Spacecraft separation spring compression device

Abstract

The application provides a spacecraft separation spring compression device, which comprises a booster rod, a threaded ejector rod, a threaded cover, a thrust ball bearing and a fixed sleeve; the bottom of the fixed sleeve is provided with a mounting portion, the top is an open portion, and the inside is a cavity for accommodating a spring assembly to be compressed; the threaded cover is fixedly connected to the open portion of the fixed sleeve, and the threaded cover is provided with a trapezoidal internal thread through hole; the threaded ejector rod is inserted into the fixed sleeve and is threadedly connected to the trapezoidal internal thread through hole of the threaded cover through the trapezoidal external thread arranged on the outer periphery of the threaded ejector rod, so as to form a trapezoidal thread pair; the shaft ring of the thrust ball bearing is fixedly connected to the threaded ejector rod and rotates synchronously with the threaded ejector rod, and the seat ring is in contact with the end face of the spring assembly to be compressed; and the booster rod is transversely arranged at one end of the threaded ejector rod located outside the fixed sleeve. The application is labor-saving through the operation of the booster rod, improves the compression efficiency of the spring to be compressed, bears part of the abrasion through the thrust ball bearing, sets the trapezoidal thread pair, and reduces the degree of thread abrasion.

Description

Technical Field

[0001] This application relates to the technical field of mechanical compression devices in spacecraft separation systems, and more particularly to a spacecraft separation spring compression device. Background Technology

[0002] During the assembly and testing of spacecraft separation systems, it is often necessary to manually pre-compress the separation spring to facilitate the installation of limiting devices. A common spring compression device in existing technology typically employs a simple screw-push structure. This structure usually consists of a screw with a standard triangular thread and a fixed base with a corresponding internal thread. In operation, the device is fixed, and the screw is rotated using a wrench or lever. The threaded joint converts the rotational motion into linear motion, directly pushing and compressing the spring assembly. This type of structure is widely used in small machinery and everyday tools; its principle is simple, and its manufacturing cost is low.

[0003] The existing publication number CN117067163A discloses a compression structure for springs, which can compress springs to a pre-assembled state and lock this pre-assembled state. This provides a compression structure and method for mass-producing compression spring assemblies containing inner and outer cylinders. The compression spring assembly includes an inner cylinder and an outer cylinder, with the inner cylinder sleeved inside the outer cylinder. A spring is sleeved on the inner cylinder. A base is included, with a connector positioning seat and a compression drive mechanism on the base. The compression drive mechanism includes a slider and a slider drive mechanism for driving the slider. The two ends of the compression spring assembly are respectively positioned on the connector positioning seat and the slider. Pin holes are correspondingly provided on the side walls of the inner and outer cylinders. When the slider compresses the spring to the pre-assembled state, the pin holes on the side walls of the inner and outer cylinders coincide. A stop pin is placed in the pin hole to lock the position between the inner and outer cylinders. However, this compression structure is laborious to operate with a handle, resulting in low operating efficiency, and the threaded connection between the screw seat and the screw is prone to wear.

[0004] While existing technical solutions have simple structures, they exhibit significant drawbacks when compressing spacecraft release springs with high stiffness and long stroke:

[0005] 1) High friction and difficult operation: Ordinary triangular threads have a high coefficient of friction, and there is sliding friction between the screw end and the spring assembly. During compression, a huge axial force needs to be overcome, resulting in extremely high friction between the threaded parts and on the contact surface. The operator needs to apply a large torque, which is very strenuous.

[0006] 2) Low efficiency: The enormous frictional force consumes most of the input work, leaving a low percentage of energy effectively used to compress the spring, resulting in low work efficiency. Compressing a spring often requires multiple people working together or takes a long time, making it difficult to meet the needs of mass production or efficient testing.

[0007] 3) Threads are prone to wear and have a short lifespan: Under high loads, ordinary thread teeth are prone to wear or even shear damage, which reduces the reliability and service life of the device.

[0008] 4) Poor neutrality and easy jamming: Pure sliding friction may cause the screw to deviate when pushing, generating radial force, which will aggravate friction and wear, and even cause jamming, thread seizing and other phenomena, affecting the smoothness of operation.

[0009] Therefore, the urgent technical problem to be solved is: how to provide a spacecraft separation spring compression device that solves the problems of laborious operation, low compression efficiency and easy wear of threads. Utility Model Content

[0010] The purpose of this application is to provide a spacecraft separation spring compression device that uses an assist rod to reduce effort and improve the compression efficiency of the spring to be compressed, uses a thrust ball bearing to bear part of the wear, and sets a trapezoidal thread pair to reduce the degree of thread wear.

