CN117002754A - Solar sail attitude adjustment actuator, solar sail assembly and spacecraft - Google Patents
Solar sail attitude adjustment actuator, solar sail assembly and spacecraft Download PDFInfo
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- CN117002754A CN117002754A CN202310976644.3A CN202310976644A CN117002754A CN 117002754 A CN117002754 A CN 117002754A CN 202310976644 A CN202310976644 A CN 202310976644A CN 117002754 A CN117002754 A CN 117002754A
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
Abstract
The invention discloses a solar sail attitude adjusting actuator, which relates to the technical field of solar sail spacecrafts and comprises the following components: the deformation layer is used for being laid on the back of the solar sail, and the deformation layer can deform to drive the solar sail to move, so that the posture of the solar sail is adjusted. The invention also discloses a solar sail assembly comprising a solar sail and a solar sail attitude adjustment actuator as described above. The invention also discloses a spacecraft comprising the solar sail assembly. The invention improves the accuracy of solar sail attitude control, saves energy, improves the load born, and greatly reduces the failure rate.
Description
Technical Field
The invention relates to the technical field of solar sail spacecrafts, in particular to a solar sail attitude adjusting actuator, a solar sail assembly and a spacecraft.
Background
As the flying distance of the spacecraft gets longer, the on-orbit task time becomes longer, which means that the spacecraft propelled by the traditional reaction force needs to carry more working medium and energy during launching, thereby causing the launching quality of the spacecraft to be increased along with the launching quality, and further increasing the difficulty and cost of the launching stage.
In recent years, solar sails have been attracting attention as a new type of spacecraft propulsion means; the spacecraft obtains propulsion through solar pressure generated by the carried large-area light-weight thin-film solar sail, the solar sail propulsion technology does not need to depend on the injection consumption of the propellant any more, and the cost and difficulty of the spacecraft launching can be reduced.
However, the attitude adjustment of the solar sail is currently controlled by a conventional motor, for example, as shown in fig. 1, which is a solar sail spacecraft structure with a control airfoil, and 4 small triangular solar sails as control airfoils 104 are mounted at the tail ends of structural rods 102 of the solar sail, and can be driven by the motor to rotate around the structural rods 102, and when the control airfoils 104 are rotated to a proper angle, the sunlight pressure acting on the control airfoils 104 is used to generate the light pressure control moment required for the three-axis attitude control of the spacecraft.
The attitude adjustment of the existing solar sail is controlled by a traditional motor, the traditional motor is large in weight, and meanwhile, the traditional motor has more problems. Firstly, in the operation process of the traditional motor, due to factors such as electromagnetic induction, resistance and the like, a plurality of energy losses such as resistance loss, iron loss, friction loss and the like are generated, and the energy losses can cause the reduction of the energy utilization efficiency of the traditional motor; secondly, the efficiency of the traditional motor under different loads is different, the efficiency is generally lower under low load and higher under full load, so that the energy utilization efficiency of the traditional motor can be influenced by load variation; furthermore, the conventional motor needs an external power supply to supply power to normally operate, but the stability of the external power supply also affects the energy utilization efficiency of the conventional motor.
Therefore, the traditional motor has the problems of higher fault rate, lower precision, smaller load, larger energy consumption and the like, and is not suitable for the solar sail inter-planet detection task with long task period and high attitude control precision requirement.
Disclosure of Invention
The invention aims to provide a solar sail attitude adjusting actuator, a solar sail assembly and a spacecraft, so as to solve the problems in the prior art, improve the accuracy of solar sail attitude control, save energy, improve the load born, and greatly reduce the failure rate.
In order to achieve the above object, the present invention provides the following solutions:
the present invention provides a solar sail attitude adjustment actuator, comprising: the deformation layer is used for being laid on the back of the solar sail, and the deformation layer can deform to drive the solar sail to move, so that the posture of the solar sail is adjusted.
Preferably, the deformation layer comprises an SMA piece and an SMP material layer, and at least one side of the SMP material layer is paved with the SMA piece; and the solar sail posture adjusting actuator further comprises a heating device, and the deformation layer can be deformed after being heated by the heating device.
