Small-size on-board camera unloading mechanism convenient to operate and controllable in force

Abstract

The invention provides a small-size convenient-to-operate force-controllable satellite camera unloading mechanism, which comprises a pulley transmission part, a truss supporting part, a force applying and measuring part, a rope and mechanism fixing part and a rope part, and is characterized in that the rope part is mounted on a camera structure through a lifting bolt; the rope and mechanism fixing part is installed on a satellite cabin plate, a rotating shaft of the force applying and measuring part is rotated, a rope can be tensioned to unload a camera, the pulley transmission part can adjust the direction of unloading force, and the truss supporting part can adjust the space distance between the camera and an operable part of the satellite cabin plate. And a spring and a sensor are arranged in the force application test part, so that the unloading force can be accurately controlled. According to the mechanism, the gravity influence after a camera is mounted on a satellite can be reduced to the greatest extent in the environment of a ground gravity field, and meanwhile, the mechanism is small in structural size, easy to operate, controllable in force and excellent in engineering property.

Description

TECHNICAL FIELD

[0001] The application relates to a small-volume and easily-operated on-satellite camera unloading mechanism, and belongs to the technical field of spaceflight. BACKGROUND

[0002] With the development of space remote sensing cameras, the resolution required by the cameras is higher and higher, and the weight and volume are smaller and smaller, so the stability of the optical-mechanical structure is higher than that of other cameras of the same type, and therefore the camera is required to avoid producing an unrecoverable (or very slow recovery) surface shape or position influence during the whole implementation process. After the camera is installed on a satellite, the satellite is assembled and tested, and the satellite cannot be ensured to be always in a 'comfortable' state of the camera. According to analysis, when the camera is connected with the satellite through a damping truss and is placed horizontally along the optical axis (i.e. cantilevered), the mirror surface shape will deteriorate, and the stress distribution of damping glue inside the damping truss is uneven, which not only has an influence on the on-orbit imaging quality of the camera, but also has an influence on stress suppression in the vibration test, and therefore it is very necessary to apply a gravity unloading on the camera on the ground to reduce the influence of gravity on the camera.

[0003] After the camera is installed on the satellite, when the satellite is turned over for test, only a small-volume and easily-operated on-satellite camera unloading mechanism is needed to be installed on the outer surface of the satellite cabin panel and connected with the unloading rope embedded on the camera, and through the rotation of the rotating shaft of the force applying and measuring part in the rotating mechanism, the rope can be tensioned to realize accurate unloading of the camera, so that the influence of gravity on the camera after the camera is installed on the satellite can be reduced to the maximum extent in the gravity field on the ground. The whole mechanism greatly compresses the three-dimensional size, so that the mechanism can be installed on the satellite cabin panel and in the narrow space under the solar wing. All the operation parts are located at the edge of the satellite cabin panel, so that the operation is convenient and the whole operation process is simple and controllable.

[0004] At present, the gravity unloading mechanism disclosed in the Chinese patent 'CN202624651 U Space Microwave Radar Servo Mechanism Ground Experiment Gravity Unloading Device' has the same application field as the present application, but the size of the device of CN202624651 U is relatively large and the mechanism is complex, so the device is not suitable for applying force on the internal camera by being installed on the satellite cabin panel. SUMMARY

[0005] The technical problem to be solved by the present application is to overcome the shortcomings of the prior art, and to provide a small-volume and easily-operated on-satellite camera unloading mechanism, which can reduce the influence of the ground gravity on the imaging quality of the camera by applying force on the camera.

[0006] The technical solution of the present application is:

[0007] The application discloses a small-size on-orbit camera unloading mechanism with controllable operation strength, which comprises a pulley transmission part, a truss support part, a force applying and measuring part, a rope and a mechanism fixing part and a rope part.

[0008] The pulley transmission part comprises two groups of pulleys.

[0009] The rope part comprises a rope and a lifting ring screw, wherein the rope passes through the lifting ring screw, and the lifting ring screw is fixed on the camera.

[0010] The rope and mechanism fixing part is fixedly installed on a cabin plate of a satellite body, connected with one end of the force applying and measuring part, and connected with one end of the rope passing through one group of pulleys.

