Step-by-step expansion type space camera primary mirror expansion supporting mechanism

Abstract

The invention provides a step-by-step expansion type space camera primary mirror expansion supporting mechanism, and belongs to the field of deep space exploration. The problems that a space camera primary mirror supporting structure is complex and poor in stability are solved. A plurality of unfolding arm pipe units are arranged on the end face of one side of the mounting base; the primary mirror support and the mounting base are coaxially arranged at intervals and are connected with the ends, away from the mounting base, of all the unfolding arm pipe units; each unfolding arm tube unit comprises a plurality of carbon fiber thin-walled tubes which are connected in sequence and are folded in a zigzag manner in sequence during folding, and the folded unfolding arm tube units form a first side and a second side; the driving mechanism comprises a first driving unit and a second driving unit which are completely identical in structure, and when the unfolding arm pipe unit is in a folded state, the first driving unit and the second driving unit are connected with the multiple synchronous hinges in the first side and the second side correspondingly to be used for controlling the first side and the second side to be alternately and sequentially unfolded step by step. The support is mainly used for supporting the space camera.

Description

Technical Field

[0001] The present invention belongs to the field of deep space exploration, and particularly relates to a step-by-step deployable main mirror deployment and support mechanism for a space camera. Background Art

[0002] The space camera is installed on the surface of the satellite. Before the satellite enters the orbit, it is necessary to fold the main mirror support so that the main mirror is pressed at a lower height. After the satellite enters the orbit, the support unfolds and pushes the camera main mirror to a certain height. Whether the space deployable arm can be deployed in a timely and high-precision manner directly affects the success or failure of the entire satellite launch mission. Deployable arms can be classified into thin-walled tube type, telescopic sleeve type, and articulated rod type according to their structural forms. They all have the characteristics of large folding ratio and are easy to store and transport for space missions. However, the thin-walled tube type deployable arm has relatively low deployment stiffness and poor load-bearing capacity. The telescopic sleeve type has a complex structure and poor locking stiffness, and a high retracted height. For the articulated deployable arm, the hinge clearance between the arm rod units will affect the stability, anti-disturbance ability, and deployment stiffness of the supported components, and a reliable locking method is required to provide higher stiffness for detection loads such as the back-mounted deployable antenna carried. To improve the stiffness of the articulated deployable arm, taking the American ADAM mechanism as an example, the deployment unit is often supported by parallel vertical rods and tension cables are arranged. However, the cables are prone to entanglement in the retracted state, and the cables in the deployed state will affect the optical path of the space telescope. The present invention proposes a deployment configuration with inclined symmetrically arranged rods, which improves the deployment stiffness and avoids the generation of stray light.

[0003] The installation space of the satellite is limited, and the layout of various payloads on the satellite is relatively compact. The deployable arm is restricted by more space dimensions during the retracted state and the deployment process. Therefore, it is necessary to reasonably design the deployment trajectory envelope and retraction envelope of the deployable arm to avoid mechanical interference during deployment and cause mission failure.

[0004] These solutions have relatively complex structures, low deployment stiffness, and a large space occupied after retraction. Therefore, there is an urgent need for a main mirror deployment mechanism for a space camera to solve the above problems. Summary of the Invention

[0005] In view of this, the present invention aims to propose a step-by-step deployable main mirror deployment and support mechanism for a space camera to solve the problems of complex structure and poor stability of the main mirror support structure of the space camera.

[0006] To achieve the above object, the present invention adopts the following technical solutions: A step-by-step deployable main mirror deployment and support mechanism for a space camera, comprising:

[0007] An installation base, on one side end face of which a plurality of deployable arm tube units are provided;

[0008] A main mirror support, arranged coaxially and at an interval with the installation base and connected to the ends of all the deployable arm tube units far from the installation base;

[0009] The primary mirror, connected to one end of the primary mirror support away from the mounting base;

[0010] The drive mechanism, connected to any one of the deployable arm tube units;

[0011] The deployable arm tube unit includes a plurality of carbon fiber thin-walled tubes connected in sequence and folds in a zigzag manner in sequence when folded. The folded deployable arm tube unit forms a first side and a second side. Each adjacent two carbon fiber thin-walled tubes are connected by a synchronous hinge. The carbon fiber thin-walled tube on the side close to the mounting base and the carbon fiber thin-walled tube on the side close to the primary mirror support are both connected to the mounting base or the primary mirror support by a synchronous hinge;

[0012] The drive mechanism includes a first drive unit and a second drive unit with exactly the same structure. When the deployable arm tube unit is in the folded state, the first drive unit and the second drive unit are respectively connected to a plurality of synchronous hinges in the first side and the second side for controlling the step-by-step and alternating sequential deployment of the first side and the second side.

