CN110884689A - Optical imaging satellite bottom light shield unfolding system - Google Patents
Optical imaging satellite bottom light shield unfolding system Download PDFInfo
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- CN110884689A CN110884689A CN201911209044.4A CN201911209044A CN110884689A CN 110884689 A CN110884689 A CN 110884689A CN 201911209044 A CN201911209044 A CN 201911209044A CN 110884689 A CN110884689 A CN 110884689A
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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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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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
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
- G02B7/18—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors
- G02B7/182—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors
Abstract
The invention provides an optical imaging satellite bottom light shield unfolding system which comprises a bottom light shield stretching mechanism (9) and a bottom light shield (8) arranged on the bottom light shield stretching mechanism, wherein the bottom light shield stretching mechanism (9) can open the bottom light shield (8) in the circumferential direction in a folding mode so as to shield a main reflector. The optical imaging satellite bottom light shield unfolding system utilizes the folding and stretching mechanism to carry out on-orbit unfolding, so that the structural size of the satellite meets the requirements of a fairing.
Description
Technical Field
The invention belongs to the technical field of satellites, and particularly relates to an optical imaging satellite bottom light shield unfolding system.
Background
The optical imaging satellite deployed in geostationary orbit (GEO) can realize long-term continuous monitoring and quick access imaging suitable for ground, when the satellite operates in the GEO orbit, the satellite is influenced by stray light such as sunlight, off-axis stray light enters an optical system of the satellite through radiation and finally reaches the position of a camera focal plane through a primary reflector and a secondary reflector, the target signal-to-noise ratio and the image plane contrast of the optical system of the satellite are reduced, target imaging is fuzzy, and the detection capability and the imaging performance of the satellite are further influenced. The light shield structure at the bottom of the optical primary mirror is usually a circular fixed structure covering the bottom of the satellite primary mirror.
The bottom light shield structure of the traditional satellite optical lens is generally of a fixed structure, and in order to realize the high resolution of the GEO high-resolution optical imaging satellite, the satellite main reflector needs a large caliber, the main reflector needs to be partitioned or folded at the beginning of launching, and the GEO high-resolution optical imaging satellite has the on-orbit unfolding capability.
Disclosure of Invention
The invention provides an optical imaging satellite bottom light shield unfolding system, which is used for carrying out on-orbit unfolding by utilizing a folding and stretching mechanism, so that the structural size of a satellite meets the requirement of a fairing.
The technical scheme of the invention comprises the following steps:
an optical imaging satellite comprises a primary mirror and secondary mirror telescopic system, a bottom light shield unfolding system, a side light shield unfolding system, a conformal structure, an optical camera and satellite subsystems, wherein:
the primary and secondary mirror telescopic system comprises a primary mirror capable of being opened in an extending mode towards the circumferential direction, a secondary mirror extending arm capable of being extended towards the length direction and a secondary mirror arranged at the end portion of the secondary mirror extending arm, wherein the secondary mirror extending arm is connected with the center of the primary mirror, and the primary mirror is opened to form an inwards concave spherical surface;
the bottom light shield unfolding system is arranged on the outer side of the main reflector of the primary and secondary mirror telescopic system and comprises a bottom light shield stretching mechanism and a bottom light shield installed on the bottom light shield stretching mechanism, and the bottom light shield stretching mechanism can open the bottom light shield towards the circumferential direction in a folding mode so as to shield the main reflector;
the side face light shield unfolding system comprises a top telescopic lantern ring support rod structure arranged at the top end of the secondary mirror stretching arm, a bottom folding rod arranged between the main mirror and the bottom light shield stretching mechanism, and a side face light shield connected between the main mirror and the bottom light shield stretching mechanism, wherein the top telescopic lantern ring support rod structure and the bottom folding rod can be opened towards the circumferential direction along with the stretching of the secondary mirror stretching arm, and the side face light shield is stretched and covered outside the secondary mirror stretching arm;
the conformal structure is arranged at the end part of the secondary mirror extending arm and is used for concentrically butting the secondary reflector and the communication antenna, wherein the communication antenna is positioned on the outer side of the secondary reflector;
the optical camera is arranged in a secondary mirror extending arm of the primary mirror and secondary mirror telescopic system.
The satellite subsystem comprises an attitude control system, an orbit control system, a power supply and distribution system, a thermal control system, a data management system, a camera and image processing system and a communication system;
the optical camera, the propellant storage tank of the propulsion system and other subsystems are fixed in the framework unit of the secondary mirror extending arm through a fixing structure;
the nozzle of the satellite propulsion subsystem is arranged at the bottom of the satellite, a hexagonal ring is fixed through six fixing supports connected to the base of the primary mirror, and the hexagonal ring is fixed on the periphery of the nozzle of the satellite propulsion subsystem so as to play a role in fixing the nozzle;
the propelling subsystem propellant storage tank is connected with the nozzle through a pipeline.
The primary mirror and the secondary mirror telescopic system are as follows:
the main reflector comprises a main mirror base, a plurality of main mirror supporting frameworks and mirror surface film traction frameworks which are uniformly hinged on the circumference of the main mirror base through self-locking joints driven by a motor and are arranged at intervals, an optical main reflector film connected to the main mirror supporting frameworks and the mirror surface film traction frameworks, and a motor for controlling the main mirror supporting frameworks and/or the mirror surface film traction frameworks to move.
The main mirror supporting framework and the mirror surface film traction framework are respectively provided with a plurality of main mirror supporting frameworks and a plurality of mirror surface film traction frameworks.
The optical main reflecting mirror film can be an integral annular film, and the main mirror supporting framework and the mirror surface film traction framework are bonded on the surface of the optical main reflecting mirror film; or a fan-shaped structure design, and two side edges of the optical main reflecting mirror film are respectively connected with the adjacent main mirror supporting framework and the mirror surface film traction framework.