[0011] The other end of the force applying and measuring part is connected with the other end of the rope passing through the other group of pulleys, and the pulleys guide the rope.

[0012] The truss support part is connected with the pulley transmission part and the rope and mechanism fixing part at two ends respectively.

[0013] Further, in the above mechanism, the pulley transmission part further comprises a shaft check ring, a pulley shaft, a deep groove ball bearing, a pulley seat, a protection cover, a rope limiting part and a positioning pin, wherein

[0014] The two deep groove ball bearings, the positioning pin and the rope limiting part are installed on the pulley seat.

[0015] Each pulley is erected on the pulley shaft through two deep groove ball bearings, and the pulley shaft is fixed on the pulley seat.

[0016] One end of the pulley shaft is limited by the shaft check ring.

[0017] The rope limiting part is provided with a front turning guide hole and a rear turning guide hole to constrain the direction of the rope, and the positioning pin realizes the positioning of the unloading mechanism relative to the satellite cabin plate.

[0018] Two protection covers are fixed on the pulley seat to protect the solar wing and the satellite cabin plate.

[0019] Further, in the above mechanism, the truss support part comprises a joint assembly and a truss rod, wherein

[0020] Two joint assemblies are connected with two ends of the truss rod respectively.

[0021] The joint assembly comprises a truss screw, a truss rod joint and a joint screw.

[0022] The truss rod is connected with the truss rod joint through the joint screw and epoxy glue.

[0023] The truss rod joint realizes the butt joint of the pulley transmission part and the rope and mechanism fixed part through the truss screw.

[0024] The space distance between the camera unloading part and the satellite cabin plate operation part is arranged by adjusting the length of the truss rod.

[0025] Further, in the above mechanism, the truss rod is a circular hollow aluminum pipe; the gap between the truss rod joint and the truss rod is 0.05mm-0.15mm.

[0026] Further, in the above mechanism, the force measuring part includes a spring, a ring screw, a moving shaft, a rotating shaft, a sleeve, a sleeve plug, a tension sensor, and a sleeve screw.

[0027] The spring, the ring screw, the tension sensor, and the moving shaft are connected in series to form a series component.

[0028] The rotating shaft is sleeved on the moving shaft.

[0029] The series component is placed in the sleeve and sealed with the sleeve plug.

[0030] The sleeve plug is provided with a through hole, and the rope is connected with the spring through the through hole.

[0031] The sleeve is installed on the rope and mechanism fixed part through the sleeve screw.

[0032] The rotating shaft is rotated manually or by a tool to realize the translation of the moving shaft, thereby realizing the pre-tightening of the spring, and the tension sensor collects the pre-tightening force.

[0033] Further, in the above mechanism, by rotating the rotating shaft, the moving shaft is translated, the spring is tensioned, the rope is tensioned, and the camera applies an unloading force; the rotating shaft is tightened in the opposite direction, the pre-tightening force of the spring drives the moving shaft to move in the opposite direction, the rope is relaxed, and the unloading force of the camera becomes smaller to zero.

[0034] Further, in the above mechanism, the rope and mechanism fixed part includes a rope pressing block, a rope limiting part, a fixed seat, a protective sleeve, a pressing block modified screw, a screw ring, and a fixed seat modified screw.

[0035] The rope pressing block, the rope limiting part, and the protective sleeve are all installed on the fixed seat.

[0036] The pressing block modified screw fixes the rope on the fixed seat through the rope pressing block.

[0037] The fixed seat modified screw fixes the fixed seat on the star cabin plate.

[0038] The moving shaft passes through the hole in the fixed seat and is connected with the rotating shaft.

[0039] Further, in the above mechanism, the rope adopts aramid rope; the two ends of the single rope adopt splicing form.

[0040] Further, in the above mechanism, the rope block is internally designed as a cavity structure, a screw ring is installed on a block modified screw, and after the threaded segment of the block modified screw is rotated, the screw ring is axially limited, and moves to the upper limit position in the cavity and then stops.

[0041] Further, in the above mechanism, the volume is less than 300mm*80mm*60mm.

