test conditions are shown in Table 1; the test results are shown in Figure 6 and Figure 7, and the support mechanism 3 is in the In the folded state, the vibration of the star is transmitted to the optical imaging load 01 to be supported, and the vibration magnitude will be magnified by 1.5 times at the first frequency (63 Hz); when the support mechanism 3 is in the unfolded state, the vibration of the star is transmitted to the optical imaging load to be supported 01, the vibration magnitude will be magnified by 20 times.

Table 1

Frequency Range Vibration amplitude (0-peak value) scan rate 10～500Hz 0.5g 1oct/min

During the pitching, azimuth, and linkage processes of the space-borne expandable turntable mechanism, there is a slight lag time when the motion stops because there are gaps between multiple motion joints, that is, the motion stop command has been given, but The mechanism will still move for a period of time, which is called the lag time. This lag time has an important impact on the tracking measurement of the photoelectric imaging system. When the photoelectric turntable tracking measurement is performed in the later stage, the actual working conditions can be compensated based on the lag time.

The invention discloses a method for testing the hysteresis time of a space satellite-borne deployable turntable mechanism, which is used for the above-mentioned space satellite-borne deployable turntable mechanism, comprising the following steps:

Step 1. Fix the space starborne expandable turntable mechanism on the micro-vibration test platform, make the support mechanism 3 in the unfolded state, and clean up the objects that generate vibration and noise around the micro-vibration test platform;

Step 2. After connecting the micro-vibration test platform and the micro-vibration host computer system, start the micro-vibration host computer system;

Step 3, setting the motion form of the space starborne expandable turntable mechanism;

The exercise forms include the following three types:

，

； The first type of motion is only the motion of the pitch axis. The optical imaging payload 01 to be supported rotates 12 times around its pitch axis at 4°/s, each rotation is 10°, and the time for each rotation is

,

;

，

； The second type of movement is the movement of the azimuth axis only. It is intended to support the optical imaging load 01 to rotate 34 times around its azimuth axis at 4°/s (from -170° to +170° relative to the preset original position), each rotation is 10° , each rotation time is

,

;

，

； The third movement form is the linkage between the azimuth axis and the pitch axis. The optical imaging payload 01 is to be supported and rotated 12 times around its azimuth axis and the pitch axis at 4°/s, each rotation is 10°, and the optical imaging payload 01 is to be supported each time. The rotation time is

,

;

， 输出时间

与旋转时间

之差即为该次旋转迟滞时间。 Step 4. Control the space star-borne expandable turntable mechanism to move according to the above-mentioned motion form, sense the motion through the micro-vibration test platform, output the induction signal, and record the output time of the induction signal for each rotation of each motion form

, the output time

and rotation time

The difference is the rotation delay time.

The above embodiments are only used to illustrate the technical solutions of the present invention, but not to limit them. For those of ordinary skill in the art, the specific technical solutions described in the foregoing embodiments can be modified, or part of the technical solutions can be modified. Features are equivalently replaced, and these modifications or replacements do not make the essence of the corresponding technical solution depart from the scope of the technical solution protected by the present invention.

Claims (10)

