High-redundancy earth screen unfolding mechanism capable of being repeatedly unlocked

Abstract

The invention discloses a high-redundancy repeatable unlocking earth screen unfolding mechanism, which relates to the technical field of satellite load unfolding mechanisms and comprises an electromagnetic unlocking assembly, a hinge spring driving assembly, a ball pin assembly, an earth screen assembly and a mounting base. The hinge spring driving assembly provides unfolding driving force and in-place pre-tightening force for the earth screen mechanism. The electromagnetic unlocking assembly locks the ball pin assembly installed on the earth screen, and therefore locking of the earth screen is achieved. When the satellite is launched, the electromagnetic box is locked to fold the earth screen, and load envelope is reduced; the electromagnetic box is unlocked after on orbit, and the earth screen is unfolded and pre-tightened in place through the hinge spring driving assembly. The earth screen mechanism is simple in structure, an electromagnetic box unlocking scheme is adopted, the earth screen mechanism can be repeatedly locked and unlocked in a ground test, the unlocking assembly and the driving assembly are in redundant design, and the reliability of the unfolding mechanism is greatly improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of satellite payload deployment mechanisms, and in particular relates to a highly redundant and repeatedly unlockable earth screen deployment mechanism. Background Art

[0002] In satellite applications, a radiant cooler is mounted on the payload to provide cooling for the payload's detectors. The deployable earth screen of the radiant cooler must remain closed during launch to reduce the payload envelope, while reliably deploying once in orbit to ensure the proper function of the radiant cooler. The transmission deployment mechanism uses pyrotechnics or hot knives to lock the mechanism, requiring component replacement after ground testing. Unlocking and locking are not repeatable. Furthermore, most unlocking mechanisms utilize a single point. While some unlocking mechanisms incorporate partial structural redundancy, few offer full redundancy for the entire mechanism, resulting in relatively poor reliability.

[0003] Furthermore, due to the low rigidity of the deployment mechanism of aerospace products, most require a locking and unlocking device to lock the deployment mechanism during launch. This unlocking device lacks redundancy and operates at a single point during in-orbit release. If this unlocking device fails to release, the entire deployment mechanism cannot be deployed, posing a significant risk.

[0004] Although some unlocking mechanisms on aerospace products have redundant designs, such as common pyrotechnic cutters, which use two backup charges of pyrotechnic powder on a single pyrotechnic unlocker to ensure that only one charge can detonate to push the movable knife to cut the screw; or hot knife unlockers, which use two backup heating elements on a single unlocker to heat and melt the fiber rope, unlocking the discriminating nut and achieving the unlocking purpose, these unlocking devices only provide backup for a certain part of a single unlocker, such as a backup charge of pyrotechnic powder on a pyrotechnic unlocker or a backup heating element on a hot knife unlocker, without backup for other components on the unlocker. If a component without backup fails, it will not work properly and cannot unlock properly. Summary of the Invention

[0005] To address the aforementioned technical problems, including the complex structure, inability to repeatedly unlock, and relatively low unlocking reliability of conventional deployment mechanisms, the present invention provides a highly redundant, repeatedly unlockable globe screen deployment mechanism. This mechanism features a simple structure, high reliability, and the ability to provide a stable deployment driving force, meeting the requirements of radiant coolers for globe screen deployment mechanisms. The present invention utilizes two independent electromagnetic unlocking devices for full backup. As long as either unlocker is operational, the deployment mechanism can be deployed, resulting in higher reliability than methods that only back up a single component of the unlocking device.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A highly redundant and repeatably unlockable globe screen deployment mechanism comprises an electromagnetic unlocking assembly, a hinge spring drive assembly, a ball pin assembly, a globe screen assembly and a mounting base; the electromagnetic unlocking assembly locks the ball pin assembly by holding it with a movable pin, and when unlocking, the electromagnetic box is energized to drive the movable pin to release the ball pin; the hinge spring drive assembly provides the deployment driving force and the pre-tightening force in place; the electromagnetic unlocking assembly adopts a dual redundant design, and any one of the electromagnetic boxes can be actuated to unlock; the ball pin assembly has two-dimensional rotational freedom, which improves the unlocking reliability; the hinge spring drive assembly adopts a double hinge design to ensure that the globe screen assembly can be reliably deployed.