The optical main reflecting mirror film material is a piezoelectric material lens made of polyvinylidene fluoride.
When the main reflector is contracted, the optical main reflector film is folded and stored in a zigzag manner.
The secondary mirror extending arm is composed of a plurality of framework units, two ends of each framework unit are of triangular frame structures, a transverse rod piece capable of being folded and stored inwards is arranged in the middle of each framework unit, a bending sleeve capable of being bent is arranged in the middle of each transverse rod piece, and the triangular frames at the two ends are connected through oblique-pulling springs.
The self-locking joint drives the worm to rotate by using the servo motor, and the worm rotates and drives the worm wheel meshed with the worm to rotate.
The secondary mirror extending arm is installed in the fairing in a folded state before being launched, and the installation structure in the fairing provides restraint force for the secondary mirror extending arm.
The secondary reflector of the optical system is a parabolic curved surface-shaped thin-wall structural part with a certain thickness.
Wherein the conformal structure:
after the secondary reflector and the communication antenna are in butt joint connection, the curvature radius of the communication antenna is smaller than that of the secondary reflector, six fixing support frames are uniformly arranged in a gap formed between the non-connecting positions of the secondary reflector and the communication antenna, the fixing support frames are of a trapezoidal structure, and radians matched with the corresponding connecting surfaces are arranged on two side edges of the fixing support frames.
The fixed support frame is connected with a communication antenna feed source support structure, and the communication antenna feed source support structure is fixedly connected with a communication antenna feed source in a triangular support mode, so that the communication antenna feed source is located at the focus of the communication antenna.
And the center of the outer side surface of the secondary reflector is provided with an optical system secondary reflector fixing structure which is used for being connected with a secondary reflector extending arm.
The optical system secondary reflector fixing structure is a circular or polygonal boss.
The optical system secondary reflector and the communication antenna are made of carbon fiber composite materials, and meanwhile, the thin-wall bottom surface of the optical system secondary reflector is plated with a layer of aluminum film.
The secondary reflector and the communication antenna adopt the same aperture size.
Wherein the side shade deployment system:
the bottom folding rod mainly comprises a folding rod upper section, a folding rod lower section, a folding rod fixing section and a motor-driven self-locking joint, the non-hinged end of the folding rod lower section is fixedly connected with the side face light shield, and the folding rod upper section and the folding rod lower section are folded and stored together and then are vertically folded towards the inner side of the folding rod fixing section.
The flexible lantern ring bracing piece structure in top is including the fixed lantern ring, the flexible lantern ring, the lead screw guide rail, the ball sleeve, the bracing piece, the support arm, the hinge, the bracing piece stiff end, the triangle is fixed to the guide rail, fixed lantern ring fixed connection is at the tip of secondary mirror extending arm, the lead screw guide rail is vertical to be connected with the fixed lantern ring, the flexible lantern ring can gliding connection so that it can slide along the lead screw guide rail on the lead screw guide rail, the protruding setting of hinge is being told still fixedly, every hinge is connected with a bracing piece, the bracing piece is connected with the side lens hood, the middle part of every bracing piece is articulated with the one end of a support arm, the other end of support arm is articulated with the flexible lantern ring, and the length of.
The bottom end of the lead screw guide rail is fixedly connected with the triangular guide rail in a triangular mode.
The lead screw guide rail comprises lead screw, lead screw mount pad, step motor, and lead screw mount pad top links firmly with the fixed lantern ring, and the bottom links firmly with the fixed triangle of guide rail, and step motor installs in the lead screw mount pad and drives the lead screw at the internal rotation of lead screw mount pad.
The end part of the supporting rod is provided with a bending part for being connected with the side face light shield.
The side face light shield adopts a flexible solar cell, and the solar cell is used for supplying power to a power supply system of the satellite.
Bottom hood deployment system among them:
the bottom light shield extension mechanism is arranged on the outer side of the main mirror base and comprises a toothed ring annular guide rail, a guide rail slide block arranged on the toothed ring annular guide rail, a self-locking joint driven by a motor and a bottom light shield extension arm connected to the guide rail slide block.
The bottom light shield extending arm is provided with a hollow groove structure, and an aluminized polyimide film is stacked in the groove.
The bottom light shield adopts an aluminized polyimide film or a flexible solar cell.
The bottom shade is received in a slot in a side of the bottom shade extension arm.
The fixed lens hood is arranged in the main mirror base.
A plurality of fixed supports pointing to the center are arranged in the main mirror base, and the fixed supports are fixedly connected with the nozzle of the propellant box of the propulsion system.
The self-locking joint drives the worm to rotate by using the servo motor, and the worm rotates and drives the worm wheel meshed with the worm to rotate.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
Fig. 1 is a schematic diagram of a usage state of a GEO high-resolution reflective optical imaging satellite.
Fig. 2 is a schematic diagram of the usage state of the GEO high resolution reflective optical imaging satellite without the light shield.
Fig. 3 is a schematic diagram of a contracted state of a GEO high-resolution reflective optical imaging satellite.
FIG. 4 is a schematic diagram of the folded state of the main mirror.
FIG. 5 is a schematic view of the open state of the main mirror.
Fig. 6 is a block diagram of a conformal structure of a secondary mirror and a communication antenna.
Fig. 7 is a cross-sectional structural view of a conformal structure of a secondary mirror and a communication antenna.
Fig. 8 is a bottom view of the conformal structure of the secondary mirror and the communication antenna.
Fig. 9 is a schematic diagram of the structural unit of the secondary mirror extending arm.
Fig. 10 is a schematic view of the structural unit of the secondary mirror extending arm.
Fig. 11 is a schematic view of the structural unit of the secondary mirror extending arm.
FIG. 12 is a schematic diagram of the satellite subsystem assembly.