[0013] Furthermore, there are six deployable arm tube units, and the connection points of the six deployable arm tube units with the mounting base are in a regular hexagon. The axis of the deployable arm tube unit in the deployed state forms an angle of 80° with the mounting base. Each adjacent two deployable arm tube units are in a V shape and are symmetric with respect to the diagonal of the corresponding position of the regular hexagon.

[0014] Furthermore, each deployable arm tube unit includes four first carbon fiber thin-walled tubes with equal lengths and connected in sequence and a second carbon fiber thin-walled tube connected to the last first carbon fiber thin-walled tube and slightly shorter than the first carbon fiber thin-walled tube. The second carbon fiber thin-walled tube is connected to the primary mirror support.

[0015] Furthermore, the synchronous hinge includes a male hinge, a female hinge, an elastic locking pin, a box body, a male hinge rotating shaft and a female hinge rotating shaft. The male hinge is rotatably connected to the box body through the male hinge rotating shaft. The female hinge is rotatably connected to the box body through the female hinge rotating shaft. The axes of the male hinge and the female hinge are parallel and are engaged through a gear ring. Elastic locking pins are arranged on both the male hinge and the female hinge. A mating hole is arranged on the box body. When the deployable arm tube unit is in the deployed state, each elastic locking pin is engaged with the mating hole at the corresponding position.

[0016] Furthermore, the elastic locking pin is conical, and the mating hole is a conical hole.

[0017] Furthermore, the male hinge and the female hinge are in a 1:1 transmission.

[0018] Further, both the first driving unit and the second driving unit include a motor and a sliding gearbox. The motor is connected to the mounting base, and the motor is connected to the sliding gearbox. The sliding gearbox is used to control the movement of the first side or the second side.

[0019] Further, the sliding gearbox includes a cam, a fork, a spline shaft, a spur gear, and a jaw clutch. There are multiple jaw clutches, which are arranged in one-to-one correspondence with the inner synchronous hinges on the first side or the second side. Each jaw clutch is connected to the sliding gearbox through a spline shaft. The cam is connected to the motor, and a driving gear is arranged on the cam. A driven spline shaft is arranged on the sliding gearbox, and the driven gear arranged on the driven spline shaft is connected to the driving gear. Multiple grooves are arranged on the cam. There are multiple forks, and one end of each fork is inserted into the groove at the corresponding position, and the other end is connected to the spline shaft and the driven spline shaft at the corresponding position. A spur gear is arranged on each spline shaft and driven spline shaft. When the cam rotates, it pushes all the forks through all the grooves to drive all the spur gears to move axially and drive all the jaw clutches to move.

[0020] Further, two jaw clutches are arranged in each sliding gearbox.

[0021] Further, each jaw clutch is used to drive the synchronous hinge at the corresponding position to move.

[0022] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0023] 1. The deployment arm tube unit of this mechanism is composed of a thin-walled tube and a synchronous hinge, with a simple structure. When fully and safely deployed, it is locked by a synchronous locking pin, which is safe and reliable, improves the stiffness, and when in the retracted state, it is fully retracted, with a low retracted height and small occupied space, capable of saving the effective payload space on the carrier.

[0024] 2. The structural and driving methods of this mechanism can achieve single-step and single-degree-of-freedom deployment, resulting in good controllability and strong stability during the movement process.

[0025] 3. The support method and spatial layout form of the deployment arm tube unit adopted by this mechanism improve the stiffness and stability of the deployment state of the deployment mechanism.

[0026] 4. The elastic locking pin adopted by this mechanism is conical, and the mating hole matched with it is also a conical hole, which can form a one-way limiting effect and can smoothly reset the elastic locking pin during folding, with strong operation convenience.

