A regulating device and a satellite

Abstract

The application relates to the technical field of satellite adjustment, and provides an adjusting device and a satellite, which comprise a adjusting component movably connected to the satellite, the adjusting component comprises: a blocking member comprising a first shell and a first deformation structure, the first shell is provided with a first containing cavity and a first opening communicated with the first containing cavity, the first deformation structure is at least partially installed in the first containing cavity, and the middle part of the first deformation structure can be deformed in a direction away from the first opening relative to the first shell; at least two driving members are respectively connected to the two ends of the blocking member along a first direction, each driving member comprises a second shell connected to the first shell and a second deformation structure, the second shell is provided with a second containing cavity and a second opening communicated with the second containing cavity, and one end of the second deformation structure is installed in the second containing cavity; and a heating member is arranged on the first deformation structure and the second deformation structure. Through the technical scheme, the adjusting efficiency of the adjusting device is improved.

Description

Technical Field

[0001] This invention relates to the field of satellite control technology, and more specifically, to a control device and a satellite. Background Technology

[0002] During satellite operation, the position of its center of mass will change due to fuel consumption, propellant gas removal, and the deployment of large onboard structures. This shift in the positions of the center of mass and centroid will affect the satellite's normal operation. To ensure that the satellite's center of mass and centroid remain relatively aligned, a satellite center of mass adjustment system needs to be designed.

[0003] In related technologies, a lead screw guide mechanism is usually used to adjust the center of mass of a satellite. However, the lead screw guide mechanism is usually composed of a guide rail, a slider, a support, a motor, a lead screw nut, a mass block, a grating ruler, a photoelectric switch, etc., which is complex in structure. At the same time, only the mass block plays the role of adjusting the center of mass of the satellite, thus reducing the adjustment efficiency of the device. Summary of the Invention

[0004] The problem addressed by this invention is how to improve the centroid adjustment efficiency of the device.

[0005] To address the above problems, the present invention provides an adjustment device and a satellite.

[0006] In a first aspect, the present invention provides an adjustment device for adjusting the center of mass of a satellite, comprising an adjustment assembly movably connected to the satellite, the adjustment assembly comprising: a stop member including a first housing and a first deformation structure, the first housing having a first receiving cavity and a first opening communicating with the first receiving cavity, the first deformation structure being at least partially installed within the first receiving cavity, the middle portion of the first deformation structure being able to contact the outer peripheral wall of the satellite to limit the displacement of the adjustment assembly, and the middle portion of the first deformation structure being able to deform relative to the first housing in a direction away from the first opening; at least two driving members respectively connected to both ends of the stop member along a first direction, each driving member comprising a second housing connected to the first housing and a second deformation structure, the second housing having a second receiving cavity and a second receiving cavity communicating with the second receiving cavity. The second opening provides a second deformation structure. One end of the second deformation structure is installed in the second receiving cavity. The middle part of the second deformation structure can bulge and deform relative to the first housing in a second direction, so that the other end of the second deformation structure contacts the outer peripheral wall of the satellite to drive the stop member to move in the first direction. The first direction and the second direction are perpendicular to each other. A heating element is provided on both the first deformation structure and the second deformation structure. The heating element is used to heat the corresponding first deformation structure and / or the second deformation structure to cause deformation of the first deformation structure and / or the second deformation structure. The driving elements located on both sides of the stop member operate selectively, and the driving element located on one side of the stop member is used to drive the stop member and the driving element located on the other side of the stop member to move.

[0007] The beneficial effects of the adjusting device of the present invention are:

[0008] At least two driving elements are connected to both ends of the actuating element, with one of the driving elements operating selectively. When no adjustment is needed, the first deformation structure of the actuating element can contact the outer peripheral wall of the satellite to form a stop, preventing relative displacement between the device and the satellite. When adjustment is needed, the second deformation structure of one driving element of the actuating element bulges outward along the second direction under the action of the heating element. The middle part of the first deformation structure of the actuating element deforms relative to the first housing in a direction away from the first opening under the action of the heating element, so that the first deformation structure moves away from the outer peripheral wall of the satellite, while its other end remains connected to the outer periphery of the satellite. The peripheral wall contacts and generates a driving force, which can drive the resisting component and the driving component on the other side to move along the first direction. This allows the driving force to be converted into the displacement of the adjustment component to meet the movement requirements of the adjustment component. Furthermore, both the first and second deformation structures achieve deformation control through heating components. Compared with mechanical transmission adjustment devices, thermally driven deformation response is faster, the time from heating to generating effective deformation is shorter, and the degree of deformation can be precisely controlled by the heating temperature, enabling rapid adjustment of minute displacements. This can significantly shorten the overall adjustment time, thereby improving the adjustment efficiency of the satellite's center of mass.