[0042] The beneficial effects of the present application over the prior art are:

[0043] (1) The ground gravity unloading device for space remote sensing high-resolution cameras provided by the present application has the advantages of simple structure, convenient installation, reliable use, easy operation, controllable force, and the like.

[0044] (2) The force control sensor can detect the size of the unloading force, the pulley and the truss rod can change the direction of the unloading force, the deep groove ball bearing is used to set up the pulley to reduce the relative movement of the frictionless rope, and the anti-falling screw design makes the operation of the mechanism on the satellite safer and more reliable.

[0045] (3) The use of the ground gravity unloading device for space remote sensing high-resolution cameras provided by the present application reduces the cantilever deformation of the camera on the satellite, and effectively guarantees the in-orbit imaging quality of the camera.

[0046] (4) The entire structure of the present application can realize the position adjustment and positioning of the camera relative to the satellite through the pulley turning and the truss rod length extension design of the mechanism itself without changing the satellite cabin plate and camera layout, and the precise control of the unloading force can be realized through the detection of the tension sensor.

[0047] (5) The parts in each component used in the present application can be realized by ordinary machining or purchasing ready-made standard parts, the part machining process performance is good, and the present application does not involve circuit design and control, so the cost is low and the maintenance is easy.

[0048] (6) The pulley of the present application is set up by a deep groove ball bearing to realize the frictionless relative movement of the rope, and the precision of the force control is improved.

[0049] (7) The operation screws of the present application are designed to be anti-falling to avoid the screw falling during the operation process. Attached Figure Description

[0050] Figure 1 This is a structural diagram of the on-board unloading mechanism of the present invention;

[0051] Figure 2 This is a cross-sectional view of the on-board unloading mechanism of the present invention.

[0052] Figure 3 This is a schematic diagram of the pulley transmission part 1 of the present invention;

[0053] Figure 4 This is a cross-sectional view showing the connection relationship of the truss support portion 2 of the present invention;

[0054] Figure 5 This is a cross-sectional view showing the connection relationship of the force-applying and force-measuring part 3 of the present invention;

[0055] Figure 6 This is a cross-sectional view of the connection relationship of the rope and mechanism fixing part 4 of the present invention;

[0056] Figure 7 This is a cross-sectional view of the anti-loosening design of the four screws for the fixing part of the rope and mechanism of the present invention. Detailed Implementation

[0057] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0058] like Figure 1 As shown, this invention provides a compact, easy-to-operate, and force-controllable unloading mechanism for an onboard camera, comprising: a pulley transmission part 1, a truss support part 2, a force application and measurement part 3, a rope and mechanism fixing part 4, and a rope part 5; wherein,

[0059] like Figure 2 As shown, the rope part 5 is connected in series with the pulley transmission part 1, the force application and measurement part 3, and the rope and mechanism fixing part 4;

[0060] The two ends of the truss support part 2 are respectively connected to the pulley transmission part 1 and the rope and mechanism fixing part 4;

[0061] The force-applying and force-measuring part 3 is installed on the rope and mechanism fixing part 4;

[0062] The rope section 5 is directly connected to the camera to unload the camera;

[0063] The rope and mechanism fixing part 4 are installed on the capsule of the star to fix the entire mechanism.

[0064] like Figure 3As shown, the pulley transmission part 1 comprises shaft check ring 11, pulley shaft 12, deep groove ball bearing 13, pulley seat 14, protective cover 15, pulley 16, rope limiting 17, positioning pin 18; wherein,

[0065] The two groups of deep groove ball bearings 13, positioning pins 18, protective covers 15 and rope limiters 17 are all installed on the pulley seat 14;

[0066] The pulley shaft 12 is installed on the two groups of deep groove ball bearings 13 and is axially limited by the shaft check ring 11.

[0067] The pulley transmission part 1 adopts a double-bearing pulley set design to realize the reciprocating path of the unloaded rope 51, one end of which is connected to the spring 21 of the force testing part 3, the rope 51 is guided through the pulley 16, passes through the camera connection part, bypasses the other group of pulleys 16, and the other end of the rope 51 is connected to the rope and mechanism fixing part 4 for fixing. The pulley transmission part adopts deep groove bearings 13 for support to reduce the loss of force on the rope. In order to better constrain the direction of the rope 51, the rope limiter 17 is provided, and the turning front guide hole and the turning rear guide hole are designed on the limiting structure. In order to better limit the unloaded part of the camera, the non-metal positioning pin 18 is provided on the pulley transmission part 1 for positioning, which can realize the positioning of the unloaded mechanism relative to the satellite cabin plate.