Figure 13 is a schematic view of the connection of a satellite propellant tank to the base of a primary mirror.
Fig. 14 is a schematic view of the light shield extending mechanism in a retracted state.
Fig. 15 is a schematic view of the extending state of the shade extending mechanism.
Figure 16 is a schematic view of the top telescoping collar support rods in a collapsed state.
Fig. 17 is a schematic view of the opened state of the top telescopic collar support rod.
Fig. 18 is a schematic structural view of a lead screw guide rail.
Fig. 19 is a schematic view of the bottom shade extension mechanism in a retracted state.
Fig. 20 is a schematic view showing an opened state of the bottom shade extension mechanism.
Fig. 21 is a schematic structural view of the main mirror base.
FIG. 22 is a schematic diagram of a sub-mirror of the optical system.
In the figure:
1. a main mirror; 2. a conformal structure; 3. an optical camera; 4. a secondary mirror extending arm; 5. a side light shield; 6. a bottom folding bar; 7. a top telescopic lantern ring support rod structure; 8. a bottom light shield; 9. a bottom hood extension mechanism; 10. a satellite subsystem; 11. an optical main mirror film; 12. a primary mirror support skeleton; 13. a mirror film traction framework; 14. a main mirror base; 15. a joint capable of self-locking; 14A, a circumscribed ring; 14B, a main beam;
21. an optical system secondary mirror; 22. a communication antenna; 23. a communication antenna feed; 24. a communications antenna feed support structure; 25. fixing a support frame; 26. a secondary mirror fixing structure of the optical system;
41. a frame unit; 41A, a longitudinal rod; 41B, a transverse rod piece; 41C, a torsion spring; 41D, spherical hinge; 41E, a spring;
61. an upper section of the folding rod; 62. a lower section of the folding rod; 63. a folding rod fixing section; 64. a joint capable of self-locking; 65. a joint capable of self-locking;
71. a fixed collar; 72. a telescopic lantern ring; 73. a lead screw guide rail; 731. a lead screw; 732. a guide rail mounting seat; 733. a stepping motor; 74. a ball sleeve; 75. a support bar; 76. a support arm; 77. hinging; 78. a fixed end of the support rod; 79. a guide rail fixing triangle;
81. a light shield at the periphery of the main mirror base;
91. an annular guide rail with a gear ring; 92. a guide rail slider; 93. a joint capable of self-locking; 94. a bottom hood extension arm;
101. a spout; 102. a propulsion system propellant tank; 103. other subsystems; 104. fixing a bracket; 105. a hexagonal ring; 106. and (5) fixing the structure.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the specific embodiments of the present invention and the accompanying drawings. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The GEO high-resolution reflective optical imaging satellite of the invention, as shown in fig. 1 and 2, is composed of a satellite optical system main reflector 1, a conformal structure 2 of an optical system secondary reflector 21 and a communication antenna 22, an optical camera 3, a secondary mirror extending arm 4, a side light shield 5, a bottom folding rod 6, a top telescopic lantern ring supporting rod structure 7, a bottom light shield 8, a bottom light shield extending mechanism 9 and a satellite subsystem 10.
The main reflector 1 can be opened in a stretching mode towards the circumferential direction, the secondary reflector stretching arm 4 can be extended towards the length direction, the secondary reflector 21 is installed at the end of the secondary reflector stretching arm 4, the secondary reflector stretching arm 4 is connected with the center of the main reflector 1, and the main reflector 1 is opened to form an inwards concave spherical surface.
The bottom hood 8 and the bottom hood extension mechanism 9 constitute a bottom hood deployment system, and are arranged outside the primary mirror 1 of the primary and secondary mirror telescopic system. The bottom shade extension mechanism 9 is foldable to open the bottom shade 8 in the circumferential direction to shield the main mirror.
The conformal structure 2 is arranged at the end of the secondary mirror extending arm 4, and the secondary mirror 21 and the communication antenna 22 are concentrically butted, wherein the communication antenna 22 is positioned at the outer side of the secondary mirror 21.
The optical camera 3 is installed in a secondary mirror extending arm 4 of the primary and secondary mirror telescopic system.
As shown in fig. 3, to reduce the satellite volume, the GEO high resolution reflective optical imaging satellite is in a folded compressed state prior to launch. The designed GEO high-resolution reflection type optical imaging satellite can realize that the aperture of the optical system main reflection mirror 1 required by the ground 2m ultrahigh resolution is 12m and the curvature radius is 144 m; the aperture of the secondary reflector of the optical system is 4.2m, and the curvature radius is 143.9 m; the distance between the primary mirror and the secondary mirror is 46.8 m; the distance between the focal point and the vertex of the primary mirror is 8.02m, and these parameters may vary depending on the choice of resolution.
Regarding the primary and secondary mirror telescopic systems:
the satellite is in a compressed state before launch, as shown in figure 4, the satellite optics primary mirror 1 is folded. The satellite optical main reflector 1 adopts a film unfolding design, 24 fan-shaped optical main reflector films 11 are supported by 12 main mirror supporting frameworks 12 and 12 mirror surface film traction frameworks 13, and the 12 main mirror supporting frameworks 12 and the 12 mirror surface film traction frameworks 13 are both bent rib plates with certain curvature and are connected with a main mirror base 14 through 24 self-locking joints 15 driven by motors. The self-locking joint utilizes the servo motor to drive the worm to rotate, the worm rotates to drive the worm wheel meshed with the worm to rotate, and the joint self-locking function is realized through the design that the lead angle of the worm is smaller than the friction angle of meshing contact. After the satellite is launched into orbit, the 24 motors arranged at the bottom of the main mirror supporting framework 12 drive the 12 main mirror supporting frameworks 12 and the 12 mirror surface film traction frameworks 13 to move around the motor-driven self-locking joints 15, so that the optical main mirror film 11 is unfolded, the motor stops working after the main mirror film 11 is completely unfolded, and the structure of the unfolded optical main mirror 1 is shown in fig. 5.