[0009] Optionally, the first deformation structure includes: a first body, installed within the first receiving cavity; a rubber component, disposed on the side wall of the first body near the first opening; and a heating element disposed between the first body and the rubber component; wherein the adjustment assembly has a fixed mode and an adjustment mode. When the adjustment assembly is in the fixed mode, the extending directions of the first body and the rubber component are parallel to the first direction, and the rubber component is located outside the first housing and contacts the outer peripheral wall of the satellite to limit the displacement of the adjustment assembly. When the adjustment assembly is in the adjustment mode, the heating element heats the first body and the rubber component located on one side of the resisting element to deform the first body and the rubber component in a direction away from the first opening, so that the rubber component separates from the outer peripheral wall of the satellite.

[0010] Optionally, the second deformation structure includes: a second body, one end of which is installed in the second receiving cavity, and the heating element is provided on the second body; and a pushing element, located at the other end of the second body, which is used to contact the outer peripheral wall of the satellite to drive the resisting element to move along the first direction; wherein, when the adjustment assembly is in the fixed mode, the middle part of the second body protrudes from the second housing through the second opening; when the adjustment assembly switches from the fixed mode to the adjustment mode, the heating element located on one side of the resisting element heats the corresponding second body, so that the middle part of the second body protrudes and deforms in a direction away from the second opening, and the pushing element contacts the outer peripheral wall of the satellite; when the adjustment assembly is in the adjustment mode, the heating element stops heating, so that the middle part of the second body gradually changes from a protruding section to a flat section, and the resisting element is driven to move by the friction between the pushing element and the outer peripheral wall of the satellite.

[0011] Optionally, the first housing, the second housing, and the pusher are made of carbon fiber material.

[0012] Optionally, the first body and the second body are made of a bidirectional shape memory polymer material.

[0013] Optionally, the number of driving members located on both sides of the stop member is the same.

[0014] Optionally, the first housing and the second housing are snap-fitted together.

[0015] Optionally, the regulating device further includes: a power supply, electrically connected to the heating element to provide electrical energy to the heating element; and a controller, communicatively connected to the power supply, the controller being configured to control the power supply to turn on or off.

[0016] Optionally, the adjustment device further includes: a position feedback unit configured to acquire the real-time theoretical position of the satellite's centroid and generate a position signal; a main control unit configured to calculate the satellite's subsequent theoretical position data based on the position signal and form a sequence-coded signal; an arithmetic control unit communicatively connected to the controller and the main control unit, the arithmetic control unit being configured to decode the sequence-coded signal and transmit the decoded signal to the controller; and a signal transmission unit communicatively connected to the position feedback unit and the main control unit, respectively.

[0017] Secondly, the present invention provides a satellite including the aforementioned adjustment device.

[0018] The advantages of the satellite in this embodiment over the prior art are the same as those of the adjustment device described above, and will not be repeated here. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the adjustment device provided in the embodiment of the present invention in a fixed mode;

[0020] Figure 2 A cross-sectional schematic diagram of the adjustment device provided in an embodiment of the present invention in a fixed mode;

[0021] Figure 3 A cross-sectional schematic diagram of the adjustment device provided in the embodiment of the present invention in the pre-preparation state of the adjustment mode;

[0022] Figure 4 A cross-sectional schematic diagram of the adjustment device provided in the embodiment of the present invention in the advancement state of the adjustment mode;

[0023] Figure 5 This is a cross-sectional schematic diagram of the adjustment device provided in an embodiment of the present invention in the state of the end of the adjustment mode.

[0024] Explanation of reference numerals in the attached figures:

[0025] 10, braking element; 11, first housing; 12, first deformation structure; 121, first main body; 122, rubber part; 13, first receiving cavity; 14, first opening.