[0008] Furthermore, the electromagnetic unlocking assembly includes two opposing electromagnetic boxes, each of which is provided with a movable pin, and the movable pin is driven by electromagnetic induction to achieve the clamping or release of the ball pin.

[0009] Furthermore, the ball pin assembly includes a ball pin, a ball pin core shaft, a ball pin rod, a pin shaft and a ball pin seat. The ball head of the ball pin is held tightly by the movable pin of the electromagnetic box, and the tail is connected to the ball pin core shaft and the ball pin rod. The ball pin can rotate freely around the ball pin rod.

[0010] Furthermore, the globe screen assembly includes a globe screen main board, a globe screen left board and a globe screen right board, which can block the effects of the earth's reflection of the sun and the earth's own radiation on the internal refrigeration components of the radiation cooler when unfolded.

[0011] Furthermore, the hinge spring drive assembly has two hinge assemblies, which are respectively installed on the globe screen main board and the mounting base. The redundant design ensures that the globe screen can be successfully unfolded when any hinge assembly is working.

[0012] Furthermore, a buffer bracket is symmetrically mounted on the mounting base, and a buffer pad is mounted on the buffer bracket. The buffer pad is made of polytetrafluoroethylene material and is used to absorb and buffer the impact force of the unfolding globe screen.

[0013] Furthermore, a Hall effect detection device is installed on the mounting base to provide an in-position signal after the globe screen is deployed into position, which is convenient for ground interpretation.

[0014] Furthermore, after the electromagnetic box of the electromagnetic unlocking assembly is unlocked, the movable pin is reset by a return tool to achieve a ground repeated locking function.

[0015] Furthermore, the ball pin seat of the ball pin assembly is installed on the globe screen main board, the ball pin rod is connected to the ball pin seat through a pin shaft, and the ball pin rod is connected to the ball pin through a ball pin core shaft to realize the connection between the electromagnetic unlocking assembly and the globe screen assembly.

[0016] Furthermore, the design of the electromagnetic unlocking assembly and the ball pin assembly enables the ball pin to still achieve the unlocking action when only one electromagnetic box is actuated.

[0017] Beneficial effects:

[0018] This invention utilizes an electromagnetic unlocking device, enabling repeated locking and unlocking after ground testing without the need for component replacement. The use of dual-redundant electromagnetic unlocking components and a two-dimensional rotational freedom scheme for the ball pin enhances the reliability of the unlocking mechanism. The dual-hinge spring assembly design improves deployment reliability, resulting in a highly redundant deployment mechanism and significantly improving its reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 Schematic diagram of the closed state;

[0020] Figure 2 Schematic diagram of the expanded state;

[0021] Figure 3 This is a schematic diagram of the electromagnetic unlocking component;

[0022] Figure 4 Schematic diagram of the ball pin assembly;

[0023] Figure 5 This is a schematic diagram of the globe screen assembly;

[0024] Figure 6 Schematic diagram of the ball pin assembly;

[0025] Figure 7 This is a schematic diagram of the redundant coordination of the electromagnetic unlocking components;

[0026] Figure 8 This is a schematic diagram of the installation base;

[0027] Figure 9 Schematic diagram of the unlocking process of a single unlocker; among them, a is a schematic diagram of the movable pin movement; b is a force diagram of the ball head of the ball pin; c is a force decomposition diagram of the ball head of the ball pin; d is a schematic diagram of the ball pin rotation unlocking.

[0028] Among them, the figures are marked as: 1. electromagnetic unlocking assembly; 2. globe screen assembly; 3. ball pin assembly; 4. hinge assembly; 5. mounting base; 11. electromagnetic box; 12. movable pin; 31. ball pin; 32. ball pin core shaft; 33. ball pin rod; 34. pin shaft; 35. ball pin seat; 21. globe screen main board; 22. left side panel of globe screen; 23. right side panel of globe screen; 40. hinge assembly main body; 50. base body; 51. buffer bracket; 52. buffer pad; 53. Hall in position detection device. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solutions and advantages of the present invention more clear, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0030] like Figure 1-Figure 5 As shown, the highly redundant and repeatably unlockable globe screen deployment mechanism of the present invention includes an electromagnetic unlocking assembly 1 , a hinge spring drive assembly, a ball pin assembly 3 , a globe screen assembly 2 and a mounting base 5 .