The base 14 of the main mirror is provided with a force bearing mechanism which is an equilateral 12-edge ring, and a preset space is reserved for the 24 skeletons of the main mirror to gather and fold towards the middle. 12 main mirror supporting skeletons 12 are extended out of the top points of 12 side rings of the main mirror base 14, and 12 mirror surface film traction skeletons 13 are extended out of the middle points of each side length of the 12 side rings. The 24 skeletons and the main mirror base 14 jointly form the main structure of the main mirror 1, and the main mirror 1 is folded and unfolded through the self-locking joint 15 driven by the motor. In addition, a round hole is designed at the intersection of the 12 main mirror supporting frameworks 12 and the 12 mirror surface film traction frameworks 13, and a reserved space is reserved for pipeline arrangement of the rail control subsystem. The main mirror supporting framework 12 and the mirror surface film traction framework 13 are fixedly connected with the optical main mirror film 11. The optical primary mirror film 11 is made of a piezoelectric material lens made of polyvinylidene fluoride, and the shape of the optical primary mirror film is rapidly changed under scanning of an electron gun controlled by a computer. The light film structure is folded, launched and expanded in orbit, and the error of mirror surface formation is controlled by an electron gun to be not more than 2.5 multiplied by 10-5mm, and the density of the used piezoelectric material polyvinylidene fluoride is not more than 1kg/m, thereby meeting the design requirement of the satellite primary mirror to a great extent.
The sub-mirror structure is composed of a sub-mirror 21 and an optical system sub-mirror fixing structure 22, as shown in fig. 21. The optical system sub-mirror 21 is a thin-walled parabolic curved surface structure having a certain thickness, and the radius of curvature of the curved surface is 143.9m according to the design parameters of the sub-mirror. The secondary mirror 21 is fixedly connected to the optical system secondary mirror fixing structure 22. The optical system sub-mirror fixing structure 22 is a 12-sided ring structure. Meanwhile, the thin-wall bottom surface of the optical system secondary reflector 21 is coated with an aluminum film to reflect light.
After the GEO high-resolution optical satellite is launched into orbit, the distance between the optical system main reflector 1 and the optical system secondary reflector 21 needs to reach tens of meters to meet the imaging requirement of the optical system 2m resolution of the satellite. The satellite at the height can not be launched into orbit once by rocket carrying, so a foldable and expandable secondary mirror extending arm 4 is required to be added between the optical system main reflecting mirror 1 and the optical system secondary reflecting mirror 21 to meet the on-orbit working requirement of the satellite. The secondary mirror extending arm is installed in the fairing in a folded state before being launched, the secondary mirror extending arm is not unfolded due to the constraint force of the installation structure in the fairing (for example, two ends of the folded secondary mirror extending arm are provided with an openable locking connecting rod, and the locking connecting rod can be opened under the control of a motor), after the satellite flies away from the fairing, the constraint force disappears after unlocking, and the secondary mirror extending arm is unfolded in a one-section mode under the gravity-free state due to the elastic potential energy of a torsion spring.
As shown in fig. 9, the secondary mirror extending arm 4 is composed of a plurality of frame units 41. The frame unit is composed of a longitudinal rod 41A, a transverse rod 41B, a bending sleeve 41C, a spherical hinge 41D, a spring 41E and the like. The 3 thin-wall strip-shaped longitudinal rods 41A are fixedly connected at the head to form a rigid triangular plane so as to achieve good supporting stability, and meanwhile, compared with a quadrilateral structure, the thin-wall strip-shaped longitudinal rods are less in material and lighter in structure; the 3 crossbars 41A are connected to a rigid triangular plane by means of spherical hinges 41D to form a rectangle and are fixed at each diagonal of the rectangle with a spring 41E and at the crossbars at their midpoints by means of a curved sleeve 41C.
As shown in fig. 10, the frame unit 41 is in a compressed state before the satellite is launched into orbit. The rod piece 41B is folded in half towards the rigid triangular plane centroid formed by the longitudinal rod piece 41A through the middle high-rigidity torsion spring 41C, the high-rigidity torsion spring 41C deforms to store elastic potential energy, no elastic potential energy exists when the upper rod and the lower rod are positioned on a straight line, and meanwhile, the spring 41E arranged at the diagonal position of the rectangular plane formed by hinging the transverse rod piece 41B and the longitudinal rod piece 41A is compressed (no elastic potential energy exists when the transverse rod piece 41B is positioned on a straight line, namely, the spring 41E does not have an elastic action at the moment); when the constraint force disappears during the in-orbit operation of the satellite, the elastic potential energy stored in the high-stiffness torsion spring 41C and the compression spring 41E is converted into kinetic energy, so that the whole secondary mirror extending arm 4 is unfolded, as shown in fig. 11. The plurality of frame units 41 share a rigid triangle to form the secondary mirror extending arm 4.
The invention has the following characteristics:
1. the light path design of the double-reflection optical imaging system realizes that the main reflector and the secondary reflector are positioned at the same side of the focus of the main reflector, and the object and the image are respectively positioned at two sides of the secondary reflector, thereby reducing the actual length of the light path.
2. And designing parameters of a primary mirror and a secondary mirror of the optical system with 2m resolution of geostationary orbit.
3. The folding mechanism of the secondary mirror extending arm of the optical system with 2m resolution of geostationary orbit is designed.
4. The foldable and unfoldable film main reflector of the GEO optical imaging satellite comprises a fan-shaped optical main reflector film, a main mirror supporting framework, a mirror surface film traction framework, a main mirror base and a motor-driven self-locking joint.
5. The main mirror supporting framework and the mirror surface film traction framework are both bent rib plates with certain curvature.
