Auxiliary support mechanism for space optical remote sensor

Abstract

The application relates to an auxiliary supporting mechanism of a space optical remote sensor, and relates to the technical field of remote sensor supporting mechanisms. The auxiliary supporting mechanism of the space optical remote sensor comprises a remote sensor and a base, a bolt connecting block one is fixed to the bottom of the remote sensor, a multichannel track groove is formed in the side surface of the base, a moving column is slidably connected in the multichannel track groove, and a plurality of buffer assemblies are arranged in the multichannel track groove in the base. The buffer assemblies are arranged to connect the remote sensor and the base, so that the remote sensor can be corrected in time and the protection effect is achieved when the base is vibrated due to external force or slides due to the inclination of the placing ground. Since the moving column is slidably connected in the multichannel track groove on the base and the multichannel track groove has a plurality of channels, the moving direction of the moving column is more, the protection direction is more extensive, and the protection effect on the remote sensor is better.

Description

Technical Field

[0001] This invention relates to the field of remote sensor support mechanism technology, specifically to an auxiliary support mechanism for aerospace optical remote sensors. Background Technology

[0002] With the rapid development of aerospace optical remote sensing technology, the requirements for the precision of camera optical systems are becoming increasingly stringent. To improve the precision of optical systems and reduce the impact of ground testing, launch phase vibrations, and on-orbit conditions, several methods have been proposed for the support structure of optical remote sensors, such as damping vibration reduction technology, flexible support technology, adaptive technology, and fully constrained technology. Damping vibration reduction technology utilizes various forms of damping structures in engineering practice to achieve vibration isolation and reduction effects. Flexible support and adaptive technologies utilize well-designed flexible elements to absorb vibrations and deformations, thereby reducing the impact of the external environment on the optical system. Fully constrained technology employs several sets of constraint mechanisms in combination to achieve full constraint of all six degrees of freedom, avoiding excessive constraints that could strain the optical system.

[0003] However, fully constrained and adaptive technologies are only applicable to on-orbit environments and are difficult to support optical remote sensors through ground testing, thus failing to meet the requirements of the launch environment. Summary of the Invention

[0004] Technical problem solved: In view of the shortcomings of the prior art, the present invention provides an auxiliary support mechanism for aerospace optical remote sensors, which solves the problems mentioned in the background art.

[0005] Technical Solution: To achieve the above objectives, the present invention is implemented through the following technical solution: an auxiliary support mechanism for an aerospace optical remote sensor, comprising a remote sensor and a base, wherein a bolt connecting block one is fixed to the bottom of the remote sensor, and a multi-channel track groove is formed on the side of the base, wherein a movable column is slidably connected inside the multi-channel track groove, and a bolt connecting block two is fixed to the end of the movable column away from the multi-channel track groove, the bolt connecting block two being connected to bolt connecting block one by bolts, and a plurality of buffer components are provided in the multi-channel track groove inside the base, wherein a total of six sets of buffer components are provided and evenly distributed inside the multi-channel track groove on the side of the base;

[0006] The buffer assembly includes a T-shaped slider and an arc-shaped elastic air tube. The T-shaped slider is slidably connected to the inside of a multi-channel track groove on the side of the base. A spring is fixed between the T-shaped slider and the inner wall of the multi-channel track groove. A resistance rod is fixed to the side of the T-shaped slider, and a resistance sleeve is slidably sleeved on the outside of the resistance rod. Both the resistance rod and the resistance sleeve are located in the middle of the spring. The arc-shaped elastic air tube is fixed to the side of the base, and a two-way jet pipe is fixed to the side of the arc-shaped elastic air tube. When the base vibrates due to external forces or slides due to tilting, the remote sensor can be corrected in time, providing a protective effect. Because the moving column is slidably connected to the multi-channel track groove on the base, and the multi-channel track groove has multiple channels, the moving column has multiple directions of movement, making its applicable protection direction wider and providing better protection for the remote sensor.

[0007] Preferably, the end of the resistance sleeve rod away from the resistance rod is connected to the outside, and the resistance sleeve rod connected to the outside is embedded in the interior of the base. The arc-shaped elastic air tube is usually made of hollow rubber tube, and the air outlet of the two-way air pipe is located below the T-shaped slider.

