Non-explosive low-impact electromagnetic locking and releasing device

Abstract

The present invention discloses a non-pyrotechnic low-impact electromagnetic locking and releasing device, comprising a target seat end assembly and a locking pin; the target seat end assembly comprises a target seat cylinder, a hole elastic retaining ring, a DC traction electromagnet, a retainer, a steel ball, and a reset spring; the target seat cylinder comprises a large-diameter inner cavity and a small-diameter inner cavity structure; the steel ball is installed in a spherical groove of the retainer, and the retainer and the steel ball are installed together in the small-diameter inner cavity of the target seat cylinder, one end of the reset spring contacts the inner end face of the retainer, and the other end contacts the end face of the DC traction electromagnet, and the DC traction electromagnet is installed in the large-diameter inner cavity of the target seat cylinder. The device adopts a non-pyrotechnic electromagnetic drive principle, has the characteristics of low unlocking impact, safety and energy saving, simple structure, reliable connection, and reusability, and adopts an electromagnetic drive form that can greatly reduce the unlocking impact load, increase the service life of the locking and releasing device, and reduce the risk of failure of high-precision detection equipment.

Description

Technical Field

[0001] The invention belongs to the field of aerospace, and in particular relates to a non-explosive low-impact electromagnetic locking and releasing device. Background Art

[0002] Connecting multiple satellites, probes and spacecraft (spacecraft, space station, spacecraft, etc.) with ropes will be more conducive to the exploration equipment to go deeper into space, realize instant and effective exploration in a larger range, greatly increase the amount of information collected, and also be more conducive to the launch and recovery of satellites and probes, reduce the burden of precise and complex attitude and orbit control systems, avoid collisions with spacecraft, reduce space debris, and effectively reduce the economic cost of recovery. With the research progress of "multiple satellites with one rocket", "space docking system", and tethered satellite system (TSS) related technologies, the technical requirements for low unlocking impact, high connection, release reliability, lightweight structure, and reusability of connection and separation devices are becoming higher and higher. Most of the existing connection and separation devices rely on pyrotechnic drive technology to achieve unlocking and separation. The pyrotechnic drive unlocking technology has the disadvantages of large unlocking impact load, poor safety, heavy device structure, and non-reusability, which increases the burden on the attitude and orbit control system of satellites and probes, and the gunpowder is prone to produce excess gas or debris after detonation, which is easy to cause the failure of high-precision instrument devices. Summary of the invention

[0003] The technical problem to be solved by the present invention is to provide a locking and releasing device used in a tethered satellite system and a space docking system. The device adopts a non-pyrotechnic electromagnetic drive principle and has the characteristics of low unlocking impact, safety and energy saving, simple structure, reliable connection and reusability. The use of electromagnetic drive can greatly reduce the unlocking impact load, increase the service life of the locking and releasing device, and reduce the risk of failure of high-precision detection equipment.

[0004] The technical solution adopted by the present invention is a non-pyrotechnic low-impact electromagnetic locking and releasing device, including a target seat end assembly and a locking pin; the target seat end assembly is fixedly mounted at one end of a separation system substrate; the locking pin is mounted on a substrate of another separation system; the target seat end assembly includes a target seat cylinder, a hole elastic retaining ring, a DC traction electromagnet, a retaining frame, a steel ball, and a reset spring; the target seat cylinder includes a large-diameter inner cavity and a small-diameter inner cavity structure; the steel ball is mounted in a spherical groove of the retaining frame, and the retaining frame and the steel ball are mounted together in the small-diameter inner cavity of the target seat cylinder, one end of the reset spring contacts the inner end face of the retaining frame, and the other end contacts the end face of the DC traction electromagnet, the DC traction electromagnet is mounted in the large-diameter inner cavity of the target seat cylinder, one axial end is in compression contact with the reset spring, and the other end is limitedly mounted with the target seat cylinder through the hole elastic retaining ring, and the lead of the DC traction electromagnet passes through the threading hole opened in the target seat cylinder.