6. The primary mirror of the GEO high-resolution optical satellite is folded before the orbit and unfolded after the orbit.
7. The film type primary mirror is driven to fold and unfold by a motor-driven primary mirror supporting framework and a mirror surface film traction framework through the rotation of a self-locking joint driven by the motor.
8. The optical main reflector film material is a piezoelectric material lens made of polyvinylidene fluoride, and an electron gun is utilized to control the mirror surface forming error.
9. The main mirror base, the main mirror supporting framework and the mirror surface film traction framework are made of carbon fiber materials.
Effects of the invention
1. The reflective optical imaging system is utilized to realize 2m high-resolution imaging of the static orbit, and chromatic aberration does not exist;
2. the main reflector and the secondary reflector are positioned at the same side of the focus of the main reflector, so that the actual length of a light path is reduced;
3. the object and the image are respectively positioned at the two sides of the secondary reflector, so that the difficulty of the manufacturing process is reduced;
5. the foldable and unfoldable film main reflector of the GEO optical imaging satellite is designed, and a film is pulled by using a film supporting framework to be in a folded state before the satellite enters the orbit, so that the overall size of the satellite is greatly reduced, and the satellite can be directly placed into a satellite fairing after being folded;
6. the flexible thin film material adopted by the satellite is used as the material of the main reflector, so that the use of rigid materials is avoided, the structural weight of the whole satellite is greatly reduced, and the satellite can realize one-time orbit entering under the existing condition.
With respect to the conformal structure 2:
when the satellite works, light reflected by the optical system main reflecting mirror 1 is reflected for the second time by the optical system secondary reflecting mirror 21. Meanwhile, in order to keep the satellite effectively communicated with the ground in the GEO orbit, a communication antenna needs to be additionally arranged on the satellite. And in order to utilize the existing structure of the satellite to the maximum extent, the parts of the satellite are reduced. As shown in fig. 6, the conformal structure of the satellite secondary reflector and the communication antenna is composed of an optical system secondary reflector 21, a communication antenna 22, a communication antenna feed 23, a communication antenna feed support structure 24, a fixed support frame 25 and an optical system secondary reflector fixing structure 26.
As shown in fig. 7, which is a cross-sectional view of a conformal structure of a satellite secondary reflector and a communication antenna, the optical system secondary reflector 21 and the communication antenna 22 are two parabolic curved surface-shaped thin-wall structural members with the same caliber and different curvatures, and the bottoms of the two thin walls are overlapped and fixedly connected to the optical system secondary reflector fixing structure 25. Usually, after the secondary reflector 21 and the communication antenna 22 are connected in a butt joint manner, the curvature radius of the communication antenna 22 is smaller than that of the secondary reflector 21, six fixing support frames 25 are uniformly arranged in a gap formed between the non-connection positions of the two, the fixing support frames 25 are in a trapezoidal structure, and two side edges of the fixing support frames have radians matched with corresponding connection surfaces. As shown in fig. 8, the optical system secondary reflector fixing support frame 25 has a 12-sided ring structure, and is fixedly connected to the optical system secondary reflector 21, and an end surface connected to the optical system secondary reflector 21 has the same curvature as that of the optical system secondary reflector 21, so that it can better support the optical system secondary reflector 21. And the optical system secondary reflector fixing support frame 25 is fixedly connected with the secondary reflector extending arm 4 of the GEO optical satellite.
The optical system secondary reflector 21 and the communication antenna 22 are supported by a fixed support frame 25, and the structural stability and structural strength are ensured. The fixed support 25 is a quadrilateral support with a certain thickness, the upper side and the lower side of the quadrilateral support are provided with curves attached to the two structures and are respectively welded and fixed with the optical system secondary reflector 21 and the communication antenna 22, and the left side and the right side of the quadrilateral support are vertical support beam structures. Six fixed support frames 25 are distributed between the optical system secondary reflector 21 and the communication antenna 22.
Every two fixed supporting frames 25 are fixed with a rod-shaped communication antenna feed source supporting structure 24 and extend out to the focus of the communication antenna 22, and the three communication antenna feed source supporting structures 24 are connected with the communication antenna feed source 23, so that the communication antenna feed source 23 is positioned at the focus of the communication antenna 22, and communication between a satellite and the ground is realized. The optical system secondary reflector 21 and the communication antenna 22 are made of carbon fiber composite materials, and meanwhile, an aluminum film is plated on the thin-wall bottom surface of the optical system secondary reflector 21 to reflect light.
The optical system sub-mirror fixing structure 26 is a ring-shaped or polygonal boss.
The invention has the following characteristics:
1. the conformal structure is composed of an optical system secondary reflector and two parabolic curved surface thin-wall structural members with different curvatures of the communication antenna, and bears double functions of reflecting light rays and communicating.
2. The secondary reflector of the optical system is superposed with the bottoms of the two thin-wall structures of the communication antenna, and the middle part of the secondary reflector is supported by a fixed structure to ensure the structural strength and stability.
3. Three rod-shaped communication antenna feed source supporting structures uniformly extend out of the edge of the thin-wall structure of the communication antenna to be connected with a communication antenna feed source, so that the communication antenna feed source is positioned at the focus of the communication antenna.
4. The secondary reflector of the optical system and the communication antenna adopt the same caliber size, and the volume of the satellite is reduced by adopting a stacking installation mode.
5. The thin-wall bottom surface of the optical system secondary reflector is plated with an aluminum film to reflect light.
The present embodiment implements a conformal design of the optical system secondary mirror and the communication antenna. The secondary satellite reflector performs double functions, when the GEO optical imaging satellite performs optical imaging on the ground, the concave surface of the secondary satellite reflector faces the ground and serves as a parabolic antenna to communicate with the ground, and the convex surface of the secondary reflector serves as the secondary reflector of the satellite optical system to converge reflected light of the primary reflector for optical reflection. The existing structure of the satellite is utilized to the maximum extent, the parts of the satellite are reduced, and the volume of the optical satellite is compressed.