[0026] Drive component 20, second housing 21, second deformation structure 22, second main body 221, push component 222, second receiving cavity 23, second opening 24, first direction X, second direction Z. Detailed Implementation

[0027] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Although some embodiments of the present invention are shown in the drawings, it should be understood that the present invention can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the present invention. It should be understood that the accompanying drawings and embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of protection of the present invention.

[0028] In the accompanying drawings, the X-axis represents the horizontal direction and is designated as the front-to-back position. The positive direction of the X-axis represents the front side, and the negative direction represents the rear side. The Z-axis represents the vertical direction, i.e., the up-down position, with the positive direction of the Z-axis representing the top and the negative direction representing the bottom. It should be noted that the aforementioned representations of the X, Y, and Z axes are merely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention.

[0029] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to"; the term "based on" means "at least partially based on"; the term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments"; and the term "optionally" means "optional embodiments". Definitions of other terms will be given in the following description. It should be noted that the concepts of "first," "second," etc., mentioned in this invention are used only to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies.

[0030] It should be noted that the terms "a" and "a plurality of" used in this invention are illustrative rather than restrictive. Those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0031] like Figures 1 to 5 As shown, in a first aspect, the present invention provides an adjustment device for adjusting the center of mass of a satellite, comprising a movable adjustment assembly connected to the satellite. The adjustment assembly includes: a stop member 10, comprising a first housing 11 and a first deformation structure 12. The first housing 11 has a first receiving cavity 13 and a first opening 14 communicating with the first receiving cavity 13. The first deformation structure 12 is at least partially installed in the first receiving cavity 13. The middle portion of the first deformation structure 12 can contact the outer peripheral wall of the satellite to limit the displacement of the adjustment assembly. The middle portion of the first deformation structure 12 can also deform relative to the first housing 11 in a direction away from the first opening 14. At least two driving members 20 are respectively connected to both ends of the stop member 10 along a first direction. Each driving member 20 includes a second housing 21 connected to the first housing 11 and a second deformation structure 22. The second housing 21 has a second receiving cavity 23 for... The second opening 24 is connected to the second receiving cavity 23. One end of the second deformation structure 22 is installed in the second receiving cavity 23. The middle part of the second deformation structure 22 can be deformed in a protruding direction relative to the first housing 11 in the second direction so that the other end of the second deformation structure 22 contacts the outer peripheral wall of the satellite to drive the stop member 10 to move in the first direction. The first direction and the second direction are perpendicular to each other. Heating member: Heating member is provided on both the first deformation structure 12 and the second deformation structure 22. The heating member is used to heat the corresponding first deformation structure 12 and / or second deformation structure 22 so that the first deformation structure 12 and / or second deformation structure 22 deform. Among them, the driving members 20 located on both sides of the stop member 10 can be operated selectively. The driving member 20 located on one side of the stop member 10 is used to drive the stop member 10 and the driving member 20 located on the other side of the stop member 10 to move.

[0032] In this embodiment, at least two driving members 20 are respectively connected to both ends of the abutment 10, and one of the driving members 20 on each side operates selectively. When no adjustment is needed, the first deformation structure 12 of the abutment 10 can contact the outer peripheral wall of the satellite to form a stop, thereby preventing relative displacement between the device and the satellite. When adjustment is needed, when the second deformation structure 22 of the driving member 20 on one side of the abutment 10 bulges and deforms along the second direction under the action of the heating element, the middle part of the first deformation structure 12 of the abutment 10 deforms relative to the first shell 11 in a direction away from the first opening 14 under the action of the heating element, so that the first deformation structure 12 is far from the outer peripheral wall of the satellite. One end of the device contacts the outer perimeter of the satellite and generates a driving force, which can drive the stop 10 and the driving component 20 on the other side to move along the first direction. This allows the driving force to be converted into the displacement of the adjustment component to meet the movement requirements of the adjustment component. Furthermore, both the first deformation structure 12 and the second deformation structure 22 achieve deformation control through heating components. Compared with mechanical transmission adjustment devices, thermally driven deformation response is faster, the time from heating to generating effective deformation is shorter, and the degree of deformation can be precisely controlled by the heating temperature, enabling rapid adjustment of minute displacements. This can significantly shorten the overall adjustment time, thereby improving the adjustment efficiency of the satellite's center of mass.