[0027] 5. By setting up two driving mechanisms, the driving mechanism of this mechanism drives the first side and the second side respectively, and performs alternate driving for single-degree-of-freedom sequential unfolding, which can achieve precise control of the unfolding action and has good controllability. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The drawings forming a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0029] Figure 1 is a schematic structural diagram of the folding state of a step-by-step unfolding space camera primary mirror unfolding support mechanism according to the present invention;

[0030] Figure 2 is a schematic structural diagram of the unfolding state of a step-by-step unfolding space camera primary mirror unfolding support mechanism according to the present invention;

[0031] Figure 3 is a schematic structural diagram of the synchronous hinge according to the present invention;

[0032] Figure 4 is a schematic structural diagram of the driving mechanism according to the present invention.

[0033] Primary mirror 1; primary mirror support 2; mounting base 3; unfolding mechanism 4; unfolding arm tube unit 4-1; thin-walled tube 4-1-1; first thin-walled tube 4-1-1-1; second thin-walled tube 4-1-1-2; synchronous hinge 4-1-2; male hinge 4-1-2-1; female hinge 4-1-2-2; elastic locking pin 4-1-2-3; box body 4-1-2-4; male hinge rotating shaft 4-1-2-5; female hinge rotating shaft 4-1-2-6; driving mechanism 5; motor 5-1; sliding gear box 5-2; cam 5-2-1; first groove 5-2-1-1; second groove 5-2-1-2; fork 5-2-2; first fork 5-2-2-1; second fork 5-2-2-2; spline shaft 5-2-3; spur gear 5-2-4; jaw clutch 5-2-5; first clutch 5-2-5-1; second clutch 5-2-5-2. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0034] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. It should be noted that, without conflict, the embodiments in the present invention and the features in the embodiments can be combined with each other. The described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0035] It should be noted that the descriptions of directions such as "left", "right", "left side", "right side", "upper part", "lower part", "top", and "bottom" in the present invention are all defined based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the described structure must be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present invention. In the description of the present invention, "a plurality of" means more than two, unless otherwise specifically defined.

[0036] In the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", and "coupled" shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0037] Referring to the accompanying drawings to illustrate this embodiment, a main mirror deployment support mechanism for a step-by-step deployment space camera includes:

[0038] An installation base 3, on one side end face, a plurality of deployment arm tube units 4-1 are provided;

[0039] A main mirror support 2, which is arranged coaxially and at intervals with the installation base 3 and is connected to one end of all the deployment arm tube units 4-1 away from the installation base 3;

[0040] A main mirror 1, which is connected to one end of the main mirror support 2 away from the installation base 3;

[0041] A drive mechanism 5, which is connected to any one of the deployment arm tube units 4-1;

[0042] The deployment arm tube unit 4-1 includes a plurality of thin-walled tubes 4-1-1 connected in sequence and folds in a zigzag manner in sequence when folded. Through this folding form, it can ensure that the overall height after folding is low enough, so that a small space can be occupied during transportation. Combined with the characteristic of light weight of its own material, it can reduce the carrying and transportation cost. The folded deployment arm tube unit 4-1 forms a first side and a second side. Each adjacent two thin-walled tubes 4-1-1 are connected by a synchronous hinge 4-1-2. The thin-walled tube 4-1-1 on the side close to the installation base 3 and the thin-walled tube 4-1-1 on the side close to the main mirror support 2 are both connected to the installation base 3 or the main mirror support 2 through a synchronous hinge 4-1-2; the thin-walled tube 4-1-1 is made of carbon fiber material, which has the characteristics of light weight and strong structural strength, and can further reduce the mass of the overall structure while ensuring sufficient deployment stiffness.

[0043] The driving mechanism 5 includes a first driving unit and a second driving unit with exactly the same structure. When the deployment arm tube unit 4-1 is in the folded state, the first driving unit and the second driving unit are respectively connected to a plurality of synchronous hinges 4-1-2 inside the first side and the second side to control the sequential and alternating deployment of the first side and the second side step by step. The first driving unit and the second driving unit operate alternately, so that each time a synchronous hinge 4-1-2 is deployed, and the degree of freedom of each deployment is 1, achieving the technical effect of completely controllable opening.