As shown in fig. 12, the satellite adopts a distributed design concept in the design of subsystems, and the satellite subsystem 10 is inserted into the satellite by using the satellite body as a loading platform, wherein the satellite subsystems are respectively: the system comprises an attitude control system, an orbit control system, a power supply and distribution system, a thermal control system, a data management system, a camera shooting and image processing system and a communication system, wherein the control systems can be configured by adopting a system commonly used by the current satellite. As shown in fig. 10, the optical camera 3, the propulsion system propellant tank 102 and other subsystems 103 are fixed in the frame units 41 of the secondary mirror extending arms 4 by fixing structures 106, and these frame units 41 are free of the bending sleeve 41C and are not folded before the satellite orbit. The structural shape and the installation fixing position of each subsystem can be specifically designed and installed according to tasks. The nozzle 101 of the satellite propulsion subsystem is arranged at the bottom of a satellite, a hexagonal ring 105 is fixed through six fixing supports 104 connected to the base 14 of the primary mirror, and the hexagonal ring 105 is fixed on the periphery of the nozzle 101 of the satellite propulsion subsystem so as to play a role in fixing the nozzle 101. Propellant subsystem propellant tank 102 is connected to nozzle 101 by tubing. The distributed design concept adopted in the design of the subsystems innovates the design concept of the traditional satellite platform-load, breaks through the platform limitation of the traditional satellite, realizes the flexible design of the subsystems-main body framework, and reduces the space and the weight required by the whole satellite.
As shown in fig. 13, in order to ensure that the connection between the secondary mirror extending arm 4 and the primary mirror 1 of the satellite optical system meets the force-bearing requirement, a rigid triangle of a construction unit where the satellite propulsion subsystem propellant storage tank 102 is located is taken as a reference, an external circular ring 14A is poured to connect and extend a support of the primary mirror 1 of the satellite optical system, and the circular ring is in contact fixed connection with 24 skeletons of the primary mirror, so that uniform force bearing can be realized. Meanwhile, 3 main beams 14B extend out of 12 side rings of the main mirror base 14 to be fixedly connected with the rigid triangular vertex on the external circular ring 14A, and the force bearing structure design of the connection part of the whole secondary mirror extending arm 4 and the main mirror 1 of the satellite optical system is completed.
Regarding the side shade deployment system:
as shown in fig. 1 and 2, in order to eliminate the influence of stray light such as sunlight on the satellite optical system, a light shield structure needs to be added to the satellite. The shade system comprises side shades 5 and bottom shades 8. The side shade 5 is supported by a bottom folding bar 6 and a top telescoping collar support bar structure 7. The bottom folding bar 6 serves to fix the lower end of the side light shield 5 for a total of six. When the satellite is in-orbit, the side shade 5 is extended in cooperation with the top telescopic collar support rod 7, as shown in fig. 14, and the bottom folding rod 6 is of a segmented structure.
As shown in fig. 15, the bottom folding rod 6 mainly includes an upper folding rod section 61, a lower folding rod section 62, a fixing folding rod section 63, a motor-driven self-lockable joint 64 between the upper folding rod section 61 and the lower folding rod section 62, and a motor-driven self-lockable joint 65 between the upper folding rod section 61 and the fixing folding rod section 63, and the upper folding rod section 61 and the lower folding rod section 62 are folded and stored together and then vertically folded toward the inside of the fixing folding rod section 63. In order to ensure that the bottom folding rod 6 does not contact the satellite optical system main reflector 1 during folding, a folding rod fixing section 63 extends out from the main reflector base 14 for a certain distance, the folding rod fixing section 63 is connected with the folding rod upper section 61 through a self-locking joint 64 driven by a motor, a reverse folding structure is adopted, the folding rod fixing section 63 is vertically folded upwards and is connected with the folding rod lower section 62 through a self-locking joint 65 driven by the motor; the lower folding bar segment 62 folds vertically downward. The non-hinged end of the lower section 62 of the folding bar is fixedly connected with the side shade 5.
As shown in fig. 16. When the satellite is unfolded in orbit, the peripheral shading cloth is driven to be unfolded to form a complete folding rod, and therefore a supporting structure for drawing the shading cloth is formed at the bottom of the satellite.
The top telescopic lantern ring support rod 7 is used for extending the side shade 5 in cooperation with the bottom folding rod 6, as shown in fig. 17, the top telescopic lantern ring support rod 7 structurally comprises a fixed lantern ring 71, a telescopic lantern ring 72, a screw guide rail 73, a ball sleeve 74, a support rod 75, a support arm 76, a hinge 77, a support rod fixing end 78 and a guide rail fixing triangle 79. The fixed lantern ring 71 is fixedly connected to the end of the secondary mirror extending arm 4, the lead screw guide rail 73 is longitudinally connected with the fixed lantern ring 71, the telescopic lantern ring 72 can be slidably connected to the lead screw guide rail 73 to enable the telescopic lantern ring to slide along the lead screw guide rail 73, the hinges 77 are convexly arranged on the fixed lantern ring 71, each hinge 77 is connected with one support rod 75, the free end of each support rod 75 is connected with the side light shield, the middle of each support rod 75 is hinged to one end of one support arm 76, the other end of each support arm 76 is hinged to the telescopic lantern ring 72, and the length of each support arm 76 is larger than the length from the joint position of the support rods 75 to the hinge 77 and is smaller than the length. The fixed collar 71 is a circular ring and is fixedly connected to the rigid triangle on the upper surface of the frame unit 41 at the uppermost end of the secondary mirror extending arm 4. Three lead screw guide rails 73 vertically penetrate through the rigid triangular connection part of the fixed lantern ring 71 and the upper surface of the framework unit 41, and the lead screw guide rails 73 are fixedly connected with the fixed lantern ring 71. The top ends of the 3 lead screw guide rails 73 are at a certain distance from the fixed lantern ring 71 and are fixedly connected with the optical system secondary reflector fixing structure 25, and the supporting effect on the optical system secondary reflector 2 is achieved.