[0031] The electromagnetic unlocking assembly 1 comprises two opposing electromagnetic boxes 11. The electromagnetic unlocking assembly 1, via movable pins 12 in the two electromagnetic boxes 11, clamps the ball pins in the ball pin assembly 3 mounted on the globe screen assembly 2, thereby locking the deployment mechanism. When the electromagnetic boxes 11 are energized, electromagnetic induction, through the amplification mechanism and spring action, drives the movable pins 12 in the electromagnetic boxes 11 into the interior of the electromagnetic boxes 11, releasing the ball pins and achieving the unlocking purpose.

[0032] After the electromagnetic box 11 is unlocked, the movable pin is reset by the return tool to realize the ground repeated locking function.

[0033] The electromagnetic boxes 11 of the electromagnetic unlocking assembly 1 cooperate with the ball pin assembly 3 which can rotate freely in a plane. If the movable pin of any one of the two electromagnetic boxes 11 can be actuated, on-track unlocking can be achieved.

[0034] like Figure 5 As shown, the globe screen assembly 2 includes a globe screen main board 21, a globe screen left side board 22 and a globe screen right side board 23. After unfolding, it can block the influence of the earth's reflection of the sun and the earth's own radiation on the internal cooling components of the radiation cooler.

[0035] like Figure 6 As shown, the ball and pin assembly 3 includes a ball pin 31, a ball pin core shaft 32, a ball pin rod 33, a pin shaft 34, and a ball and pin seat 35. The ball head of the ball pin 31 is held tightly by the electromagnetic housing, while the tail is connected to the ball pin core shaft 32 and the ball pin rod 33. The ball pin 31 can rotate freely about the ball pin rod 33. When the electromagnetic housing of the electromagnetic housing unlocking assembly 1 is only actuated, the ball pin 31 can slide toward the actuated electromagnetic housing, thereby unlocking the housing. This two-dimensional rotational freedom of the ball pin improves the reliability of the unlocking and deployment mechanism.

[0036] The ball pin seat 35 is mounted on the globe screen main board 21, and the ball pin rod 33 is connected to the ball pin seat 35 via the pin shaft 34. The ball pin rod 33 is connected to the ball pin 31 via the ball pin core shaft 32. One end of the ball pin assembly 3 is connected to the globe screen main board 21, and the other end is connected to the movable pin 12 of the electromagnetic box unlocking assembly 1, thereby connecting the electromagnetic unlocking assembly 1 to the globe screen assembly 2 to be deployed.

[0037] like Figure 8 As shown, the hinge assembly 4 has a hinge assembly body 40, one end of which is installed on the globe screen main board 21, and the other end is installed on the base body 50. The globe screen assembly 2 is unfolded by two hinge assemblies 4. The redundant design ensures that the globe screen can be successfully unfolded when only any one hinge assembly is working.

[0038] Two buffer brackets 51 are symmetrically mounted on the base body 50 , and buffer pads 52 are mounted on the buffer brackets.

[0039] Preferably, the cushioning pad 52 is made of polytetrafluoroethylene (PTFE). Taking advantage of its excellent cushioning properties, it effectively absorbs and cushions the impact of the globe screen when it is deployed, protecting the globe screen from damage. Once deployed, the globe screen comes into direct contact with the cushioning pad, and the angle of deployment can be adjusted by adjusting the height of the cushioning pad. A Hall effect position detection device 53 is mounted on the base 50 and provides a position signal when the globe screen is deployed, facilitating ground interpretation.

[0040] The present invention utilizes an electromagnetic unlocking assembly and a two-dimensionally rotating ball pin to achieve a redundant design for the electromagnetic unlocking assembly. Two spring assemblies are used to drive the earth screen assembly to deploy, achieving a redundant deployment drive. In space, the earth screen assembly is unaffected by gravity and only needs to overcome its own rotational friction to rotate, ensuring that the driving force of a single spring is significantly greater than the rotational friction. The two hinge assemblies act as backups. This invention achieves dual-backup unlocking and deployment drive systems for the entire deployment mechanism, ensuring high reliability for in-orbit deployment.