[0011] To achieve the above objectives, this application provides a spacecraft separation spring compression device, comprising: an assist rod, a threaded push rod, a threaded cap, a thrust ball bearing, and a fixed sleeve;

[0012] The bottom of the fixed sleeve is provided with a mounting part for fixed connection with the ground or a vise, the top is an opening, and the inside is a cavity for accommodating the spring assembly to be compressed.

[0013] The threaded cap is fixedly connected to the opening of the fixed sleeve, and the threaded cap is provided with a trapezoidal internal thread through hole;

[0014] The threaded push rod is inserted into the fixed sleeve and is threadedly connected to the trapezoidal internal thread through hole of the threaded cover through the trapezoidal external thread on its outer periphery to form a trapezoidal thread pair;

[0015] The thrust ball bearing is fitted onto the end of the threaded push rod that extends into the fixed sleeve. The shaft ring of the thrust ball bearing is fixedly connected to the threaded push rod and rotates synchronously with the threaded push rod. Its seat ring contacts the end face of the spring assembly to be compressed.

[0016] The assist rod is laterally positioned at one end of the threaded push rod located outside the fixed sleeve. The assist rod applies a rotational torque to the threaded push rod, causing the threaded push rod to rotate. Under the action of the trapezoidal thread pair, the threaded push rod converts the rotational motion into linear motion, generating an axial thrust force for compressing the spring assembly to be compressed.

[0017] The spacecraft separation spring compression device described above, wherein the thrust ball bearing includes a shaft ring, balls, a cage, and a seat ring;

[0018] The ball bearings are tactilely connected between the shaft ring and the seat ring via the cage;

[0019] The seat ring contacts the end face of the spring assembly to be compressed;

[0020] After the threaded push rod rotates, it drives the shaft ring to rotate, and the ball rolls between the shaft ring and the seat ring;

[0021] The axial thrust is transmitted to the shaft ring through the threaded push rod, then to the seat ring through the ball bearings, and finally acts on the spring assembly to be compressed, thus compressing the spring assembly.

[0022] In the spacecraft separation spring compression device described above, the bottom end of the threaded push rod is provided with a shoulder;

[0023] The axial end face of the shoulder fits against one side of the shaft ring, restricting the shaft ring from moving axially along the threaded push rod;

[0024] The radial cylindrical surface of the shoulder is connected to the inner hole of the shaft ring.

[0025] In the spacecraft separation spring compression device described above, the side wall of the fixed sleeve is provided with an observation window for observing the compression amount of the spring assembly to be compressed.

[0026] In the spacecraft separation spring compression device described above, the bottom of the fixed sleeve is provided with a mounting flange or clamping part for fixed connection with the ground or a vise.

[0027] In the spacecraft separation spring compression device described above, the tooth angle of the trapezoidal external thread is 30°;

[0028] The trapezoidal internal thread angle of the trapezoidal internal thread through hole is 30°.

[0029] In the spacecraft separation spring compression device described above, the fixed sleeve is a hollow cylindrical structure.

[0030] In the spacecraft separation spring compression device described above, the top end of the threaded push rod is provided with a radial insertion hole.

[0031] The assist rod is disposed inside the socket.

[0032] The spacecraft separation spring compression device described above, wherein the assist rod comprises multiple components.

[0033] The top of the threaded push rod has multiple insertion holes;

[0034] The plurality of the assist rods are inserted into the plurality of the insertion holes respectively, perpendicular to the axial direction of the threaded push rod.

[0035] In the spacecraft separation spring compression device described above, the threaded cap is fixedly connected to the end of the fixed sleeve by bolts.

[0036] The beneficial effects achieved by this application are as follows:

[0037] (1) This application uses a trapezoidal thread pair and a thrust ball bearing. The high transmission efficiency of the trapezoidal thread pair and the low friction characteristics of the thrust ball bearing combine to allow the operator to compress a spring with a large stiffness with only a small torque. This makes it easy to achieve single-person operation, improves the operating speed, and thus improves the compression efficiency of the spring assembly.

[0038] (2) The trapezoidal thread pair of this application has high strength and wear resistance; the thrust ball bearing bears most of the friction and wear, protects the end of the threaded push rod and the end face of the spring assembly, and extends the service life of the core components of the device.

[0039] (3) The thrust ball bearing of this application makes the threaded push rod run reliably and smoothly during the pushing process, avoiding jamming and skew. Attached Figure Description

[0040] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0041] Figure 1 This is a three-dimensional structural view of a spacecraft separation spring compression device according to an embodiment of this application.