As shown in fig. 18, the three lead screw guide rails 73 are composed of a lead screw 731, a lead screw mounting seat 732 and a stepping motor 733, the top end of the lead screw mounting seat 732 is fixedly connected with the fixed lantern ring 71, the bottom of the lead screw mounting seat is fixedly connected with the guide rail fixing triangle 79, and the stepping motor 733 is mounted in the lead screw mounting seat and drives the lead screw 731 to rotate in the lead screw mounting seat. The fixed lantern ring 71 is uniformly extended with 6 supporting rod fixing ends 78 with certain length around the excircle, and the supporting rod fixing ends 78 are connected with the supporting rod 75 through a spherical hinge 77. The support bar 75 is formed by connecting two sections of slender rods, and an obtuse angle is formed between the two rods. The top end of the support bar 75 is connected with the shade cloth. The telescopic collar 72 and the fixed collar 71 are both circular rings, and the telescopic collar 72 is moved on the screw guide 73 by the ball sleeve 74. One end of the support arm 76 is hinged to the support bar 75, and one end is hinged to the sliding sleeve. As shown in fig. 15, the top retractable lantern ring support rod 7 is folded before the satellite enters the orbit, and the retractable lantern ring 72 moves downwards along the lead screw guide rail 73 until the support arm 76 is parallel to the guide rail. After the satellite enters the orbit, the stepping motor connected with the guide rail of the screw structure rotates to drive the ball sleeve 74 with the balls mounted inside to move upwards along the screw guide rail 73, so as to drive the supporting arm 76 and the supporting rod 75 to expand, and the satellite shading cloth is driven to extend in the orbit from the top.
As shown in fig. 3, the side face light shield 5 of the GEO high resolution optical imaging satellite is folded around the folding optical system main reflector 1 before the satellite is launched, and the folding is divided into radial compression folding and axial layered folding. Radial folding is the cockscomb structure folding, and its top is connected with top telescopic lantern ring bracing piece structure 7 and bottom folding rod 6 respectively with the bottom, and when bottom folding rod 6 expandes simultaneously with top telescopic lantern ring bracing piece structure 7, outside extension along the circumference of side lens hood 5, the grow thereupon of sawtooth folding angle, total girth grow, the folding lens hood of cockscomb structure expandes completely and is the hexagon. When the secondary mirror extending arm 4 is unfolded, because the uppermost end of the secondary mirror extending arm is fixedly connected with the fixed sleeve ring 71 of the top telescopic sleeve ring support rod, when the secondary mirror extending arm 4 moves upwards, the top telescopic sleeve ring support rod structure 7 is driven to move upwards, so that the side light shield 5 is driven to stretch along the radial direction, and after the secondary mirror extending arm is completely extended on the track, as shown in fig. 1, a 6-surface giant light shielding structure can be formed. In order to fully utilize the structure, the satellite is designed to adopt a flexible solar cell as a side face shading cover 5, and the flexible solar cell is used for shading the optical system of the satellite and supplying power to the satellite as an energy system of the satellite.
The invention has the following characteristics:
a self-unfolding solar cell shade around a GEO optical imaging satellite is supported and unfolded by a top telescopic lantern ring support rod structure and a top telescopic lantern ring folding rod structure.
2. The bottom folding rod is of a reverse folding structure, and the top telescopic lantern ring supporting rod and the traction mechanism of the shading cloth at the periphery of the satellite are folded and contracted along with the main framework of the satellite and extend in an orbit, so that the size of the shading structure at the periphery of the satellite meets the requirements of the fairing.
3. The flexible solar cell is used as peripheral shading cloth of the satellite, and the flexible solar cell is used as an energy system of the satellite to supply power to the satellite while shading the optical system of the satellite, so that the structure of the satellite is reduced, and the overall weight of the satellite is reduced.
Effects of the invention
The invention designs a self-unfolding solar cell lens hood around a GEO optical imaging satellite, wherein the lens hood is in a folded state before the satellite enters the orbit, the lens hood can be unfolded by utilizing a top telescopic lantern ring support rod structure 7 and a bottom folding rod 6, a foldable solar cell is adopted as an outer layer structure of the lens hood and can be used as an energy system of the satellite to supply power to the satellite, and the design of the folding and unfolding type lens hood enables the GEO optical imaging satellite to enter the orbit once under the existing condition.
Regarding the bottom hood deployment system:
as shown in fig. 1 and 2, in order to eliminate the influence of stray light such as sunlight on the satellite optical system, a light shield structure needs to be added to the satellite. The GEO optical imaging satellite lens hood comprises a side lens hood 5 and a satellite bottom expandable lens hood 8. The bottom expandable light shield 8 of the GEO optical imaging satellite consists of two parts, namely a fixed light shield inside the main mirror base and an expandable light shield outside the main mirror base. The external expandable light shield of the main mirror base is composed of a foldable light shield cloth 81 and a bottom light shield extending mechanism 9.