Preferably, the SMA element is an SMA rod, two sides of the SMP material layer are paved with the SMA rod, the SMA rods on two sides are respectively arranged in an elastic material layer, and the elastic material layer is paved on two sides of the SMP material layer.
Preferably, the elastic material layer is a Veroclear elastic material layer.
Preferably, the heating device comprises a power supply and a heating element, the SMA rod is electrically connected with the power supply, the heating element is arranged in the SMP material layer, the SMP material layer is heated by the heating element and then has reduced hardness, the SMA rod is deformed after being electrified and drives the SMP material layer to deform, and when the deformation is completed, the SMP material layer is heated to the transition temperature again and can be restored to the original state.
Preferably, the heating element is an electric heating wire, and the electric heating wire is electrically connected with the power supply.
The present invention also provides a solar sail assembly including a solar sail and a solar sail attitude adjustment actuator as described above.
Preferably, the solar sail comprises a fixed shaft and a plurality of sail surface assemblies, all of which are disposed around the fixed shaft; the sail surface assembly comprises a first sail surface and a second sail surface, wherein one side of the first sail surface and one side of the second sail surface are connected to a fixed truss, and one end of the fixed truss is fixed on the fixed shaft; the first sail surface and the second sail surface are respectively connected with a movable truss on one side far away from the fixed truss, and one end of the movable truss is rotatably connected to the fixed shaft.
Preferably, the sail panel assembly is provided with four.
The invention also provides a spacecraft comprising a solar sail assembly as described above.
Compared with the prior art, the invention has the following technical effects:
according to the invention, the solar sail is driven to move through the deformation of the deformation layer, so that the posture of the solar sail is adjusted, the use of a traditional motor is eliminated, the accuracy of the posture control of the solar sail is greatly improved, the energy is saved, the load born by the solar sail is also improved, and the failure rate is greatly reduced; moreover, compared with the prior art, the solar sail attitude control is performed through four triangular control wing surfaces, and the controllable angle range is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of a prior art solar sail spacecraft configuration with control airfoils;
in fig. 1: 101-spacecraft loading; 102-structural rod; 103-sail surface; 104-control airfoil.
FIG. 2 is a memory shape diagram of an SMA rod in an embodiment of the present invention;
FIG. 3 is a diagram illustrating a memory shape of a SMP material layer in accordance with an embodiment of the present invention;
FIG. 4 is a schematic diagram of deformation of a deformation layer according to an embodiment of the present invention;
FIG. 5 is a schematic view of a solar sail structure according to an embodiment of the present invention;
FIG. 6 is a schematic representation of attitude adjustment of a solar sail in an embodiment of the invention;
fig. 7 is a simulation diagram of a Simuink circuit in an embodiment of the present invention.
Fig. 2-7: 1-an SMA rod; a layer of 2-SMP material; 3-fixing shaft; 4-a first sail surface; 5-a second sail surface; 6-fixing the truss; 7-a movable truss; 8-connecting piece.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a solar sail attitude adjusting actuator, a solar sail assembly and a spacecraft, so as to solve the problems in the prior art, improve the accuracy of solar sail attitude control, save energy, improve the load born, and greatly reduce the failure rate.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Example 1
As shown in fig. 2 to 4, there is provided a solar sail posture adjustment actuator in the present embodiment, including: the deformation layer is used for being laid on the back of the solar sail, and the deformation layer can deform to drive the solar sail to move, so that self-posture adjustment of the solar sail is achieved.
In the embodiment, the solar sail is driven to move through the deformation of the deformation layer, so that the posture of the solar sail is adjusted, the use of a traditional motor is eliminated, the accuracy of the posture control of the solar sail is greatly improved, energy is saved, the load born by the solar sail is also improved, and the failure rate is greatly reduced; moreover, compared with the prior art, the solar sail attitude control is performed through four triangular control wing surfaces, and the controllable angle range is improved.
In this embodiment, the deformation layer may be selected according to specific working requirements, for example, the deformation layer may be a piezoelectric fiber sheet, preferably an MFC (Macro Fiber Composite, macroscopic fiber composite material) piezoelectric fiber sheet, and the deformation of the piezoelectric fiber sheet is controlled by the driver, so as to drive the solar sail to move, and realize attitude control of the solar sail.