[0068] Two groups of movable pulleys 16 are arranged on the pulley seat 14 through the space rope position, each pulley is erected on the pulley shaft 12 through a group of deep groove ball bearings 13, the pulley shaft 12 is fixed on the pulley seat 14, and the other end of the pulley shaft 12 is limited by the shaft check ring 11. Small gap fit is adopted between the pulley shaft 12 and the deep groove ball bearing 13. In order to better protect the solar wing and the satellite cabin plate, the non-metal upper and lower protective covers 15 are fixed on the pulley seat 14.

[0069] As shown, Figure 4 The truss support part 2 comprises truss screw 21, truss rod joint 22, joint screw 23, truss rod 24; wherein,

[0070] The truss support part is a symmetrical structure, and the truss rod 24 is connected with the truss rod joint 22 through the joint screw 23 and epoxy glue;

[0071] The truss rod joint 22 realizes the butt joint of the pulley transmission part 1 and the rope and mechanism fixing part 4 through the truss screw 21.

[0072] The truss support part 2 connects the rope and mechanism fixed part 4 and the pulley transmission part 1, and the truss support part 2 adjusts the length of the truss rod 24 to accurately arrange the spatial distance between the camera unloading part and the satellite cabin plate operation part. The truss rod 24 unit adopts a circular hollow aluminum pipe to reduce the weight and cost of the whole machine mechanism. The gap between the truss rod joint 22 and the truss rod 24 is 0.1mm, and the connection adopts a gap joint. The upper connection adopts a glue joint + joint screw 23 double connection form. The truss rod joint 22 is provided with a threaded hole, and the truss rod 24 is provided with a light hole, and the two are screwed through the joint screw 23. One end of the truss support part 2 is connected to the pulley seat 14 through three groups of truss screws 21, and the other end is connected to the fixed seat 43 through three groups of truss screws 21.

[0073] As shown in Figure 5 The force measuring part 3 includes a spring 31, a ring screw 32, a moving shaft 33, a rotating shaft 34, a sleeve 35, a sleeve plug 36, a tension sensor 37, and a sleeve screw 38.

[0074] The spring 31, the ring screw 32, the tension sensor 37, the moving shaft 33, and the rotating shaft 34 are connected in series.

[0075] The above-mentioned series parts are placed in the sleeve 35, and the sleeve plug 36 is used for edge sealing.

[0076] The sleeve screw 38 is installed on the rope and mechanism fixed part 4 to fix the force measuring part 3.

[0077] The force applying and measuring part 3 is used to apply and control the unloading force of the camera. The spring 31 and the tension sensor 37 are arranged in the force applying and measuring part 3. The translation of the moving shaft 33 can be realized by rotating the rotating shaft 34 manually or by a tool, so as to realize the pre-tightening of the spring 31. The spring 31 is a common cylindrical helical tension spring. One end of the spring 31 is connected to the unloading rope 51, and the other end of the spring 31 is connected to the tension sensor 37 through the lifting ring screw 32. The range and accuracy of the tension sensor 37 are selected according to the requirement of the unloading force of the camera. The tension sensor 37 is connected to the moving shaft 33 through screw thread. The moving shaft 33 is designed in a "racetrack type" with external thread. The moving shaft 33 is connected to the rotating shaft 34 through the "racetrack type" hole of the fixing seat 43. The external surface of the rotating shaft 34 is provided with knurling, which facilitates manual operation. The rotating of the rotating shaft 34 drives the translation of the moving shaft 33 in the fixing seat 43, so as to pre-tighten the spring 31. The pre-tightening force is monitored by the tension sensor 37. The whole movable device is placed in the sleeve 35, which plays a protection role. The sleeve 35 is designed with an opening for leading the lead wire of the tension sensor 37 and an operation opening for hooking the rope 51 to the spring 31. One end of the sleeve 35 is installed on the fixing seat 43 through the three sleeve screws 38, and the other end of the sleeve 35 is cantilevered. The rope 51 and the spring 31 are limited by the sleeve plug 36, which is adhered to the end of the sleeve 35 by epoxy glue.