[0042] Figure 2 This is a schematic diagram of the internal structure of a spacecraft separation spring compression device according to an embodiment of this application.

[0043] Figure 3 This is a schematic diagram of the compression state of a spacecraft separation spring compression device according to an embodiment of this application.

[0044] Reference numerals: 1-Fixed sleeve; 2-Threaded cap; 3-Thrust ball bearing; 4-Threaded push rod; 5-Auxiliary rod; 6-Observation window; 7-Spring assembly to be compressed; 11-Mounting part; 12-Through hole; 13-Connecting through hole; 21-Cylindrical section; 22-Flange part; 23-Counterhead through hole; 31-Shaft ring; 32-Ball; 33-Seat ring; 41-Insertion section; 42-Auxiliary rod mounting part; 421-Insertion hole. Detailed Implementation

[0045] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0046] like Figure 1-3 As shown, this application provides a spacecraft separation spring compression device, including: an assist rod 5, a threaded push rod 4, a threaded cap 2, a thrust ball bearing 3, and a fixed sleeve 1; the fixed sleeve 1 has a mounting part 11 at the bottom for fixed connection with the ground or a vise, an opening at the top, and a cavity inside for accommodating the spring assembly 7 to be compressed. The mounting part 11 is a flange structure with 4 through holes, which are suitable for mounting bolts to achieve a fixed connection between the fixed sleeve 1 and the ground or a vise. The threaded cap 2 is fixedly connected to the opening of the fixed sleeve 1. The threaded cap 2 is provided with a trapezoidal internal thread through hole. The threaded push rod 4 is inserted into the fixed sleeve 1 and is threadedly connected to the trapezoidal internal thread through hole of the threaded cap 2 through the trapezoidal external thread on its outer circumference, forming a trapezoidal thread pair. The thrust ball bearing 3 is fitted on the end of the threaded push rod 4 that extends into the fixed sleeve 1. The shaft ring 31 of the thrust ball bearing 3 is fixedly connected to the threaded push rod 4 and rotates synchronously with the threaded push rod 4. Its seat ring 33 contacts the end face of the spring assembly 7 to be compressed. The assist rod 5 is laterally arranged at the end of the threaded push rod 4 located outside the fixed sleeve 1. The assist rod 5 applies a rotational torque to the threaded push rod 4. The threaded push rod 4 rotates. Under the action of the trapezoidal thread pair, the threaded push rod 4 converts the rotational motion into linear motion, generating an axial thrust force for compressing the spring assembly 7 to be compressed.

[0047] like Figure 2As shown, the thrust ball bearing 3 includes a shaft ring 31, balls 32, a cage, and a seat ring 33. The balls 32 are rolled between the shaft ring 31 and the seat ring 33 via the cage. The seat ring 33 contacts the end face of the spring assembly 7 to be compressed. After the threaded push rod 4 rotates, it drives the shaft ring 31 to rotate, and the balls 32 roll between the shaft ring 31 and the seat ring 33. The seat ring 33 is a movable ring structure, which abuts against the end face of the spring assembly to be compressed, thereby transmitting the axial thrust force of the threaded push rod 4 to the spring assembly 7 to be compressed, thus compressing the spring assembly 7. The axial thrust force is transmitted to the shaft ring 31 through the threaded push rod 4, and then to the seat ring 33 through the balls 32, and finally acts on the spring assembly 7 to be compressed. The thrust ball bearing 3 is the key to achieving labor saving and efficiency improvement. The thrust ball bearing 3 transforms the sliding friction between the rotational motion of the threaded push rod 4 and the end face of the spring assembly 7 to be compressed into rolling friction inside the thrust ball bearing 3. The rolling friction coefficient is much lower than the sliding friction coefficient, which means that under the condition of compressing the same spring and generating the same axial force, the frictional torque that needs to be overcome is greatly reduced, and the force required for the operator to rotate the assist rod 5 is also significantly reduced, thus achieving the effect of labor saving in operation.

[0048] In a specific embodiment of this utility model, the bottom end of the threaded push rod 4 is provided with a shoulder; the axial end face of the shoulder fits against one side of the shaft ring 31, restricting the shaft ring 31 from moving axially along the threaded push rod 4; the radial cylindrical surface of the shoulder is engaged with the inner hole of the shaft ring 31. Providing a shoulder at the bottom end of the threaded push rod 4 is a preferred solution for restricting the shaft ring 31 from moving axially along the threaded push rod 4.