In the embodiment, an SMA-SMP two-way deformation material is preferably used as a deformation layer, and solar sail structure modeling and solar sail stress simulation based on Matlab and Simulink are performed simultaneously based on Solidworks; specifically, the deformation layer mainly comprises an SMA (shape memory alloys, shape memory alloy) piece and an SMP (shape memory polymer ) material layer 2, wherein the SMA piece is preferably an SMA rod 1, and the SMA rods 1 are preferably laid on two sides of the SMP material layer 2 to form an SMA-SMP actuator; and the memory property of the SMA rod 1 is U-shaped, the memory property of the SMP material layer 2 is rectangular, the solar sail posture adjusting actuator further comprises a heating device, and the deformation layer can deform after being heated by the heating device, as shown in figures 2-4.
In this embodiment, the heating device mainly includes a power supply and a heating element, where the SMA rod 1 is electrically connected to the power supply, and the SMA rod 1 is electrically heated by the power supply, and the heating element is disposed in the SMP material layer 2 and is used to heat the SMP material layer 2; the SMP material layer 2 is heated by the heating element and then has reduced hardness, the SMA rod 1 is electrified and then heated to deform, the SMP material layer 2 with reduced hardness is driven to deform, and after the deformation is completed, the SMP material layer is heated to the transition temperature to be capable of recovering the original state.
In this embodiment, the heating device is preferably a heating wire, and the heating wire is electrically connected to the power supply.
In this embodiment, the SMA rods 1 on two sides are respectively disposed in an elastic material layer, and the two elastic material layers are respectively laid on two sides of the SMP material layer 2; as a preferred embodiment, the elastic material layer is a Veroclear elastic material layer, wherein Veroclear (photosensitive resin) is a rigid, nearly colorless material, has higher dimensional stability, and is suitable for conventional use, well-defined modeling and visual simulation of transparent thermoplastic materials (such as PMMA); alternatively, other layers of elastomeric material may be selected according to specific operational needs.
In the embodiment, the SMA-SMP actuator realizes a driving function by utilizing the shape memory effect of an SMA material; SMA rod 1 is preloaded and mounted in a resilient layer of Veroclear elastomer material and mounted on both sides of SMP material layer 2, while heating wires (preferably resistance heating wires) are also mounted in SMP material layer 2. During the deformation process, the SMP material layer 2 is first heated by the heating wire and softened, it is changed from a glassy state (high rigidity) to a rubbery state (low rigidity), then, the current input to the heating wire is stopped, the SMA rod 1 is energized and heated, shrinkage occurs based on the shape memory effect of itself, and the SMA rod 1 remains in the driving state until the SMP material layer 2 is cooled to the high-rigidity glassy state. When the SMA rod 1 is heated, the surrounding Veroclear material is also heated, and the hardness decreases, thereby being compressed.
In this embodiment, in the above manner, the SMA-SMP actuator bends sideways and drives the deformation of the solar sail; after the deformation is completed, the SMP material layer 2 is firstly stopped to be heated and hardened, and when the SMP material layer 2 is hard enough, the SMA rod 1 is stopped to be heated, and the deformation is completed; at this time, the solar sail deployment actuator maintains the deformed shape due to the high stiffness of the SMP material layer 2.
Finally, current is applied to the heating wire again, the SMP material layer 2 is heated to a transition temperature, the SMP material layer 2 is restored to a memory shape, and then cooled, thereby realizing the shape restoration of the solar sail posture adjustment actuator.
In the embodiment, the SMA-SMP bidirectional deformation intelligent material is adopted to replace the traditional motor-driven solar sail, and the SMA rod 1 can be trained into a temporary elongated shape under the combination of thermal load and mechanical load and then contracted to restore the original shape; this is caused by the transformation between the martensite phase at low temperature and the austenite phase at high temperature.