[0008] Preferably, a vibration protection device is provided on the side of the base away from the remote sensor. The vibration protection device includes a hexagonal connecting plate and contact components. The hexagonal connecting plate is fixed on the side of the base away from the remote sensor. An inflatable airbag is fixed on the side of the hexagonal connecting plate away from the base. There are six sets of contact components, all fixed on the side of the base. Each contact component includes a support block, which is fixed on the side of the base. A permanent magnet is fixed on the upper surface of the support block. Four pneumatic telescopic rods are fixed on the upper surface of the support block. A permanent magnet is fixed at the top of each of the four pneumatic telescopic rods. An annular pipe is embedded inside the support block. One end of the annular pipe is connected to the bottom of the multiple pneumatic telescopic rods. An L-shaped pipe is fixed at the other end of the annular pipe. The end of the L-shaped pipe away from the annular pipe is connected to the inflatable airbag. When vibration occurs, permanent magnet one will move closer to permanent magnet two. Since the magnetic poles of permanent magnet one and permanent magnet two are the same on the opposite side, a repulsive force will be generated when permanent magnet one and permanent magnet two approach each other, which plays a buffering and protective role. At the same time, by setting multiple pneumatic telescopic rods, gas will be transported into the expansion airbag through the annular pipe and L-shaped pipe during its contraction process, causing the expansion airbag to expand, increasing the friction with the placement area, and further improving the overall stability of the equipment.

[0009] Preferably, the second permanent magnet is shaped like a gyroscope and has a flat bottom, and the magnetic poles at the bottom of the second permanent magnet are the same as the magnetic poles at the top of the first permanent magnet.

[0010] Preferably, a plurality of deceleration components are provided between the remote sensor and the base. Six sets of deceleration components are evenly distributed on the outer side of the remote sensor. Each deceleration component includes a universal joint seat, with a universal joint first movably connected inside the universal joint seat. A support rod first is fixed on the universal joint first, and a support rod second is rotatably connected inside the support rod first via a torsion spring shaft. The end of the support rod second, away from the support rod first, is connected to the side of the remote sensor via the universal joint second. When the remote sensor moves on the base, the support rod first and support rod second in the deceleration components will move relative to each other, providing a reverse thrust under the action of the torsion spring shaft, thereby decelerating the remote sensor and further improving the overall stability of the equipment.

[0011] This invention provides an auxiliary support mechanism for aerospace optical remote sensors. It has the following beneficial effects:

[0012] (1) This application connects the remote sensor and the base by setting a buffer component. When the base vibrates due to external force or slides due to tilting, the remote sensor can be corrected in time and at the same time, it can play a protective role. Since the moving column is slidably connected in the multi-channel track groove on the base, and the multi-channel track groove has multiple channels, the moving column has many directions of movement, and its applicable protection direction is more extensive, and the protection effect on the remote sensor is better.

[0013] (2) This application provides vibration protection for the remote sensor by setting up a vibration protection device. When vibration occurs, permanent magnet one will move closer to permanent magnet two. Since the magnetic poles of permanent magnet one and permanent magnet two are the same on the opposite side, a repulsive force will be generated when permanent magnet one and permanent magnet two are close together, which will play a buffer protection role. At the same time, by setting up multiple pneumatic telescopic rods, gas will be transported into the expansion airbag through the annular pipe and L-shaped pipe during its contraction process, so that the expansion airbag expands, increases the friction with the placement area, and further improves the overall stability of the equipment.