[0044] In this embodiment, six deployment arm tube units 4-1 are provided. The connection points of the six deployment arm tube units 4-1 with the mounting base 3 form a regular hexagon. The angle between the axis of the deployment arm tube unit 4-1 in the deployed state and the mounting base 3 is 80°. Each adjacent two deployment arm tube units 4-1 form a V shape and are symmetric with respect to the diagonal of the corresponding position of the regular hexagon. Through this arrangement method, a plurality of V-shaped supports can be formed, and cooperate with the mounting base 3 and the main mirror support 2 to form a plurality of triangular stable support structures. Combining with the fact that the connection points of the six deployment arm tube units 4-1 with the mounting base 3 form a regular hexagon, and the angle between the axis of the deployment arm tube unit 4-1 in the deployed state and the mounting base 3 is 80°, the stability of the support can be further improved, so that each unit and the whole are in a stable support form. Combining with the material of the carbon fiber tube, a better support effect can be formed.

[0045] In this embodiment, each deployment arm tube unit 4-1 includes four first thin-wall tubes 4-1-1-1 with equal lengths and sequentially connected, and a second thin-wall tube 4-1-1-2 connected to the last first thin-wall tube 4-1-1-1 and slightly shorter than the first thin-wall tube 4-1-1-1. The second thin-wall tube 4-1-1-2 is connected to the main mirror support 2. In this way, it can be ensured that the main mirror support 2 can be deployed smoothly.

[0046] In this embodiment, the synchronous hinge 4-1-2 includes a male hinge 4-1-2-1, a female hinge 4-1-2-2, an elastic locking pin 4-1-2-3, a box body 4-1-2-4, a male hinge rotating shaft 4-1-2-5 and a female hinge rotating shaft 4-1-2-6. The male hinge 4-1-2-1 is rotatably connected to the box body 4-1-2-4 through the male hinge rotating shaft 4-1-2-5. The female hinge 4-1-2-2 is rotatably connected to the box body 4-1-2-4 through the female hinge rotating shaft 4-1-2-6. The axes of the male hinge 4-1-2-1 and the female hinge 4-1-2-2 are parallel and meshed through a gear ring. Elastic locking pins 4-1-2-3 are arranged on both the male hinge 4-1-2-1 and the female hinge 4-1-2-2. A mating hole is arranged on the box body 4-1-2-4. When the deployment arm tube unit 4-1 is in the deployed state, each elastic locking pin 4-1-2-3 is engaged with the mating hole at the corresponding position.

[0047] In this embodiment, the elastic locking pin 4-1-2-3 is conical, and the mating hole is a conical hole. During the relative rotation of the male hinge 4-1-2-1 and the female hinge 4-1-2-2, when the elastic locking pin 4-1-2-3 moves into the corresponding mating hole, it can be engaged. At this time, the adjacent two first thin-walled tubes 4-1-1-1 are just in a straight state, and after the engagement, it has good unfolding stiffness. When folding in the reverse direction, due to the conical setting, the reverse movement is just a way of mating two conical surfaces, so that the reverse process can proceed smoothly, ensuring the smoothness of the folding process.

[0048] In this embodiment, the male hinge 4-1-2-1 and the female hinge 4-1-2-2 have a 1:1 transmission.

[0049] In this embodiment, both the first driving unit and the second driving unit include a motor 5-1 and a sliding gearbox 5-2. The motor 5-1 is connected to the mounting base 3, the motor 5-1 is connected to the sliding gearbox 5-2, and the sliding gearbox 5-2 is used to control the movement of the first side or the second side.