[0033] In this embodiment, the adjustment system includes three adjustment components, which move along a first direction, a second direction, and a third direction, respectively, thereby changing the position of the satellite's center of mass.

[0034] In this embodiment, a heating element can be selected as a heating wire. Because the heating wire heats up rapidly, it can transfer heat to the first deformation structure 12 and the second deformation structure 22 in a short time, enabling them to quickly reach the required deformation temperature. This significantly shortens the deformation response time and indirectly improves the adjustment efficiency of the center of mass. In addition, the heating wire has a simple structure and small size, which does not occupy too much installation space and avoids structural redundancy caused by an excessively large heating element.

[0035] Optionally, the first deformation structure 12 includes: a first body 121, installed in the first receiving cavity 13; a rubber part 122, disposed on the side wall of the first body 121 near the first opening 14, and a heating element is provided between the first body 121 and the rubber part 122; wherein, the adjustment assembly has a fixed mode and an adjustment mode. When the adjustment assembly is in the fixed mode, the extension directions of the first body 121 and the rubber part 122 are parallel to the first direction, and the rubber part 122 is located outside the first housing 11 and contacts the outer peripheral wall of the satellite to limit the displacement of the adjustment assembly. When the adjustment assembly is in the adjustment mode, the heating element heats the first body 121 and the rubber part 122 located on the side of the stop member 10 to deform the first body 121 and the rubber part 122 in a direction away from the first opening 14, so that the rubber part 122 separates from the outer peripheral wall of the satellite.

[0036] By setting the above structure, in the fixed mode, the extension directions of the first main body 121 and the rubber part 122 are parallel to the first direction. The rubber part 122 is located outside the first housing 11 and contacts the outer peripheral wall of the satellite. With the help of the elastic deformation characteristics of the rubber part 122, it can closely fit the satellite surface and form a stable resistance effect, effectively limiting the displacement of the adjustment component. When switching to the adjustment mode, the heating element heats the first main body 121 and the rubber part 122 on the side of the resistance element 10. The first main body 121 and the rubber part 122 deform in a direction away from the first opening 14, so that the rubber part 122 quickly separates from the outer peripheral wall of the satellite to eliminate resistance. The above setting can make the mode switching response of the device faster, thereby further improving the adjustment efficiency of the device.

[0037] In this embodiment, the first body 121 and the rubber part 122 are flat plates in the low temperature state and arch bridges resembling the letter "Ω" in the high temperature state. When the power is turned on, the heating will turn the body into a high temperature state, and when the power is turned off, the cooling will return the body to a low temperature state. The rubber part 122 is a high friction coefficient rubber. In the low temperature state, it is in close contact with the wall surface, and in the high temperature state, it is detached from the wall surface, thus relieving the obstruction effect on the device.

[0038] Optionally, the second deformation structure 22 includes: a second body 221, one end of which is installed in the second receiving cavity 23, and a heating element is provided on the second body 221; and a pushing element 222, which is provided at the other end of the second body 221, and is used to contact the outer peripheral wall of the satellite to drive the stop member 10 to move along the first direction. When the adjustment assembly is in the fixed mode, the middle part of the second body 221 protrudes from the second housing 21 through the second opening 24. When the adjustment assembly switches from the fixed mode to the adjustment mode, the heating element located on one side of the stop member 10 heats the corresponding second body 221, causing the middle part of the second body 221 to bulge and deform in a direction away from the second opening 24, and the pushing element 222 contacts the outer peripheral wall of the satellite. When the adjustment assembly is in the adjustment mode, the heating element stops heating, causing the middle part of the second body 221 to gradually change from a bulging section to a flat section, and the friction between the pushing element 222 and the outer peripheral wall of the satellite drives the stop member 10 to move.

[0039] By setting the above structure, in the fixed mode, the middle part of the second main body 221 protrudes from the second shell 21 through the second opening 24. At this time, the pusher 222 does not form effective contact with the outer peripheral wall of the satellite and will not generate driving force, ensuring the stability of the adjustment component in the resistive state. When switching to the adjustment mode, the heating element heats the corresponding second main body 221, causing its middle part to bulge and deform away from the second opening 24. The pusher 222 then contacts the outer peripheral wall of the satellite and forms a reliable abutment. When switching to the adjustment mode, the heating element stops heating, and the middle part of the second main body 221 gradually changes from a bulging section to a flat section. During this deformation recovery process, the pusher 222 will generate frictional force with the wall surface during the deformation process, thereby pushing the resistive member 10 to move along the first direction. The above setting can make the mode switching response of the device faster, so as to further improve the adjustment efficiency of the device.