1. A space satellite-borne expandable turntable mechanism, characterized in that: it includes a base (1) and a support mechanism (3) arranged on the base (1), and the support mechanism (3) includes a first rotating arm (31 ), the second rotating arm (32), the deployment drive mechanism (33) and the mechanical locking mechanism (34); The first rotating arm (31) is arranged on the base (1), the rotating shaft of the first rotating arm (31) is perpendicular to the surface of the base (1), and the first rotating arm (31) can be relatively preset around its rotating shaft In situ rotation of ±170°, the azimuth axis to support the optical imaging load (01) coincides with the rotation axis of the first rotating arm (31); One end of the second rotating arm (32) is hinged to the end of the first rotating arm (31) through the unfolding drive mechanism (33), and the other end is connected to the optical imaging load (01) to be supported, and is provided with an optical imaging load (01) to be supported. The pitch axis of the imaging load (01); the deployment drive mechanism (33) includes a mounting shaft (331), a motor (332) arranged at one end of the mounting shaft (331), and the rotating shaft of the second rotating arm (32) Coinciding with the axis of the installation shaft (331), the second rotating arm (32) can rotate 90° around its rotating shaft; the pitch axis is perpendicular to the second rotating arm (32) and the rotating shaft of the second rotating arm (32); The mechanical locking mechanism (34) includes a position detection component (341), a first locking component (342) and a second locking component (343); the position detection component (341) is used to detect the second rotating arm (32) and the included angle between the first rotating arm (31), and when detecting that the included angle between the second rotating arm (32) and the first rotating arm (31) is 90°, the output signal is in place Give the second locking assembly (343); the second locking assembly (343) is used to fix the position of the second rotating arm (32) according to the signal in place; the first locking assembly (342) is used for Temporarily fix the position of the second rotating arm (32) before the second locking assembly (343) is fixed; The support mechanism (3) is provided with a folded state and an unfolded state; the support mechanism (3) is in the folded state, and the included angle between the second rotating arm (32) and the first rotating arm (31) is 0 °, the optical imaging load (01) to be supported is located under the second rotating arm (32), and the optical imaging load (01) to be supported is connected to the base (1); or, the support mechanism (3) is in an unfolded state, the The included angle between the second rotating arm (32) and the first rotating arm (31) is 90°, the optical imaging load (01) to be supported is separated from the base (1), and the second locking assembly (343) The position of the second rotating arm (32) is fixed. 2. The space-borne deployable turntable mechanism according to claim 1, characterized in that: the second locking assembly (343) includes a locking element arranged at the end of the first rotating arm (31) and close to the deploying drive mechanism. (33) the second locking and fixing part (3431), and the second locking and moving part (3432) provided on the second rotating arm (32), the second locking and fixing part (3431) and the first The included angle between the top surfaces of the rotating arms (31) is 90°. One end of the second locking moving part (3432) is hinged to the second rotating arm (32), and the other end can rotate around the hinge, and the supporting mechanism (3) In the unfolded state, that is, when the angle between the second rotating arm (32) and the first rotating arm (31) is 90°, it engages with the second locking and fixing part (3431). 3. A space satellite-borne deployable turntable mechanism according to claim 2, characterized in that: the position detection component (341) includes a second locking and fixing part (3431) close to the second rotating arm (32) ) Hall switch (3411) on one side, and the Hall magnet (3412) corresponding to the Hall switch (3411) arranged on the second rotating arm (32); the Hall switch (3411) is When the second rotating arm (32) rotates to an angle of 90° with the first rotating arm (31), it outputs an in-position signal; the first locking assembly (342) includes a second locking and fixing part ( 3431) close to the first electromagnet (3421) on the side of the second rotating arm (32), and the second electromagnet (3422) corresponding to the first electromagnet (3421) arranged on the second rotating arm (32) ). 4. A space starborne expandable turntable mechanism according to claim 3, characterized in that: the rotating end of the second locking moving part (3432) is provided with a first connecting piece (3433), and the second The rotating arm (32) is provided with a second connecting piece (3434) that can be engaged with the first connecting piece (3433). Separate from the second connector (3434). 5. A space starborne expandable turntable mechanism according to any one of claims 1 to 4, characterized in that: the end of the first rotating arm (31) is provided with a U-shaped hinge (311), U-shaped Both ends of the hinge part (311) are provided with a first through hole; the end of the first rotating arm (31) has a protruding part (321) adapted to the opening of the U-shaped hinge part (311), and the protruding part ( 321) is provided with a second through hole; the other end of the installation shaft (331) is provided with a torsion spring (333), and the installation shaft (331) includes a first transfer shaft connected to the motor (332) through a coupling And the second transfer shaft connected with the torsion spring (333), the first transfer shaft passes through the first through hole at one end of the U-shaped hinge (311), and the second transfer shaft passes through the U-shaped hinge (311) The first through hole at the other end, the first transfer shaft and the second transfer shaft are docked in the second through hole of the protrusion (321); the first transfer shaft, the second transfer shaft and the U-shaped hinge ( 311) An angular contact bearing (334) is arranged between the first through holes at both ends, the inner ring of the angular contact bearing (334) is provided with an inner pressure plate (335), and the outer ring is provided with an outer pressure plate (336). 6. A space starborne expandable turntable mechanism according to claim 5, characterized in that: said base (1) is provided with a fixing piece (2), and the fixing piece (2) is used to wear it in the folded state. The optical imaging load to be supported (01) is fixed on the base (1) through the fixing holes (02) on the optical imaging load to be supported (01). 7. A method for testing the hysteresis time of a space satellite-borne deployable turntable mechanism, characterized in that it is used for the space satellite-borne deployable turntable mechanism of claim 1, comprising the steps of: Step 1. Fix the space starborne expandable turntable mechanism on the micro-vibration test platform, make the support mechanism (3) in the unfolded state, and clean up objects that generate vibration and noise around the micro-vibration test platform; Step 2. After connecting the micro-vibration test platform and the micro-vibration host computer system, start the micro-vibration host computer system; Step 3, setting the motion form of the space starborne expandable turntable mechanism; The exercise forms include the following three types: The first type of movement is only the movement of the pitch axis, and the optical imaging load (01) to be supported rotates around its pitch axis several times at a preset speed, and the time of each rotation is T1 _; The second type of movement is only the movement of the azimuth axis, and the optical imaging load (01) to be supported rotates around its azimuth axis several times at a preset speed, and the time of each rotation is T ₂ ; The third form of movement is the linkage between the azimuth axis and the pitch axis. The optical imaging load (01) to be supported rotates around its azimuth axis and the pitch axis multiple times at a preset speed at the same time. The time for each rotation of the optical imaging load (01) to be supported is is T3 _; Step 4. Control the space starborne expandable turntable mechanism to move according to the movement form described in step 3, sense the movement through the micro-vibration test platform, output the induction signal, and record the output time T of the induction signal for each rotation of each movement form, Then the difference between the output time T and the rotation time T ₁ /T ₂ /T ₃ is the delay time of the rotation. 8. A method for testing the hysteresis time of a space-borne expandable turntable mechanism according to claim 7, characterized in that: in step 3, the first form of motion is specifically: to support the optical imaging load (01) Rotate 12 times around its pitch axis at a preset speed, each rotation is 10°, each rotation time is 2.5s, and the preset speed is 4°/s. 9. The method for testing the hysteresis time of a space-borne expandable turntable mechanism according to claim 8, characterized in that: in step 3, the second movement form is specifically: to support the optical imaging load (01) Rotate 34 times around its azimuth axis at a preset speed, each rotation is 10°, each rotation time is 2.5s, and the preset speed is 4°/s. 10. The method for testing the hysteresis time of a space-borne expandable turntable mechanism according to claim 9, characterized in that: in step 3, the third movement form is specifically: to support the optical imaging load (01) At the same time, it rotates 12 times around its azimuth axis and pitch axis at a preset speed, each rotation is 10°, and the optical imaging load (01) to be supported (01) rotates for 2.5s each time, and the preset speed is 4°/s.

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