[0050] In this embodiment, the sliding gearbox 5-2 includes a cam 5-2-1, a fork 5-2-2, a spline shaft 5-2-3, a spur gear 5-2-4, and a jaw clutch 5-2-5. A plurality of jaw clutches 5-2-5 are provided and arranged in one-to-one correspondence with the inner synchronous hinges 4-1-2 on the first side or the second side. Each jaw clutch 5-2-5 is connected to the sliding gearbox 5-2 through a spline shaft 5-2-3. The cam 5-2-1 is connected to the motor 5-1. A driving gear is provided on the cam 5-2-1. A driven spline shaft is provided on the sliding gearbox 5-2. The driven gear provided on the driven spline shaft is connected to the driving gear. A plurality of grooves are provided on the cam 5-2-1. A plurality of forks 5-2-2 are provided and one end of each fork 5-2-2 is inserted into the groove at the corresponding position, and the other end is connected to the spline shaft 5-2-3 and the driven spline shaft at the corresponding position. A spur gear is provided on each spline shaft 5-2-3 and the driven spline shaft. The cam 5-2-1 is used to drive all the forks 5-2-2 through all the grooves during rotation to drive all the spur gears to move axially and drive all the jaw clutches 5-2-5 to move. By rotating the cam 5-2-1, the corresponding fork can be toggled through the groove provided thereon, so that the spline shaft 5-2-3 and the driven spline shaft can be driven to slide correspondingly, and thus the corresponding jaw clutch 5-2-5 can be driven to act, achieving a way of step-by-step switching to drive the synchronous hinge. At the same time, in cooperation with the gear transmission relationship provided on the spline shaft 5-2-3 and the driven spline shaft, when the cam 5-2-1 rotates, the rotation can be transmitted from the driving gear to the driven gear, and then the driven gear is transmitted to other spline shafts 5-2-3 through the spur gear on the driven spline shaft, and drives the corresponding jaw clutches 5-2-5 to rotate, so as to drive the synchronous hinges at different positions. A joint cooperating with the jaw clutch 5-2-5 is provided on the synchronous hinge 4-1-2.

[0051] In this embodiment, two jaw clutches 5-2-5 are provided in each sliding gearbox 5-2 and are respectively used in cooperation with two synchronous hinges 4-1-2 on the same side, so as to complete the form of step-by-step sequential deployment.

[0052] In this embodiment, each jaw clutch 5-2-5 is used to drive the synchronous hinge 4-1-2 at the corresponding position to act.

[0053] The main mirror deployment support mechanism of the step-by-step deployment space camera of the present invention is initially in a retracted state, as Figure 1As shown, that is, each set of deployment arm units 4-1 is in a flattened state. When the jaw clutch 5-2-5 of the drive mechanism 5 is connected to the drive hinge, the position of the jaw clutch 5-2-5 is 0. In the initial state, the position of the first clutch 5-2-5-1 in the first drive unit is 0, the position of the first clutch 5-2-5-1 in the second drive unit is -20 mm, the position of the second clutch 5-2-5-2 in the first drive unit is -40 mm, and the position of the second clutch 5-2-5-2 in the second drive unit is -40 mm.

[0054] Step 1: The drive motor 5-1 rotates from 0° to 150°. The four sets of sliding forks 5-2-2 move along the grooves of the cylindrical cam 5-2-1. The first clutch 5-2-5-1 in the first drive unit drives the corresponding synchronous hinge to rotate 83.2°, causing the shorter second thin-walled tube 4-1-1-2 to rotate relative to the adjacent long carbon fiber thin-walled tube 4-1-1-1 and unfold into a straight line. The synchronous hinge 4-1-2 connecting the two is locked. Then, the first clutch 5-2-5-1 in the first drive unit rotates by 30° and reaches the -20 mm position. The position of the first clutch 5-2-5-1 in the second drive unit remains unchanged at -20 mm and rotates 150°. The position of the second clutch 5-2-5-2 in the first drive unit remains unchanged and rotates 120°, and rotates 30° to reach the -20 mm position. The position of the second clutch 5-2-5-2 in the second drive unit remains unchanged at -40 mm and rotates 150°.

[0055] Step 2: The drive motor 5-1 rotates from 150° to 270°. The first clutch 5-2-5-1 in the first drive unit maintains the -20 mm position. The first clutch 5-2-5-1 in the second drive unit rotates 30° and reaches the 0 mm position, driving the drive hinge to rotate 71.49°, causing the long carbon fiber thin-walled tube 4-1-1-1 locked at one end in the first step to unfold into a straight line with the long carbon fiber thin-walled tube 4-1-1-1 hinged at the other end. The synchronous hinge 4-1-2 connecting the two is locked. Then, the first clutch 5-2-5-1 in the second drive unit rotates 30° and returns to and maintains the -20 mm position. The second clutch 5-2-5-2 in the first drive unit maintains the -20 mm position. The second clutch 5-2-5-2 in the second drive unit maintains the -40 mm position.