[0005] Furthermore, the locking pin comprises a pin rod and a tapered structure, and the pin rod is provided with an annular locking groove for locking the steel ball.

[0006] Furthermore, the threading hole provided on the target base cylinder is arranged on the large diameter inner cavity.

[0007] Furthermore, the target seat cylinder and the locking pin are matched with each other using conical surfaces.

[0008] Furthermore, the steel ball is installed in the ball groove from outside to inside in the radial direction of the retaining frame.

[0009] Furthermore, a traction stroke is reserved between the armature end face of the DC traction electromagnet and the outer end face of the inner tube of the retaining frame.

[0010] Furthermore, the return spring always maintains an elastically compressed state.

[0011] Furthermore, it can be applied to a multi-unit separation system.

[0012] Furthermore, the DC traction electromagnet, retaining frame and locking pin are all provided with an inner hole structure for inserting a space traction rope to form a tethered satellite system.

[0013] The beneficial effects of the present invention are: 1. The non-pyrotechnic electromagnetic drive form adopted by the present invention can significantly reduce the impact load of unlocking the separation system, and has the advantages of being reusable, energy-saving and environmentally friendly.

[0014] 2. The ball lock structure adopted in the present invention has the characteristics of large load-bearing capacity, reliable locking, and smooth locking and unlocking movements.

[0015] 3. The target seat cylinder and locking pin of the present invention adopt conical surface matching, which helps to play a guiding role in the docking movement and reduce the axial impact load during the docking process.

[0016] 4. The return spring used in the present invention is always in a compressed energy storage state after installation, always provides a preload, and ensures the reliability of the locking connection.

[0017] 5. In the present invention, a suitable traction stroke is left between the DC traction electromagnet and the retaining frame, which helps to reduce the impact load during unlocking and releasing, and improves the unlocking time.

[0018] 6. The present invention adopts an installation method in which a hole elastic retaining ring is used to limit the DC traction electromagnet in the large-diameter inner cavity of the target base cylinder, which has the characteristics of simple operation, easy replacement and quick installation.

[0019] 7. The interface adopted by the present invention is simple and diverse, and can be universalized.

[0020] 8. The product of the present invention has a serialized bearing capacity, a simple structure, and various specifications, and can be standardized and serialized. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 A schematic diagram of a non-pyrotechnic electromagnetic locking and releasing device provided in one embodiment of the present invention.

[0022] Figure 2 for Figure 1 Cross-sectional view of the structure.

[0023] Figure 3 for Figure 1 Front and side views of the structure.

[0024] Figure 4 for Figure 2 Cross-sectional view of the target holder cylinder.

[0025] Figure 5 for Figure 4 Right view of .

[0026] Figure 6 for Figure 4 Side view of the front.

[0027] Figure 7 for Figure 5 Top view of the .

[0028] Figure 8 for Figure 2 Schematic diagram of the locking pin structure.

[0029] Fig. 9 for Figure 8 Right view of .

[0030] Fig.10 for Figure 8 sectional view of .

[0031] Fig.11 for Figure 8 Side view of the front.

[0032] Fig.12 for Figure 2 Schematic diagram of the assembly structure of the middle cage and steel balls.

[0033] Fig.13 for Fig.12 Right view of .

[0034] Fig.14 for Fig.12 Top view of the .

[0035] Fig.15 It is the front and side view of the retainer and steel ball assembly structure.

[0036] Fig.16The present invention is a schematic diagram of an application example of a non-pyrotechnic electromagnetic locking and releasing device provided by the present invention in a multi-unit separation system.

[0037] Fig.17 for Fig.16 Side view of the front.

[0038] Markings in the figure: 1. Target base end assembly, 2. Locking pin, 3. First detector simulation part, 4. Second detector simulation part, 11. Target base cylinder, 12. Elastic retaining ring for hole, 13. DC traction electromagnet, 14. Retaining frame, 15. Steel ball, 16. Reset spring. DETAILED DESCRIPTION

[0039] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with examples. 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.