[0040] In this embodiment, the second body 221 is an inverted "Ω" shape at low temperature and an arch bridge shape resembling the letter "Ω" at high temperature. When heated by power, it will become a high temperature state, and when cooled by power-off, it will return to a low temperature state.

[0041] Optionally, the first housing 11, the second housing 21, and the pusher 222 are made of carbon fiber material.

[0042] By setting the above structure, due to the lightweight characteristics of carbon fiber material, the weight of the first shell 11, the second shell 21, and the pusher 222 can be significantly reduced while ensuring structural strength. The lightweight structure allows the drive component 20 to overcome less inertia when driving the adjustment component to move, thereby reducing energy consumption. In addition, the deformation of carbon fiber material is minimal when the temperature changes, so the dimensional changes of the first shell 11 and the second shell 21 are negligible when the temperature rises due to the operation of the heating element and when the ambient temperature fluctuates. This will not interfere with the deformation of the first deformation structure 12 and the second deformation structure 22, ensuring that the deformation structure can deform accurately according to the preset trajectory and improving the accuracy of adjustment.

[0043] Optionally, the first body 121 and the second body 221 are made of a bidirectional shape memory polymer material.

[0044] By setting the above structure, the bidirectional shape memory polymer can maintain two preset forms at different temperatures, and can achieve precise switching between the two forms through temperature changes. In the fixed mode, the first body 121 and the rubber part 122 maintain an extension state parallel to the first direction, and the rubber part 122 contacts the outer peripheral wall of the satellite to achieve resistance. When switching to the adjustment mode, the heating element heats the first body 121 to deform, causing the rubber part 122 to move away from the first opening 14 and detach from the satellite surface, thus releasing the resistance. When heating stops, the first body 121 can automatically return to the initial extension state by virtue of the material's memory properties, allowing the rubber part 122 to re-contact the satellite and quickly switch back to the fixed mode. This makes the switching action faster and more precise, further improving the adjustment efficiency of the device.

[0045] In the fixed mode, the second body 221 protrudes from the second housing 21 through the second opening 24. When the second body 221 is heated, it deforms and protrudes away from the second opening 24 along a preset trajectory, and the pushing member 222 contacts the satellite. After heating stops, the second body 221 automatically returns to its flat section, and the adjustment component moves by means of the friction between the pushing member 222 and the satellite. This allows the switching action to be faster and more precise, further improving the adjustment efficiency of the device.

[0046] Optionally, the number of drive members 20 located on both sides of the stop member 10 is the same.

[0047] By setting the above structure, it can be ensured that the driving force of the adjustment component is consistent when it moves in both directions. This allows the adjustment component to have the same acceleration, velocity change pattern and displacement control accuracy when it moves in both directions along the first direction, ensuring the consistency of the satellite's center of mass during the bidirectional adjustment process and avoiding adjustment deviations caused by asymmetric driving forces.

[0048] Optionally, the first housing 11 and the second housing 21 are snap-fitted together.

[0049] In this embodiment, the first housing 11 is provided with a slot, and the second housing 21 is provided with a buckle.

[0050] By setting the above structure, rapid assembly can be achieved through the pre-set slots and snap-fit ​​structures on the first housing 11 and the second housing 21. This significantly shortens the assembly time of the first housing 11 and the second housing 21, reduces assembly steps, and lowers labor costs. At the same time, the high positioning accuracy of the snap-fit ​​structure ensures that the first housing 11 and the second housing 21 maintain a preset relative position after assembly, avoiding uneven force on the driving component 20 and the resisting component 10 due to connection deviations, thereby ensuring the overall structural stability of the adjustment assembly.

[0051] Optionally, the regulating device further includes: a power supply, electrically connected to the heating element to provide electrical energy to the heating element; and a controller, communicatively connected to the power supply, configured to control the power supply to turn on or off.