[0078] As shown in Figure 6 the rope and mechanism fixing part 4 comprises a rope pressing block 41, a rope limiting part 42, a fixing seat 43, a protection sleeve 44, a pressing block modification screw 45, a screw ring 46 and a fixing seat modification screw 47. The rope pressing block 41, the rope limiting part 42 and the protection sleeve 44 are installed on the fixing seat 43. The pressing block modification screw 45 fixes the rope 51 on the fixing seat 43 through the rope pressing block 41. The fixing seat modification screw 47 fixes the whole mechanism on the starboard of the spacecraft.

[0079] The rope pressing block 41, the rope limiting part 42 and the protection sleeve 44 are installed on the fixing seat 43.

[0080] The pressing block modification screw 45 fixes the rope 51 on the fixing seat 43 through the rope pressing block 41.

[0081] The fixing seat modification screw 47 fixes the whole mechanism on the starboard of the spacecraft.

[0082] The moving shaft 33 passes through the hole of the fixing seat 43 and is connected to the rotating shaft 34.

[0083] The rope and mechanism fixing part 4 serves as the interface between the entire mechanism and the satellite module. The main structure is the fixing base 43. The upper part of the rope 51 passes through the rope limiter 42. A small U-shaped gap is left between the rope clamping block 41 and the fixing base 43, through which the rope passes. The rope clamping block 41 is pressed down by tightening the clamping block modification screw 45, thereby fixing this end of the rope 51. The lower end of the fixing base 43 is connected to the satellite module via a fixing base modification screw 47. Both the clamping block modification screw 45 and the fixing base modification screw 47 are designed to prevent detachment.

[0084] like Figure 1 As shown, the rope portion 5 includes: a rope 51 and a lug screw 52; wherein,

[0085] The rope 51 passes through the eye bolt 52, which is fixed to the camera.

[0086] The rope section 5 connects the entire mechanism to the corresponding unloading point on the camera via an unloading rope. Eye bolts 52 need to be installed on the camera unloading point beforehand, and the rope 51 applies force for unloading through these eye bolts. The rope 51 used is a high-strength, low-creep aramid rope. The load-bearing capacity of a single rope can be selected according to the camera's unloading force requirements; generally, the load-bearing capacity of a single rope is greater than 100 kg. The rope ends are connected by a plug-in joint to improve connection reliability and facilitate the rope's insertion between different structural components and its connection to the spring 31.

[0087] like Figure 7 As shown, the screw 45 is modified by a pressure block to make a smooth section. At the same time, the rope pressure block 41 is designed to be hollow. A standard screw retainer 46 is installed on the screw smooth section. After the modified screw 45 rotates the threaded section, it is restricted by the axial direction of the retainer and can only move to the upper limit of the retainer in the cavity. It cannot come out, thus avoiding the screw from falling into the planetary body and causing foreign objects during the screw operation.

[0088] One end of rope 51 is fixed to the fixed base 43. Rope 51 passes through rope limit 17, pulley 16, rope limit 17, camera eye bolt 52, rope limit 17, pulley 16, rope limit 17, sleeve plug 36, and spring 31. Rotating the rotating shaft 34 causes the moving shaft 33 to move horizontally, increasing the force on spring 31 and tightening rope 51, thus applying unloading force to the camera. Tightening the rotating shaft 34 in the opposite direction causes the spring 31 to move horizontally in the opposite direction, slackening rope 51 and reducing the camera unloading force to zero. Finally, when dismantling the entire device, loosening the pressure block modification screw 45 loosens rope 51, allowing it to be removed along with the unloading device.

[0089] The ground gravity unloading device for space remote sensing high-resolution camera greatly compresses the three-dimensional size of the mechanism, and the size of the complete mechanism is less than 300mm*80mm*60mm, which can be placed in the gap between the satellite cabin plate and the solar wing. Through the structure and lightweight and material selection design, the weight of the complete mechanism is controlled within 2kg, facilitating manual installation operation.