[0040] like Figure 1 , Figure 2 Combination Figure 3 , is a schematic diagram of the structure of a non-pyrotechnic electromagnetic locking and releasing device provided by an embodiment of the present invention, comprising a target base end assembly 1 and a locking pin 2. The target base end assembly 1 comprises a target base cylinder 11, a hole elastic retaining ring 12, a DC traction electromagnet 13, a retaining frame 14, a steel ball 15, and a reset spring 16. The steel ball 15 is installed in the spherical groove of the retaining frame 14, and the retaining frame 14 and the steel ball 15 are installed together in the small diameter inner cavity of the target base cylinder 11. One end of the reset spring 16 contacts the inner end surface of the retaining frame 14, and the other end contacts the end surface of the DC traction electromagnet 13, and always maintains an elastic compression state. The lead wire of the DC traction electromagnet 13 passes through the threading hole opened in the target base cylinder 11, is installed in the large diameter inner cavity of the target base cylinder 11, one axial end is pressed and contacted with the reset spring 16, and the other end is limitedly installed with the target base cylinder 11 through the hole elastic retaining ring 12.

[0041] See also Figure 3 , Fig.16 Combination Fig.17 The target seat cylinder 11 and the locking pin 2 are respectively installed on the end faces of the first detector simulation component 3 and the second detector simulation component 4 that need to be connected and separated by bolts using flange structures, and have the characteristics of simple interface form and convenient installation.

[0042] like Figure 2 , Figure 4 , Figure 8 As shown, the target base cylinder 11 and the locking pin 2 are matched with conical surfaces, which helps the inner conical surface of the target base cylinder 11 to guide the locking pin 2 during the docking movement, and the use of conical surface matching helps to reduce the axial docking impact load.

[0043] See also Figure 8 As shown, the locking pin 2 is composed of a pin rod and a tapered structure, and an annular locking groove for locking the steel ball 15 is provided on the pin rod at the front end.

[0044] like Figure 2 , Figure 4 Combination Fig.12 The steel ball 15 is installed in the ball groove from outside to inside in the radial direction of the retainer 14. It should be noted that the steel ball 15 cannot pass through the ball groove of the retainer 14 and enter the inner cavity of the retainer 14. The steel ball 15 and the retainer 14 slide together into the small diameter inner cavity of the target seat cylinder 11. The cylindrical surface, arc surface and inner cavity end surface of the small diameter inner cavity limit the steel ball 15 in the radial and axial directions, and the minimum limit in the radial direction ensures that the steel ball 15 contacts the locking groove of the locking pin 2, and the maximum limit in the radial direction satisfies that the locking pin 2 can be smoothly inserted and pulled out from the inner cavity of the retainer 14. The ball lock structure has the characteristics of reliable locking, large load, smooth locking and unlocking, etc.

[0045] See also Figure 2 Combination Fig.15 As shown, the armature end face of the DC traction electromagnet 13 and the outer end face of the inner tube of the retaining frame 14 leave a suitable traction stroke, which ensures that when unlocking and releasing, the steel ball 15 has a lower unlocking impact load and unlocking time when it disengages from the locking groove of the locking pin 2.

[0046] like Figure 2 As shown, the DC traction electromagnet 13 is installed in the large diameter inner cavity of the target base cylinder 11 in the axial upper limit position through the hole using an elastic retaining ring 12, which has the characteristics of simple operation, easy replacement and quick installation.

[0047] See also Figure 2 Combination Fig.16 , Fig.17 , to explain in detail an application example of the present invention in a multi-unit separation system, wherein the DC traction electromagnet 13, the retaining frame 14, and the locking pin 2 are all provided with an inner hole structure for inserting a space traction rope to form a tethered satellite system.