[0052] By setting up the above structure, the controller and power supply work together to achieve intelligent control of the heating element's working status. The controller can automatically determine whether to initiate an adjustment action based on real-time monitoring data of the satellite's center of mass, and precisely regulate the working status of the heating element by controlling the power supply to turn it on or off. For example, when the satellite attitude sensor detects that the center of mass shift exceeds the preset range, the controller will immediately send a command to the power supply to supply power to the corresponding heating element, causing the first deformation structure 12 or the second deformation structure 22 to deform and initiate the adjustment process; when the center of mass returns to the reasonable range, the controller can promptly cut off the power supply to stop heating, avoiding energy waste and thus improving the device's adjustment efficiency.

[0053] In this embodiment, the size of the power supply can be freely adjusted according to the number of drive components 20, with sufficient power supply slots provided, and the power supply can go into standby mode in a stable state to save power.

[0054] In this embodiment, the power supply and controller are located on the damping component 10, and the density of the assembly mass unit can be customized according to the requirements to cooperate with the damping component 10 and the driving component 20 to adjust the efficiency and accuracy of the center of mass adjustment.

[0055] In this embodiment, when the device is in fixed mode: the power supply is off, the second deformation structure 22 is a low-temperature inverted "Ω" shape, and the pusher 222 at its end is suspended in the air. The pusher 222 does not contact the satellite wall; only the protruding part of the inverted "Ω" shape of the second deformation structure 22 contacts and supports the satellite wall, ensuring the consistency of the device's height from front to back and avoiding the impact of unbalanced height on the center of mass. The first deformation structure 12 is in a low-temperature flat plate state, and the rubber part 122 is in close contact with the wall. Due to its high coefficient of friction, it has a good damping effect, ensuring the stability of the device in fixed mode.

[0056] In dynamic adjustment mode: With the power on, the second deformation structure 22 corresponding to the forward direction is heated, transforming it into a high-temperature "Ω" shape. At this time, the pusher 222 at its end is in close contact with the satellite wall. Since the first deformation structure 12 has not yet detached from the wall, and the reaction force provided by the rubber part 122 is greater than or equal to the force provided by the pusher 222 during deformation, the device will not experience reverse movement, resulting in slippage and ineffective drive. After the second deformation structure 22 transforms into a high-temperature "Ω" shape, the first deformation structure 12 is heated to detach from the wall, eliminating its resistance effect on the device. Then, heating of the second deformation structure 22 is stopped, allowing it to cool and return to a low-temperature reverse "Ω" shape. During this process, the pusher 222 connected to it contacts and rubs against the satellite wall, propelling the device forward.

[0057] Optionally, the adjustment device further includes: a position feedback unit configured to acquire the real-time theoretical position of the satellite's centroid and generate a position signal; a main control unit configured to calculate the satellite's subsequent theoretical position data based on the position signal and form a sequence-coded signal; an arithmetic control unit communicatively connected to the controller and the main control unit, configured to decode the sequence-coded signal and transmit the decoded signal to the controller; and a signal transmission unit communicatively connected to the position feedback unit and the main control unit, respectively.

[0058] By setting up the above structure, the position feedback unit can assist the overall satellite center-of-gravity adjustment system in enhancing its real-time feedback capability for center-of-gravity adjustment, improving adjustment precision and accuracy. The position feedback unit is not limited to a certain form; it can use infrared ranging to measure the position within the satellite, use positioning rudders to determine the actuator position, or use clear cameras, gratings, etc., to acquire the position information of the intelligent actuator. The computation and control unit is used to improve the computational efficiency of the overall system. After the onboard main control system or the ground base station main control system performs simulation calculations to obtain accurate motion sequence codes, the computation and control unit parses and edits the codes to improve the efficiency of center-of-gravity adjustment and alleviate computational pressure. The signal transmission unit is used to complete the real-time transmission of signals, promptly feeding back the real-time position information of the actuator, assisting the overall system in real-time calculation of the center of gravity, and also receiving the code transmission from the main control system. Different signal transmission units have different numbers in the entire system, accurately obtaining the correct code when receiving codes. At the same time, it can assist the operation of more auxiliary accessories after carrying more accessories, such as carrying satellite health monitoring accessories to provide real-time satellite health feedback to the main control system.