[0056] Step 3: The drive motor 5-1 rotates from 270° to 450°. The first clutch 5-2-5-1 in the first drive unit remains at the -20 mm position; the first clutch 5-2-5-1 in the second drive unit remains at the -20 mm position; the third clutch 5-2-5-3 rotates 30°, reaching the 0 mm position, driving the drive hinge to rotate 86.74°, causing the long carbon fiber thin-walled tube 4-1-1-1 locked at one end and the long carbon fiber thin-walled tube 4-1-1-1 hinged at the other end in Step 2 to unfold into a straight line, and the synchronous hinge 4-1-2 connecting the two is locked. Then, the second clutch 5-2-5-2 in the first drive unit rotates 30°, returning to and remaining at the -20 mm position; the second clutch 5-2-5-2 in the second drive unit rotates 30°, reaching the -20 mm position and remaining there.

[0057] Step 4: The drive motor 5-1 rotates from 450° to 600°. The first clutch 5-2-5-1 in the first drive unit remains at the -20 mm position; the first clutch 5-2-5-1 in the second drive unit remains at the -20 mm position; the second clutch 5-2-5-2 in the first drive unit remains at the -20 mm position; the second clutch 5-2-5-2 in the second drive unit rotates 30°, reaching the 0 mm position, driving the drive hinge to rotate 79.97°, causing the long carbon fiber thin-walled tube 4-1-1-1 locked at one end and the long carbon fiber thin-walled tube 4-1-1-1 hinged at the other end in Step 3 to unfold into a straight line, and the synchronous hinge 4-1-2 connecting the two is locked. Then, the fourth clutch 5-2-5-2 rotates 30°, returning to and remaining at the -20 mm position and remaining there. The deployment mechanism is fully deployed.

[0058] The embodiments of the present invention disclosed above are only used to help illustrate the present invention. The embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. According to the content of this specification, many modifications and variations can be made. These embodiments are selected and specifically described in this specification to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and utilize the present invention well.

Claims

1. A step-by-step deployment support mechanism for the primary mirror of a space camera, characterized in that, Comprising: An installation base (3) with a plurality of deployment arm tube units (4-1) arranged on one side end face; A main mirror support (2) coaxially spaced from the installation base (3) and connected to one end of all the deployment arm tube units (4-1) away from the installation base (3); A main mirror (1) connected to one end of the main mirror support (2) away from the installation base (3); A driving mechanism (5) connected to any one of the deployment arm tube units (4-1); The deployment arm tube unit (4-1) comprises a plurality of thin-walled tubes (4-1-1) connected in sequence and folded in a zigzag manner in sequence when folded. The folded deployment arm tube unit (4-1) forms a first side and a second side. Each adjacent two thin-walled tubes (4-1-1) are connected by a synchronous hinge (4-1-2). The thin-walled tube (4-1-1) on the side close to the installation base (3) and the thin-walled tube (4-1-1) on the side close to the main mirror support (2) are both connected to the installation base (3) or the main mirror support (2) by a synchronous hinge (4-1-2); The driving mechanism (5) comprises a first driving unit and a second driving unit with exactly the same structure. When the deployment arm tube unit (4-1) is in a folded state, the first driving unit and the second driving unit are respectively connected to a plurality of synchronous hinges (4-1-2) inside the first side and the second side for controlling the step-by-step and alternating sequential deployment of the first side and the second side.

2. The step-by-step deployment support mechanism for the primary mirror of a space camera according to claim 1, characterized in that: Six deployment arm tube units (4-1) are provided. The connection points of the six deployment arm tube units (4-1) with the installation base (3) are in a regular hexagon. The axis of the deployment arm tube unit (4-1) in the deployed state forms an angle of 80° with the installation base (3). Each adjacent two deployment arm tube units (4-1) are in a V shape and symmetric with respect to the diagonal of the corresponding position of the regular hexagon.