[0041] like Figure 7 , Figure 9 As shown in the figure, in order to solve the problem of having two unlocking mechanisms locking one rod and any unlocking mechanism working normally, a ball-holding unlocking solution is designed, as shown in the figure. Figure 9 As shown in a, when any electromagnetic box 11 is working, assuming that only the left electromagnetic box is working, the movable pin inside the electromagnetic box moves to the left. At this time, the ball pin is subjected to two forces: the support force F1 of the right movable pin on the ball pin, and the driving force F2 of the hinge spring to expand the ball pin (as shown in FIG. Figure 9 The force F1 of the right movable pin on the ball pin is decomposed, and the force F1 of the right movable pin on the ball pin will generate a lateral thrust F3 on the ball pin (as shown in b). Figure 9As shown in c), the ball pin can deflect around the ball pin core axis under the force of the lateral thrust F3, thereby realizing the unlocking function (as shown in Figure 9 If the ball pin is not used, the unlocking action cannot be achieved when only one electromagnetic box is working. F4 is the support force of the right movable pin on the ball pin and F1 is the vertical support force of the ball pin (as shown in Figure d). Figure 9 As shown in c), F4 is equal to the driving force generated by the hinge assembly.

Claims

1. A highly redundant and repeatable unlocking globe screen deployment mechanism, characterized in that: It includes an electromagnetic unlocking component, a hinge spring drive component, a ball pin component, a globe screen component and a mounting base; the electromagnetic unlocking component locks the ball pin component by holding it with a movable pin, and when unlocking, the electromagnetic box is energized to drive the movable pin to release the ball pin; the hinge spring drive component provides the deployment driving force and the pre-tightening force in place; the electromagnetic unlocking component adopts a dual redundant design, and any electromagnetic box can be operated to unlock; the ball pin component has two-dimensional rotational freedom, which improves the unlocking reliability; the hinge spring drive component adopts a double hinge design to ensure that the globe screen component can be reliably deployed.

2. The highly redundant and repeatedly unlockable globe screen deployment mechanism according to claim 1 is characterized in that: The electromagnetic unlocking assembly includes two opposing electromagnetic boxes, each of which is provided with a movable pin. The movable pin is driven by electromagnetic induction to achieve the clamping or release of the ball pin.

3. The highly redundant and repeatedly unlockable globe screen deployment mechanism according to claim 1, characterized in that: The ball pin assembly includes a ball pin, a ball pin core shaft, a ball pin rod, a pin shaft and a ball pin seat. The ball head of the ball pin is held tightly by the movable pin of the electromagnetic box, and the tail is connected to the ball pin core shaft and the ball pin rod. The ball pin can rotate freely around the ball pin rod.

4. The highly redundant and repeatedly unlockable globe screen deployment mechanism according to claim 1, characterized in that: The globe screen assembly includes a globe screen main board, a globe screen left board and a globe screen right board. When unfolded, it can block the influence of the earth's reflection of the sun and the earth's own radiation on the internal refrigeration components of the radiation cooler.

5. The highly redundant and repeatedly unlockable globe screen deployment mechanism according to claim 1, characterized in that: The hinge spring drive assembly has two hinge assemblies, which are respectively installed on the globe screen mainboard and the mounting base. The redundant design ensures that the globe screen can be successfully unfolded when any hinge assembly is working.

6. The highly redundant and repeatedly unlockable globe screen deployment mechanism according to claim 1, characterized in that: Buffer brackets are symmetrically mounted on the mounting base, and buffer pads are mounted on the buffer brackets. The buffer pads are made of polytetrafluoroethylene material and are used to absorb and buffer the impact force of the unfolding globe screen.

7. The highly redundant and repeatedly unlockable globe screen deployment mechanism according to claim 1, characterized in that: The mounting base is also provided with a Hall effect detection device for providing an in-position signal after the globe screen is deployed into position, so as to facilitate ground interpretation.

8. The highly redundant and repeatedly unlockable globe screen deployment mechanism according to claim 1, characterized in that: After the electromagnetic box of the electromagnetic unlocking assembly is unlocked, the movable pin is reset by a return tool to achieve a ground repeated locking function.

9. The highly redundant and repeatedly unlockable globe screen deployment mechanism according to claim 1, characterized in that: The ball pin seat of the ball pin assembly is installed on the globe screen mainboard, the ball pin rod is connected to the ball pin seat through a pin shaft, and the ball pin rod is connected to the ball pin through a ball pin core shaft to realize the connection between the electromagnetic unlocking assembly and the globe screen assembly.

10. The highly redundant and repeatedly unlockable globe screen deployment mechanism according to claim 1, characterized in that: The design of the electromagnetic unlocking assembly and the ball pin assembly ensures that the ball pin can still achieve the unlocking action when only one electromagnetic box is actuated.

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