[0014] (3) This application increases the sliding resistance between the remote sensor and the base by setting multiple deceleration components between the remote sensor and the base. When the remote sensor moves on the base, the support rod one and support rod two in the deceleration components will move relative to each other and provide a reverse thrust under the action of the torsion spring shaft, thereby decelerating the remote sensor and further improving the overall stability of the equipment. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall front-view three-dimensional structure of the present invention;

[0016] Figure 2 This is a schematic diagram of the overall three-dimensional side view of the present invention;

[0017] Figure 3This is a schematic diagram of the remote sensor and its connection structure of the present invention;

[0018] Figure 4 This is a schematic diagram showing the positional relationship between the base and its internal buffer components of the present invention;

[0019] Figure 5 This is a dual-view three-dimensional structural schematic diagram of the buffer component of the present invention;

[0020] Figure 6 This is a schematic diagram of the vibration protection device of the present invention;

[0021] Figure 7 This is a three-dimensional structural schematic diagram of the contact component of the present invention;

[0022] Figure 8 This is a three-dimensional structural schematic diagram of the deceleration component of the present invention.

[0023] In the diagram: 1. Remote sensor; 2. Base; 3. Buffer assembly; 31. T-shaped slider; 32. Arc-shaped elastic air tube; 33. Spring; 34. Resistance rod; 35. Resistance sleeve rod; 36. Two-way jet pipe; 4. Vibration protection device; 41. Hexagonal connecting plate; 42. Inflatable airbag; 43. Contact assembly; 44. Support block; 45. Permanent magnet one; 46. Pneumatic telescopic rod; 47. Permanent magnet two; 48. Annular pipe; 49. L-shaped pipe; 5. Deceleration assembly; 51. Universal joint seat; 52. Universal joint one; 53. Support rod one; 54. Support rod two; 55. Torsion spring pivot; 56. Universal joint two; 6. Bolt connection block one; 7. Moving column; 8. Bolt connection block two. Detailed Implementation

[0024] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0025] Please see Figure 1-8 The present invention provides a technical solution: an auxiliary support mechanism for an aerospace optical remote sensor, including a remote sensor 1 and a base 2. A bolt connecting block 6 is fixed to the bottom of the remote sensor 1. A multi-channel track groove is opened on the side of the base 2. A movable column 7 is slidably connected inside the multi-channel track groove. A bolt connecting block 8 is fixed to the end of the movable column 7 away from the multi-channel track groove. The bolt connecting block 8 is connected to the bolt connecting block 6 by bolts. A plurality of buffer components 3 are provided in the multi-channel track groove inside the base 2.

[0026] The buffer assembly 3 includes a T-shaped slider 31 and an arc-shaped elastic air tube 32. The T-shaped slider 31 is slidably connected to the inside of the multi-channel track groove on the side of the base 2. A spring 33 is fixed between the T-shaped slider 31 and the inner wall of the multi-channel track groove. A resistance rod 34 is fixed to the side of the T-shaped slider 31. A resistance sleeve 35 is slidably sleeved on the outside of the resistance rod 34. Both the resistance rod 34 and the resistance sleeve 35 are located in the middle of the spring 33. The end of the resistance sleeve 35 away from the resistance rod 34 is connected to the outside, and the resistance sleeve 35 connected to the outside is embedded in the inside of the base 2. The arc-shaped elastic air tube 32 is fixed to the side of the base 2. A two-way jet pipe 36 is fixed to the side of the arc-shaped elastic air tube 32. The arc-shaped elastic air tube 32 is usually made of hollow rubber tube. The jet port of the two-way jet pipe 36 is located below the T-shaped slider 31. The buffer assembly 3 has a total of six sets of multi-channel track grooves evenly distributed on the side of the base 2. This application connects the remote sensor 1 and the base 2 by setting a buffer component 3. When the base 2 vibrates due to external force or slides due to tilting, the remote sensor 1 can be corrected in time and a protective effect can be achieved. Since the moving column 7 is slidably connected in the multi-channel track groove on the base 2, and the multi-channel track groove has multiple channels, the moving column 7 has multiple directions of movement, and its applicable protection direction is wider, resulting in a better protection effect for the remote sensor 1.