[0059] like Figure 1 and Figure 2As shown in the diagram, in this embodiment, which is a fixed mode state diagram, the second deformation structures 22 are all in a low-temperature inverted "Ω" shape. At this time, the pusher 222 at its end is in a suspended state and does not contact the satellite wall. Only the inverted "Ω" shaped protrusion of the second deformation structure 22 contacts and supports the satellite wall. The first deformation structure 12 is in a low-temperature flat plate state at this time, wherein the rubber part 122 is in contact with the satellite wall.

[0060] like Figure 3 The diagram shows the pre-preparation state of the adjustment mode, which is also the initial state diagram of the adjustment mode. The main control unit calculates the theoretical position of the satellite's real-time centroid based on the pre-set satellite trajectory. Based on the position data fed back by the position feedback unit, it calculates the subsequent theoretical position data of the intelligent actuator. It calculates the subsequent theoretical position data of the satellite based on the position signal and forms a sequence-encoded signal. The signal transmission unit receives the signal, and the computation and control unit parses the code, sorts the subsequent motion sequence, and the power supply changes from sleep standby to working state. Based on the motion direction data provided by the motion code, the corresponding second deformation structure 22 is first heated, making it a high-temperature "Ω" shape. At this time, due to a... The first deformation structure 12 on one side has not left the satellite wall. The friction between the rubber part 122 and the satellite wall is greater than the friction between the pushing part 222 and the satellite wall during the shape change of the second deformation structure 22. The second deformation structure 22 on the other side is still in the low temperature reverse "Ω" shape at this time. The part in contact with the satellite wall is only the smooth arch. However, due to the support of the second deformation structure 22 on the other side, the height of the second deformation structures 22 on both sides is balanced, and the overall positive pressure distribution is consistent. Only the second deformation structure 22 completes the shape change from the low temperature state to the high temperature state, so that the device enters the propulsion pre-preparation state.

[0061] like Figure 4 As shown, in the propulsion state of the adjustment mode, the controller controls the power supply to heat the first deformation structure 12 on one side, making it a high-temperature "Ω" shape. Then, the controller controls the second deformation structure 22 to stop heating, allowing it to cool down to a low-temperature inverse "Ω" shape, but not completely. It only cools down to near the intermediate state of its motion trajectory to complete the propulsion action. If there is a subsequent propulsion preparation, it can be reheated to reach the propulsion preparation state more quickly. If there is no subsequent propulsion preparation, it can be further cooled to a low-temperature inverse "Ω" shape. During the process of reaching the intermediate flat state of the motion trajectory, the propulsion component 222 contacts the satellite wall, generating relative motion. At this time, because the middle of the second deformation structure 22 is suspended, the friction coefficient between the propulsion component 222 and the satellite wall is higher than the friction force between the first deformation structure 12 on the other side and the satellite wall, so the intelligent device moves forward.

[0062] like Figure 5As shown, in the end state of the adjustment mode, the controller controls the power supply to stop heating the first deformed structure 12, so that it returns to a low-temperature flat plate shape and remains in close contact with the satellite wall. If the motion sequence is not yet finished, the next round of propulsion preparation is carried out. The above preparation and propulsion process are cycled to keep the device moving intermittently and evenly, and to control the consistency of each round of propulsion. If the motion sequence has ended, the position feedback unit obtains the current position data of the device and feeds it back to the main control unit by the signal transmission unit. If there is no next instruction, the power supply enters the sleep standby state and switches to the fixed mode.

[0063] Secondly, the present invention provides a satellite including the aforementioned adjustment device.

[0064] The beneficial effects of the satellite in this embodiment compared to the prior art are the same as those of the adjustment device described above, and will not be repeated here. Although the present invention has been disclosed above, the scope of protection of the present invention is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.