The SMA-SMP actuator is formed by printing a rigid SMP material layer 2 and an elastic soft layer (Veroclear elastic material and an SMA rod 1 in the elastic soft layer); shape retention and recovery stiffness adjustment are achieved using layers 2 of embedded SMP material of different thickness, the temperature in the deformation zone being controlled by heating with heating wires to transition it from a high stiffness state at room temperature to a low stiffness state at high temperature. When the SMP material layer 2 is in a low stiffness state, actuation of the SMA rod 1 causes a large bending deformation of the deformation region; the shape memory of the SMP material layer 2 is also able to recover its original shape at high temperatures.
The present example measured various properties of SMA-SMP actuators, including bending stiffness and maximum deflection, to show versatility of multi-material 3D printing; finite element models have also been developed to determine important actuation parameters, including shape fixation and recovery.
In this embodiment, the SMP material layer 2 may be returned to its original shape by heating to a particular transition temperature, which may be the glass transition temperature or the crystalline melting temperature of the polymer; the deformation of the SMP material layer 2 into the desired shape is achieved by a specific thermo-mechanical process, which typically begins above the transition temperature. While maintaining this deformed state, the SMP material layer 2 cools below the transition temperature; during cooling, the SMP material layer 2 becomes more rigid due to vitrification or crystallization, thereby maintaining the shape unchanged.
In this embodiment, by combining SMA and SMP, an active composite material can be produced that can recover with a large force at high temperature, retain its deformed shape at low temperature, recover its deformed shape, and withstand a large load, and from which a reversible actuator can be produced.
Due to the characteristics of the SMA-SMP, the SMA-SMP is used in a solar sail attitude adjusting actuator, so that the actuator with a complex shape can be manufactured according to different task requirements, and a traditional motor is limited by a structure; also, the energy conversion efficiency of the composite material is high, so that the energy conversion rate of mechanical energy and electric energy of the actuator is high. Meanwhile, the SMA-SMP is applied to the solar sail, so that the structure is light in weight and high in strength, and the operation efficiency of the whole system is improved. The same sample embodiment carries out self-posture adjustment through the area change of the whole solar sail, the change area is increased, and the controllable posture change range can be enlarged.
In summary, the solar sail posture adjustment actuator in the embodiment is an intelligent structure based on intelligent material SMA-SMP, and achieves the aim of self posture adjustment control of the solar sail through the two-way deformation function and three-axis posture control of the intelligent material, so that the accuracy of posture control is greatly improved, energy is saved, the load borne by the solar sail is improved, and the failure rate is greatly reduced; moreover, compared with the technical scheme that the attitude control is performed through four triangular control wing surfaces in the prior art, the triangular control wing surface has smaller light receiving area and smaller controllable angle range, and the controllable attitude change range can be enlarged.
As shown in fig. 6-7, there is also provided in this embodiment a solar sail assembly including a solar sail and a solar sail attitude adjustment actuator as described above; specifically, the solar sail comprises a plurality of sail surface assemblies and a fixed shaft 3, all of the sail surface assemblies being disposed around the fixed shaft 3; the solar sail attitude adjusting actuators are arranged on the first sail surface 4 and the second sail surface 5, one side of the first sail surface 4 and one side of the second sail surface 5 are connected to a fixed truss 6, and one end of the fixed truss 6 is fixed on the fixed shaft 3; the first sail surface 4 and the second sail surface 5 are respectively connected with a movable truss 7 at one side far away from the fixed truss 6, and one end of the movable truss 7 is rotatably connected to the fixed shaft 3, specifically, one end of the movable truss 7 is rotatably connected to the fixed shaft 3 through a universal spherical hinge.
In this embodiment, the first sail surface 4 and the second sail surface 5 may be connected to the corresponding fixed truss 6 and movable truss 7 by means of connectors 8; the connection piece 8 may be selected according to specific working requirements, for example, a strap or a buckle may be selected.
In the embodiment, a single sail surface assembly is propped up by three trusses in total through a fixed truss 6 and two movable trusses 7; the fixed trusses 6 are fixed, play a supporting role on the solar sail, the two movable trusses 7 can be driven by the SMA-SMP actuator to bend, the sail surface of each part is controlled to deflect around the middle fixed shaft 3, and the deformation of the solar sail is realized. In this embodiment, the total area of the solar sail and the area distribution in different directions can be controlled by the cooperative deformation of the multiple parts, so as to control the stress on the solar sail, the moment and the direction, and further realize the propulsion and attitude control of the solar sail spacecraft.