[0027] Furthermore, a vibration protection device 4 is provided on the side of the base 2 away from the remote sensor 1. The vibration protection device 4 includes a hexagonal connecting plate 41 and contact components 43. The hexagonal connecting plate 41 is fixed on the side of the base 2 away from the remote sensor 1, and an inflatable airbag 42 is fixed on the side of the hexagonal connecting plate 41 away from the base 2. Six sets of contact components 43 are provided, all of which are fixed on the side of the base 2. The contact components 43 include a support block 44, which is fixed on the side of the base 2. A permanent magnet 45 is fixed on the upper surface of the support block 44. Four pneumatic telescopic rods 46 are fixed on the upper surface of the support block 44. A permanent magnet 47 is fixed at the top of the four pneumatic telescopic rods 46. An annular pipe 48 is embedded inside the support block 44. One end of the annular pipe 48 is connected to the bottom of the multiple pneumatic telescopic rods 46. An L-shaped pipe 49 is fixed at the other end of the annular pipe 48. The end of the L-shaped pipe 49 away from the annular pipe 48 is connected to the expansion airbag 42. The permanent magnet 47 is shaped like a gyroscope and its bottom is flat. The magnetic pole at the bottom of the permanent magnet 47 is the same as the magnetic pole at the top of the permanent magnet 45. This application provides vibration protection for the remote sensor 1 by setting a vibration protection device 4. When vibration occurs, the first permanent magnet 45 will move closer to the second permanent magnet 47. Since the magnetic poles of the first permanent magnet 45 and the second permanent magnet 47 are the same on the opposite side, a repulsive force will be generated when the first permanent magnet 45 and the second permanent magnet 47 approach each other, which will play a buffering and protective role. At the same time, by setting multiple pneumatic telescopic rods 46, gas will be transported into the expansion airbag 42 through the annular pipe 48 and the L-shaped pipe 49 during the contraction process, so that the expansion airbag 42 expands, increases the friction with the placement area, and further improves the overall stability of the equipment.

[0028] Furthermore, multiple speed reduction components 5 are provided between the remote sensor 1 and the base 2. Each speed reduction component 5 includes a universal joint 51, with a first universal joint 52 movably connected inside the universal joint 51. A first support rod 53 is fixed to the first universal joint 52, and a second support rod 54 is rotatably connected inside the first support rod 53 via a torsion spring shaft 55. The end of the second support rod 54 away from the first support rod 53 is connected to the side of the remote sensor 1 via a second universal joint 56. Six sets of speed reduction components 5 are provided and evenly distributed on the outer side of the remote sensor 1. This application increases the sliding resistance between the remote sensor 1 and the base 2 by providing multiple speed reduction components 5 between them. When the remote sensor 1 moves on the base 2, the first support rod 53 and the second support rod 54 in the speed reduction components 5 will move relative to each other, providing a reverse thrust under the action of the torsion spring shaft 55, thereby creating a speed reduction effect on the remote sensor 1 and further improving the overall stability of the equipment.

[0029] In use, the entire device is first placed in the placement area, so that the contact component 43 contacts the placement area. Then, when the base 2 vibrates due to external force or slides due to tilting of the placement, the moving column 7 is slidably connected to the multi-channel track groove on the base 2. Since the multi-channel track groove has multiple channels, the moving column 7 has multiple directions of movement, and its applicable protection direction is wider, resulting in better protection for the remote sensor 1. When the moving column 7 moves in any direction, it will compress the spring 33, which provides directional support force. At the same time, the resistance rod 34 slides in the resistance sleeve 35, providing friction. When a side collision occurs, the arc-shaped elastic air tube 32 will deform, and the gas inside it will be ejected through the two-way jet pipe 36, providing a reverse impact force to the T-shaped slider 31.

[0030] At the same time, when vibration occurs, permanent magnet 45 will move closer to permanent magnet 47. Since the magnetic poles of permanent magnet 45 and permanent magnet 47 are the same on the opposite side, a repulsive force will be generated when permanent magnet 45 and permanent magnet 47 approach each other, which plays a buffering and protective role. At the same time, by setting multiple pneumatic telescopic rods 46, gas will be transported into the expansion airbag 42 through the annular pipe 48 and L-shaped pipe 49 during its contraction, causing the expansion airbag 42 to expand, increasing the friction with the placement area, and further improving the overall stability of the equipment.

[0031] Subsequently, when the remote sensor 1 moves on the base 2, the support rod 53 and support rod 54 in the deceleration assembly 5 will move relative to each other, providing a reverse thrust under the action of the torsion spring shaft 55, thereby decelerating the remote sensor 1 and further improving the overall stability of the equipment.