[0090] The truss support part 2 realizes the adjustable space distance between the camera and the satellite cabin plate operable part, and the long-distance connection design is realized by adopting the truss rod 24.

[0091] The spring 31 and the tension sensor 37 arranged in the force applying and measuring part 3 can realize the accurate and controllable unloading force. The translation is realized by rotating the rotating shaft 34 manually or by tools, so as to realize the pre-tightening of the spring 31. The sleeve 35 design protects the whole mechanism from the solar wing of the whole satellite.

[0092] The rope and mechanism fixing part 4 can fix one end of the rope 51 and connect the whole mechanism to the satellite cabin plate, and all the operable screws are designed to prevent falling off.

[0093] The complete mechanism greatly compresses the three-dimensional size, so that the mechanism can be installed on the satellite cabin plate and under the solar wing.

[0094] All the operation parts are located on the edge of the satellite cabin plate, which is convenient for operation, and the whole operation process is simple and controllable.

[0095] A non-metal protective sleeve is designed on the mechanism, which can effectively prevent the bumping of the solar wing during installation and removal. All the contacts with the satellite cabin plate are non-metal materials, which can prevent the bumping of the cabin plate during installation or separation to generate redundant materials.

[0096] All the operation screws on the mechanism are designed to be clamped to prevent the screws from falling off and generating redundant materials.

[0097] The force applying process on the mechanism only needs to rotate the rotating shaft 34, and the force releasing process only needs to loosen the screw, which is easy to operate.

[0098] During the removal process of the mechanism, one end of the rope is loosened, and the other end can be withdrawn with the mechanism, without leaving redundant ropes on the camera.

[0099] The unloading force can be diverted and the camera unloading position can be adjusted. It can be popularized to other applications.

[0100] The content not described in detail in the specification of the present application is the known technology of the person skilled in the art. Although the specific embodiments of the present application are described in the structural drawings, the person skilled in the art can make several modifications, substitutions and improvements without departing from the present application, and these are also considered to belong to the protection scope of the present application.

[0101] Although the content of the present application has been described in detail by the above preferred embodiments, it should be recognized that the above description should not be considered as a limitation of the present application. After reading the above content, various modifications and substitutions of the present application will be obvious to the person skilled in the art. Therefore, the protection scope of the present application should be defined by the appended claims.

[0102] The content not described in detail in the specification of the present application is the known technology of the person skilled in the art.

Claims

1. A compact, easy-to-operate, and force-controllable unloading mechanism for an onboard camera, characterized in that: include: The components include: a pulley drive section (1), a truss support section (2), a force application and measurement section (3), a rope and mechanism fixing section (4), and a rope section (5); among which, The pulley transmission part (1) includes two sets of pulleys (16); The rope portion (5) includes: a rope (51) and a lug screw (52); the rope (51) passes through the lug screw (52); the lug screw (52) is fixed to the camera; The rope and mechanism fixing part (4) is fixedly installed on the cabin plate of the star body, connected to one end of the force measuring part (3), and connected to one end of the rope (51) that passes through a set of pulleys (16); The other end of the force-applying and force-measuring part (3) is connected to the other end of the rope (51) that passes through another set of pulleys (16); the pulleys (16) guide the rope (51); The two ends of the truss support part (2) are respectively connected to the pulley transmission part (1) and the rope and mechanism fixing part (4).

2. The small-volume, easy-to-operate, and force-controllable on-board camera unloading mechanism according to claim 1, characterized in that, The pulley transmission part (1) further includes a shaft retaining ring (11), a pulley shaft (12), a deep groove ball bearing (13), a pulley seat (14), a protective cover (15), a rope limiter (17), and a positioning pin (18); wherein, The two deep groove ball bearings (13), the locating pins (18), and the rope limiter (17) are all mounted on the pulley seat (14); Each pulley (16) is mounted on the pulley shaft (12) by two deep groove ball bearings (13); the pulley shaft (12) is fixed on the pulley seat (14); One end of the pulley shaft (12) is limited by a retaining ring (11); The rope limiter (17) is provided with a guide hole before turning and a guide hole after turning to constrain the direction of the rope (51); the positioning pin (18) realizes the positioning of the unloading mechanism relative to the satellite cabin plate. Two protective covers (15) are fixed to the pulley base (14) to protect the solar panels and satellite cabin panels.