3. The step-by-step deployment support mechanism for the primary mirror of a space camera according to claim 2, characterized in that: Each deployment arm tube unit (4-1) comprises four first thin-walled tubes (4-1-1-1) with equal lengths and connected in sequence and a second thin-walled tube (4-1-1-2) connected to the end first thin-walled tube (4-1-1-1) and slightly shorter than the first thin-walled tube (4-1-1-1). The second thin-walled tube (4-1-1-2) is connected to the main mirror support (2).

4. The step-by-step deployment support mechanism for the primary mirror of a space camera according to claim 1, characterized in that: The synchronous hinge (4-1-2) includes a male hinge (4-1-2-1), a female hinge (4-1-2-2), an elastic locking pin (4-1-2-3), a box body (4-1-2-4), a male hinge rotating shaft (4-1-2-5) and a female hinge rotating shaft (4-1-2-6). The male hinge (4-1-2-1) is rotatably connected to the box body (4-1-2-4) through the male hinge rotating shaft (4-1-2-5), and the female hinge (4-1-2-2) is rotatably connected to the box body (4-1-2-4) through the female hinge rotating shaft (4-1-2-6). The axes of the male hinge (4-1-2-1) and the female hinge (4-1-2-2) are parallel and meshed through a gear ring. Elastic locking pins (4-1-2-3) are arranged on both the male hinge (4-1-2-1) and the female hinge (4-1-2-2). A mating hole is arranged on the box body (4-1-2-4). When the deployment arm tube unit (4-1) is in the deployed state, each elastic locking pin (4-1-2-3) is engaged with the mating hole at the corresponding position.

5. The step-by-step deployment support mechanism for the primary mirror of a space camera according to claim 4, characterized in that: The elastic locking pin (4-1-2-3) is conical, and the mating hole is a tapered hole.

6. The step-by-step deployment support mechanism for the primary mirror of a space camera according to claim 4, characterized in that: The male hinge (4-1-2-1) and the female hinge (4-1-2-2) have a 1:1 transmission.

7. The step-by-step deployment support mechanism for the primary mirror of a space camera according to any one of claims 1-6, characterized in that: Both the first drive unit and the second drive unit include a motor (5-1) and a sliding gearbox (5-2). The motor (5-1) is connected to the mounting base (3), the motor (5-1) is connected to the sliding gearbox (5-2), and the sliding gearbox (5-2) is used to control the action of the first side or the second side.

8. The step-by-step deployment support mechanism for the primary mirror of a space camera according to claim 7, characterized in that: The sliding gearbox (5-2) includes a cam (5-2-1), a fork (5-2-2), a spline shaft (5-2-3), a spur gear (5-2-4) and a jaw clutch (5-2-5). A plurality of jaw clutches (5-2-5) are provided and arranged in one-to-one correspondence with the internal synchronous hinges (4-1-2) on the first side or the second side. Each jaw clutch (5-2-5) is connected to the sliding gearbox (5-2) through a spline shaft (5-2-3). The cam (5-2-1) is connected to the motor (5-1). A driving gear is arranged on the cam (5-2-1). A driven spline shaft is arranged on the sliding gearbox (5-2), and the driven gear arranged on the driven spline shaft is connected to the driving gear. A plurality of grooves are arranged on the cam (5-2-1). A plurality of forks (5-2-2) are provided, and one end of each fork (5-2-2) is inserted into the groove at the corresponding position, and the other end is connected to the spline shaft (5-2-3) and the driven spline shaft at the corresponding position. A spur gear is arranged on each spline shaft (5-2-3) and the driven spline shaft. The cam (5-2-1) is used to drive all the spur gears to move axially and drive all the jaw clutches (5-2-5) to act by pushing all the forks (5-2-2) through all the grooves when rotating.

9. The step-by-step deployment support mechanism for the primary mirror of a space camera according to claim 7, characterized in that: Two jaw clutches (5-2-5) are arranged in each sliding gearbox (5-2).

10. The step-by-step deployment support mechanism for the primary mirror of a space camera according to claim 7, characterized in that: Each of the jaw clutches (5-2-5) is used to drive the synchronous hinge (4-1-2) at the corresponding position to act.

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