[0032] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. An auxiliary support mechanism for an aerospace optical remote sensor, comprising a remote sensor (1) and a base (2), characterized in that: The bottom of the remote sensor (1) is fixed with a bolt connecting block one (6). The side of the base (2) has a multi-channel track groove. The inside of the multi-channel track groove is slidably connected with a moving column (7). The end of the moving column (7) away from the multi-channel track groove is fixed with a bolt connecting block two (8). The bolt connecting block two (8) is connected to the bolt connecting block one (6) by bolts. The multi-channel track groove inside the base (2) is provided with multiple buffer components (3). The buffer assembly (3) includes a T-shaped slider (31) and an arc-shaped elastic air tube (32). The T-shaped slider (31) is slidably connected to the inside of the multi-channel track groove on the side of the base (2). A spring (33) is fixed between the T-shaped slider (31) and the inner wall of the multi-channel track groove. A resistance rod (34) is fixed to the side of the T-shaped slider (31). A resistance sleeve rod (35) is slidably sleeved on the outside of the resistance rod (34). The resistance rod (34) and the resistance sleeve rod (35) are both located in the middle of the spring (33). The arc-shaped elastic air tube (32) is fixed to the side of the base (2). A two-way jet pipe (36) is fixed to the side of the arc-shaped elastic air tube (32). The arc-shaped elastic air tube (32) is made of hollow rubber tube. The jet nozzle of the two-way jet pipe (36) is located below the T-shaped slider (31). A vibration protection device (4) is provided on the side of the base (2) away from the remote sensor (1). The vibration protection device (4) includes a hexagonal connecting plate (41) and a contact assembly (43). The hexagonal connecting plate (41) is fixed on the side of the base (2) away from the remote sensor (1). An inflatable airbag (42) is fixed on the side of the hexagonal connecting plate (41) away from the base (2). There are six sets of contact assemblies (43), all of which are fixed on the side of the base (2). The contact assembly (43) includes a support block (44). The support block (44) is fixed on the side of the base (2). A permanent magnet (45) is fixed on the upper surface of the support block (44). Four pneumatic telescopic rods (46) are fixed on the upper surface of the support block (44). A permanent magnet (47) is fixed at the top of each of the four pneumatic telescopic rods (46). An annular pipe (48) is embedded inside the support block (44). One end of the annular pipe (48) is connected to the bottom of the multiple pneumatic telescopic rods (46). An L-shaped pipe (49) is fixed at the other end of the annular pipe (48). The end of the L-shaped pipe (49) away from the annular pipe (48) is connected to the inflatable airbag (42). The permanent magnet (47) is gyroscope-shaped and its bottom is flat. The magnetic pole at the bottom of the permanent magnet (47) is the same as the magnetic pole at the top of the permanent magnet (45).

2. The aerospace optical remote sensor auxiliary support mechanism according to claim 1, characterized in that: The buffer assembly (3) is provided with six sets of multi-channel track grooves evenly distributed on the side of the base (2).

3. The aerospace optical remote sensor auxiliary support mechanism according to claim 1, characterized in that: The end of the resistance sleeve (35) away from the resistance rod (34) is connected to the outside, and the resistance sleeve (35) connected to the outside is embedded in the base (2).

4. The aerospace optical remote sensor auxiliary support mechanism according to claim 1, characterized in that: Multiple deceleration components (5) are provided between the remote sensor (1) and the base (2). The deceleration components (5) include a universal joint seat (51). A universal joint first (52) is movably connected inside the universal joint seat (51). A support rod first (53) is fixed on the universal joint first (52). A support rod second (54) is rotatably connected inside the support rod first (53) through a torsion spring shaft (55). The end of the support rod second (54) away from the support rod first (53) is connected to the side of the remote sensor (1) through a universal joint second (56).

5. The aerospace optical remote sensor auxiliary support mechanism according to claim 4, characterized in that: The deceleration components (5) are arranged in six groups and are evenly distributed on the outside of the remote sensor (1).

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