Claims

1. An adjustment device for adjusting the center of mass of a satellite, characterized in that, Includes an adjustment component that is movably connected to the satellite, the adjustment component comprising: The damping member (10) includes a first housing (11) and a first deformation structure (12). The first housing (11) has a first receiving cavity (13) and a first opening (14) communicating with the first receiving cavity (13). The first deformation structure (12) is at least partially installed in the first receiving cavity (13). The middle part of the first deformation structure (12) can contact the outer peripheral wall of the satellite to limit the displacement of the adjustment component. The middle part of the first deformation structure (12) can also deform relative to the first housing (11) in a direction away from the first opening (14). At least two drive members (20) are respectively connected to the two ends of the stop member (10) along a first direction. Each drive member (20) includes a second housing (21) connected to the first housing (11) and a second deformation structure (22). The second housing (21) has a second receiving cavity (23) and a second opening (24) communicating with the second receiving cavity (23). One end of the second deformation structure (22) is installed in the second receiving cavity (23). The middle part of the second deformation structure (22) can be deformed in a convex direction relative to the first housing (11) along a second direction so that the other end of the second deformation structure (22) contacts the outer peripheral wall of the satellite to drive the stop member (10) to move along the first direction. The first direction and the second direction are perpendicular to each other. Heating element, the first deformation structure (12) and the second deformation structure (22) are both provided with the heating element, the heating element is used to heat the corresponding first deformation structure (12) and / or second deformation structure (22) to cause the first deformation structure (12) and / or second deformation structure (22) to deform; Among them, the driving member (20) located on both sides of the stop member (10) operates selectively, and the driving member (20) located on one side of the stop member (10) is used to drive the stop member (10) and the driving member (20) located on the other side of the stop member (10) to move.

2. The adjusting device according to claim 1, characterized in that, The first deformable structure (12) includes: The first main body (121) is installed in the first receiving cavity (13); A rubber component (122) is disposed on the side wall of the first body (121) near the first opening (14), and the heating element is disposed between the first body (121) and the rubber component (122); The adjustment component has a fixed mode and an adjustment mode. When the adjustment component is in the fixed mode, the extension directions of the first body (121) and the rubber part (122) are parallel to the first direction. The rubber part (122) is located outside the first housing (11) and contacts the outer peripheral wall of the satellite to limit the displacement of the adjustment component. When the adjustment component is in the adjustment mode, the heating element heats the first body (121) and the rubber part (122) located on the side of the stop member (10) to deform the first body (121) and the rubber part (122) away from the first opening (14) so ​​that the rubber part (122) separates from the outer peripheral wall of the satellite.

3. The adjusting device according to claim 2, characterized in that, The second deformation structure (22) includes: The second body (221) has one end installed in the second receiving cavity (23) and the heating element is provided on the second body (221); A pusher (222) is provided at the other end of the second body (221), and the pusher (222) is used to contact the outer peripheral wall of the satellite to drive the stop (10) to move along the first direction; When the adjustment component is in the fixed mode, the middle part of the second body (221) protrudes from the second housing (21) through the second opening (24). When the adjustment component switches from the fixed mode to the adjustment mode, the heating element located on the side of the stop member (10) heats the corresponding second body (221) so that the middle part of the second body (221) protrudes and deforms in a direction away from the second opening (24). The pushing member (222) contacts the outer peripheral wall of the satellite. When the adjustment component is in the adjustment mode, the heating element stops heating so that the middle part of the second body (221) gradually changes from a protruding section to a flat section, and the friction between the pushing member (222) and the outer peripheral wall of the satellite pushes the stop member (10) to move.

4. The adjusting device according to claim 3, characterized in that, The first housing (11), the second housing (21), and the pusher (222) are made of carbon fiber material.

5. The adjusting device according to claim 3, characterized in that, The first body (121) and the second body (221) are made of bidirectional shape memory polymer material.

6. The adjusting device according to claim 1, characterized in that, The number of driving members (20) located on both sides of the stop member (10) is the same.

7. The adjusting device according to claim 1, characterized in that, The first housing (11) and the second housing (21) are snap-fitted together.

8. The adjusting device according to claim 1, characterized in that, The regulating device further includes: A power source is electrically connected to the heating element to provide electrical energy to the heating element; A controller, communicatively connected to the power supply, is configured to control the power supply to be turned on or off.

9. The adjusting device according to claim 8, characterized in that, The regulating device further includes: The position feedback unit is configured to acquire the real-time theoretical position of the satellite's center of mass and generate a position signal; The main control unit is configured to calculate the satellite's subsequent theoretical position data based on the position signal and form a sequence-coded signal; The computation control unit is communicatively connected to the controller and the main control unit. The computation control unit is configured to decode the sequence encoded signal and transmit the decoded signal to the controller. The signal transmission unit is communicatively connected to both the position feedback unit and the main control unit.

10. A satellite, characterized in that, Includes the adjusting device as described in any one of claims 1 to 9.

Images