3. The on-board camera unloading mechanism with small size, easy operation, and controllable force as described in claim 1, characterized in that, The truss support portion (2) includes: a joint assembly and truss rods (24); wherein, The two joint assemblies are respectively connected to both ends of the truss rod (24); The joint assembly includes a truss screw (21), a truss rod joint (22), and a joint screw (23); Truss members (24) are connected to truss member joints (22) by joint screws (23) and epoxy adhesive; The truss rod joint (22) connects the pulley transmission part (1) and the rope and mechanism fixing part (4) through the truss screw (21); The spatial distance between the camera unloading area and the satellite panel operation area is determined by adjusting the length of the truss rod (24).

4. The small-volume, easy-to-operate, and force-controllable on-board camera unloading mechanism according to claim 3, characterized in that, The truss rod (24) is made of circular hollow aluminum tube; the truss rod joint (22) and the truss rod (24) are fitted with a shaft hole clearance of 0.05mm to 0.15mm.

5. The small-volume, easy-to-operate, and force-controllable unloading mechanism for an onboard camera according to claim 1, characterized in that, The force-applying and force-measuring part (3) includes: a spring (31), a lifting eye screw (32), a moving shaft (33), a rotating shaft (34), a sleeve (35), a sleeve plug (36), a tension sensor (37), and a sleeve screw (38); wherein, The spring (31), eye bolt (32), tension sensor (37), and moving shaft (33) are connected in series to form a series component; The rotating shaft (34) is sleeved on the outside of the moving shaft (33); The tandem component is placed inside the sleeve (35) and sealed with a sleeve plug (36); The sleeve plug (36) is provided with a through hole, and the rope (51) is connected to the spring (31) through the through hole; The sleeve (35) is installed on the rope and mechanism fixing part (4) by the sleeve screw (38); The rotating shaft (34) is rotated manually or with a tool to realize the translation of the moving shaft (33), thereby realizing the pre-tension of the spring (31), and the tension sensor (37) collects the pre-tension force.

6. The on-board camera unloading mechanism with small size, easy operation, and controllable force according to claim 5, characterized in that, By rotating the rotating shaft (34), the moving shaft (33) is driven to move horizontally, the spring (31) is stressed, the rope (51) is tightened, and the camera is subjected to unloading force; by tightening the rotating shaft (34) in the opposite direction, the preload of the spring (31) drives the moving shaft (33) to move horizontally in the opposite direction, the rope (51) is relaxed, and the camera unloading force is reduced to zero.

7. A small-volume, easy-to-operate, and force-controllable unloading mechanism for an onboard camera according to claim 5, characterized in that, The rope and mechanism fixing part (4) includes: a rope clamp (41), a rope limiter (42), a fixing seat (43), a protective sleeve (44), a clamp modification screw (45), a screw retainer (46), and a fixing seat modification screw (47); wherein, The rope clamp (41), rope limiter (42), and protective sleeve (44) are all installed on the fixed base (43); The modified screw (45) of the pressure block fixes the rope (51) to the fixing seat (43) through the rope pressure block (41); The mounting bracket modification screw (47) fixes the mounting bracket (43) to the star body panel; The movable shaft (33) passes through a hole in the fixed base (43) and is connected to the rotating shaft (34).

8. The on-board camera unloading mechanism with small size, easy operation, and controllable force according to claim 1, characterized in that, The rope (51) is made of aramid fiber; the two ends of a single rope (51) are connected by a plug.

9. A small-volume, easy-to-operate, force-controllable on-board camera unloading mechanism according to claim 6, characterized in that, The rope clamp (41) is designed with a cavity structure. A screw retainer (46) is installed on the clamp modified screw (45). After the screw modified screw (45) rotates the threaded section, it is axially restricted by the retainer and stops after moving to the upper limit of the screw retainer (46) in the cavity.

10. A small-volume, easy-to-operate, force-controllable on-board camera unloading mechanism according to claim 1, characterized in that, The volume is less than 300mm×80mm×60mm.

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