In this embodiment, the sail cloth is preferably provided with four; alternatively, other numbers of sail surface assemblies may be selected, such as five or six sail surface assemblies, etc., depending on the particular operational requirements.
In this embodiment, the preset solar sail area is about 1200m 3 The mass of the solar sail is about 30kg, and the moment of inertia is about 70000 kg x m 2 The method comprises the steps of carrying out a first treatment on the surface of the Then, a circuit is built in the Simulink for simulating the movement of the solar sail after being subjected to force and moment. As shown in fig. 7, the simulation results show that the solar sail can be turned 22 ° in a period of 16 minutes, sufficient to control the attitude of the solar sail spacecraft in space.
There is also provided in this embodiment a spacecraft comprising a solar sail assembly as described above.
The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided to facilitate understanding of the method and core ideas of the present invention; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (10)
1. A solar sail deployment actuator, characterized by: comprising the following steps: the deformation layer is used for being laid on the back of the solar sail, and the deformation layer can deform to drive the solar sail to move, so that the posture of the solar sail is adjusted.
2. The solar sail formula adjustment actuator of claim 1, wherein: the deformation layer comprises an SMA piece and an SMP material layer, and the SMA piece is laid on at least one side of the SMP material layer; and the solar sail posture adjusting actuator further comprises a heating device, and the deformation layer can be deformed after being heated by the heating device.
3. The solar sail formula adjustment actuator of claim 2, wherein: the SMA piece is an SMA rod, the SMA rods are paved on two sides of the SMP material layer, the SMA rods on two sides are respectively arranged in an elastic material layer, and the elastic material layer is paved on two sides of the SMP material layer.
4. A solar sail formula adjustment actuator according to claim 3, wherein: the elastic material layer is a Veroclear elastic material layer.
5. The solar sail cloth adjustment actuator of any one of claims 2-4, wherein: the heating device comprises a power supply and a heating element, the SMA rod is electrically connected with the power supply, the heating element is arranged in the SMP material layer, the SMP material layer is reduced in hardness after being heated by the heating element, the SMA rod is deformed after being electrified and drives the SMP material layer to deform, and after the deformation is completed, the SMP material layer is heated to the transition temperature again to be capable of recovering the original state.
6. The solar sail cloth adjustment actuator of claim 5, wherein: the heating element is an electric heating wire, and the electric heating wire is electrically connected with the power supply.
7. A solar sail assembly, characterized by: comprising a solar sail as claimed in any one of claims 1-6.
8. The solar sail assembly of claim 7, wherein: the solar sail comprises a fixed shaft and a plurality of sail surface assemblies, and all the sail surface assemblies are arranged around the fixed shaft; the sail surface assembly comprises a first sail surface and a second sail surface, wherein one side of the first sail surface and one side of the second sail surface are connected to a fixed truss, and one end of the fixed truss is fixed on the fixed shaft; the first sail surface and the second sail surface are respectively connected with a movable truss on one side far away from the fixed truss, and one end of the movable truss is rotatably connected to the fixed shaft.
9. The solar sail assembly of claim 8, wherein: the sail surface assembly is provided with four.
10. A spacecraft, characterized in that: a solar sail assembly including any one of claims 7-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310976644.3A CN117002754A (en) | 2023-08-03 | 2023-08-03 | Solar sail attitude adjustment actuator, solar sail assembly and spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310976644.3A CN117002754A (en) | 2023-08-03 | 2023-08-03 | Solar sail attitude adjustment actuator, solar sail assembly and spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117002754A true CN117002754A (en) | 2023-11-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310976644.3A Pending CN117002754A (en) | 2023-08-03 | 2023-08-03 | Solar sail attitude adjustment actuator, solar sail assembly and spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117002754A (en) |
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2023
- 2023-08-03 CN CN202310976644.3A patent/CN117002754A/en active Pending
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