In addition to the side of the satellite needing shading, the bottom of the satellite also needs shading. The light shield 81 on the periphery of the main mirror base is unfolded by the bottom light shield extending mechanism 9, as shown in fig. 19, the bottom light shield extending mechanism 9 is composed of a toothed ring annular guide rail 91, 1 guide rail slide block 92, 2 motor-driven self-locking joints 93 and 2 bottom light shield extending arms 94. Before the satellite enters the orbit, 2 annular guide rail sliders 92, 2 motor-driven self-locking joints 93 and 2 bottom light shield extension arms 94 are arranged in parallel, the bottom light shield extension mechanism 9 is in a compressed state, and the bottom light shield extension arms 94 rotate around the motor-driven self-locking joints 93 to be in a vertical state. The bottom hood extension arm 94 is of a hollow groove structure, aluminum-plated polyimide films are stacked in the groove, when a satellite enters a track, as shown in fig. 20, the bottom hood extension arm 94 rotates around a self-locking joint 93 driven by a motor to be in a horizontal state, an annular guide rail 91 with a gear ring is fixed, a gear is installed in a guide rail slider 92 and is meshed with the gear ring of the annular guide rail, the motor driving gear installed on the guide rail slider moves along the circumference of the annular guide rail 91 with the gear ring, the bottom hood extension arm 94 is fixed on the annular guide rail slider 92 and moves along with the movement of the annular guide rail slider 92, so that the two bottom hood extension arms 94 are separated, the aluminum-plated polyimide films stacked in the folding rod are stretched, a webbed metal wire mesh is embedded in the aluminum-plated polyimide films, the metal wire mesh and the aluminum-plated polyimide films are manually folded in the hollow groove structure of the bottom hood extension arm 94 before entering the track, after entering the orbit, the wire mesh is gradually unfolded along with the unfolding of the aluminized polyimide film to support the whole circular light shield structure, as shown in fig. 20, a complete circular light shield structure is formed at the bottom of the satellite.
The self-locking joint utilizes the servo motor to drive the worm to rotate, the worm rotates to drive the worm wheel meshed with the worm to rotate, and the joint self-locking function is realized through the design that the lead angle of the worm is smaller than the friction angle of meshing contact.
As shown in fig. 21, the structure within the 12 side rings of the main mirror base 14 does not change during the entire launching process, so in the initial structural design of the satellite, an aluminized polyimide film (PI) is directly used as a light-shielding cloth to wrap the satellite structure within the side rings of the main mirror base 14, and the side rings of the main mirror base 14 and the 6 fixing brackets 104 of the nozzle fixing bracket are used for drawing, so that the nozzle is arranged outside the light shield.
The invention has the following characteristics:
the bottom-expandable light shield of the GEO optical imaging satellite consists of a fixed light shield inside a main mirror base and an expandable light shield outside the main mirror base.
2. The external extensible lens hood of the main mirror base is composed of a bottom lens hood extending mechanism and foldable light shielding cloth, the bottom lens hood extending mechanism is in a folded state before satellite launching, and the foldable light shielding cloth is stacked in a hollow groove in the bottom lens hood extending mechanism.
3. The material of the foldable shade cloth is aluminized polyimide film (PI)
4. The bottom light shield extension mechanism utilizes a motor to drive the annular guide rail slide block to open the foldable light shield cloth in a fan shape along the annular guide rail.
5. The fixed lens hood in the main mirror base utilizes the spray pipe fixing support to fix the lens hood.
Effects of the invention
The invention designs a bottom-extensible lens hood of a GEO optical imaging satellite, overcomes the defect that a traditional lens hood fixing structure cannot be folded, is suitable for shielding the bottom of a foldable primary mirror of the GEO optical imaging satellite, and reduces the occupied space of the lens hood, so that the GEO optical imaging satellite can be launched into the orbit at one time under the existing condition.
In summary, it is readily understood by those skilled in the art that the advantageous modes described above can be freely combined and superimposed without conflict.
The above description is only an example of the present invention, and is not intended to limit the present invention, and it is obvious to those skilled in the art that various modifications and variations can be made in the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.
Claims (8)
1. The bottom light shield unfolding system for the optical imaging satellite is characterized by comprising a bottom light shield stretching mechanism (9) and a bottom light shield (8) arranged on the bottom light shield stretching mechanism, wherein the bottom light shield stretching mechanism (9) can open the bottom light shield (8) in the circumferential direction in a folding mode so as to shield a main reflector.
2. The optical imaging satellite bottom shade deployment system of claim 1,
the bottom light shield extension mechanism (9) is arranged on the outer side of the main mirror base (14) and comprises a toothed ring annular guide rail (91), a guide rail slide block (92) arranged on the toothed ring annular guide rail (91), a motor-driven self-locking joint (93) and a bottom light shield extension arm (94) connected to the guide rail slide block.
3. The optical imaging satellite bottom shade deployment system of claim 2,
the bottom hood extension arm (94) is hollow, and an aluminized polyimide film is stacked in the hollow.
4. The optical imaging satellite bottom shade deployment system of claim 1,
the bottom light shield adopts an aluminized polyimide film or a flexible solar cell.
5. The optical imaging satellite bottom shade deployment system of claim 2,
the bottom hood (8) is received in a slot in the side of the bottom hood extension arm (94).
6. The optical imaging satellite bottom shade deployment system of claim 2,
a fixed light shield is arranged in the main mirror base (14).
7. The optical imaging satellite bottom shade deployment system of claim 2,
a plurality of fixed supports (104) pointing to the center are arranged in the main mirror base (14), and the fixed supports (104) are fixedly connected with a nozzle (101) of a propellant tank of the propulsion system.
8. The optical imaging satellite bottom shade deployment system of claim 2,
the self-locking joint drives the worm to rotate by using the servo motor, and the worm rotates and drives the worm wheel meshed with the worm to rotate.
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| CN113515002A (en) * | 2021-04-23 | 2021-10-19 | 上海卫星工程研究所 | External heat flow restrained satellite-borne shading system |
| CN117031862A (en) * | 2023-10-09 | 2023-11-10 | 天津航天机电设备研究所 | Assembling and adjusting system of connecting rod unfolding mechanism for folding and unfolding light shield and using method |
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