[0048] The main working principle of the present invention is:

[0049] When the two-stage separation system is locked and connected, the pin rod of the locking pin 2 is guided along the inner conical surface of the target base cylinder 11 and inserted into the locking hole of the target base cylinder 11. The front end of the pin rod of the locking pin 2 pushes the steel ball 15 to move radially outward along the small-diameter inner cavity surface of the target base cylinder 11, and drives the retaining frame 14 to compress the reset spring 16 axially. When the movement distance of the steel ball 15 is close to the maximum limit in the radial direction, the axial limit constraint of the steel ball 15 on the locking pin 2 is released, and the locking pin 2 is inserted into the inner cavity of the retaining frame 14. Under the elastic force of the reset spring 16, the retaining frame 14 is pushed to drive the steel ball 15 to move axially until the steel ball 15 falls into the locking groove of the locking pin 2 and is locked, completing the locking connection action of the two-stage separation system.

[0050] When the two-stage separation system is separated, a separation electrical signal is given, the DC traction electromagnet 13 generates magnetic force, and the traction retainer 14 drives the steel ball 15 to move axially to overcome the elastic force of the reset spring 16. When the steel ball 15 leaves the locking groove of the locking pin 2, the locking pin 2 is pulled out of the target seat cylinder 11, and at the same time the reset spring 16 pushes the retainer 14 to drive the steel ball 15 to reset, completing the separation action of the two-stage separation system.

Claims

1. Non-explosive low-impact electromagnetic locking and releasing device, characterized by: It includes a target seat end assembly and a locking pin; the target seat end assembly is fixedly mounted on one end of a separation system substrate; the locking pin is mounted on a substrate of another separation system; the target seat end assembly includes a target seat cylinder, a hole elastic retaining ring, a DC traction electromagnet, a retaining frame, a steel ball, and a reset spring; the target seat cylinder includes a large-diameter inner cavity and a small-diameter inner cavity structure; the steel ball is mounted in a spherical groove of the retaining frame, and the retaining frame and the steel ball are mounted together in the small-diameter inner cavity of the target seat cylinder; one end of the reset spring contacts the inner end face of the retaining frame, and the other end contacts the end face of the DC traction electromagnet; the DC traction electromagnet is mounted in the large-diameter inner cavity of the target seat cylinder, one axial end is in compression contact with the reset spring, and the other end is limitedly mounted with the target seat cylinder through the hole elastic retaining ring, and the lead wire of the DC traction electromagnet passes through the threading hole provided in the target seat cylinder.

2. The non-explosive low-impact electromagnetic locking and releasing device according to claim 1, characterized in that: The locking pin comprises a pin rod and a conical structure, and the pin rod is provided with an annular locking groove for locking the steel ball.

3. The non-explosive low-impact electromagnetic locking and releasing device according to claim 1, characterized in that: The threading hole provided on the target seat cylinder is arranged on the inner cavity with a large diameter.

4. The non-explosive low-impact electromagnetic locking and releasing device according to claim 1, characterized in that: The target seat cylinder and the locking pin are matched with each other using conical surfaces.

5. The non-explosive low-impact electromagnetic locking and releasing device according to claim 1, characterized in that: The steel balls are installed in the ball-shaped grooves from outside to inside in the radial direction of the retaining frame.

6. The non-explosive low-impact electromagnetic locking and releasing device according to claim 1, characterized in that: A traction stroke is reserved between the armature end face of the DC traction electromagnet and the outer end face of the inner tube of the retaining frame.

7. The non-explosive low-impact electromagnetic locking and releasing device according to claim 1, characterized in that: The return spring always keeps an elastically compressed state.

8. The non-explosive low-impact electromagnetic locking and releasing device according to claim 1, characterized in that: The release device can be applied to a multi-unit separation system.

9. The non-explosive low-impact electromagnetic locking and releasing device according to claim 1, characterized in that: The DC traction electromagnet, the retaining frame and the locking pin are all provided with an inner hole structure for inserting the space traction rope to form a tethered satellite system.

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