[0049] In another embodiment of this utility model, the bottom end of the threaded push rod 4 is provided with a snap ring groove, and a snap ring is installed in the snap ring groove to achieve axial positioning of the shaft ring 31.

[0050] like Figure 1 As shown, the side wall of the fixed sleeve 1 is provided with an observation window 6 for observing the compression amount of the spring assembly 7 to be compressed. The observation window 6 is an elongated opening, arranged along the length of the fixed sleeve 1. Preferably, scale marks are provided on the edge of the observation window 6 for reading the compression amount of the spring assembly 7 to be compressed.

[0051] In another embodiment of this utility model, the bottom of the fixing sleeve 1 is provided with a mounting flange or clamping part for fixed connection with the ground or vise. The mounting flange or clamping part is used to securely fix the entire device to the ground foundation or vise.

[0052] In a specific embodiment of this utility model, the tooth profile angle of the trapezoidal external thread is 30°; the tooth profile angle of the trapezoidal internal thread in the trapezoidal internal thread through hole is also 30°. Compared with the triangular thread commonly used in the prior art, the trapezoidal thread has a smaller tooth profile angle (preferably 30°), a thicker root of the trapezoidal thread teeth, higher strength, and can withstand greater axial loads. At the same time, the transmission efficiency of the trapezoidal thread is significantly higher than that of the triangular thread, making it more conducive to converting rotational torque into axial thrust, thus achieving preliminary labor saving from the perspective of transmission principle.

[0053] As a specific embodiment of this utility model, the fixing sleeve 1 is a hollow cylindrical structure.

[0054] like Figure 2 As shown, the top of the threaded push rod 4 is provided with a radial insertion hole 421, and the assist rod 5 is disposed in the insertion hole 421.

[0055] like Figure 2 As shown, the threaded push rod 4 is a long rod structure, comprising: an insertion section 41 and an assist rod mounting part 42. The insertion section 41 and the assist rod mounting part 42 are integral structures. The insertion section 41 is machined with a trapezoidal external thread, which mates with the trapezoidal internal thread machined at the center of the threaded cap 2. The threaded push rod 4 and the threaded cap 2 are movably connected through the trapezoidal thread pair. The assist rod mounting part 42 has an insertion hole 421, which is perpendicular to the axis of the insertion section 41, for inserting the assist rod 5.

[0056] As a specific embodiment of this utility model, the assist rod 5 includes multiple ones, and the top of the threaded push rod 4 has multiple insertion holes 421; the multiple assist rods 5 are respectively inserted into the multiple insertion holes 421 in a direction perpendicular to the axis of the threaded push rod 4.

[0057] As a specific embodiment of this utility model, the threaded cap 2 is fixedly connected to the end of the fixed sleeve 1 by bolts, or the threaded cap 2 is threadedly connected to the fixed sleeve 1 to achieve the fixed connection between the threaded cap 2 and the fixed sleeve 1.

[0058] like Figure 2 As shown, the threaded cap 2 includes a cylindrical section 21 and a flange portion 22; the cylindrical section 21 and the flange portion 22 are an integral structure. The top end of the fixed sleeve 1 is provided with a connecting through hole 13; the flange portion 22 has a countersunk through hole 23; a bolt is installed in the countersunk through hole 23, the bolt passes through the connecting through hole 13 and is locked by a nut to achieve a fixed connection between the threaded cap 2 and the fixed sleeve 1.

[0059] like Figure 2 As shown, the bottom of the fixed sleeve 1 is provided with a through hole 12, which communicates with the cavity inside the fixed sleeve 1.

[0060] The working principle of this utility model is as follows:

[0061] First, securely fix the fixing sleeve 1 to the ground or a vise. Then, place the spring assembly 7 to be compressed into the fixing sleeve 1, with the lower end of the spring assembly 7 supported by the bottom of the fixing sleeve 1 and the upper end facing the seat ring 33 of the thrust ball bearing 3. Insert the assist rod 5 into the insertion hole 421 at the top of the threaded push rod 4. The operator rotates the assist rod 5, causing the threaded push rod 4 to rotate. Since the threaded cap 2 is fixed, the threaded push rod 4, under the action of the trapezoidal thread pair that mates with the threaded cap, converts the rotational motion into downward linear motion, thereby generating an axial thrust. This axial thrust is transmitted through the threaded push rod 4 to the shaft ring 31 of the thrust ball bearing 3, and then through the balls 32 to the seat ring 33, ultimately acting on the spring assembly 7 to be compressed, compressing the spring assembly 7. During this process, the thrust ball bearing 3 separates the rotational motion of the threaded push rod 4 from the stationary (or potentially slightly rotating) state of the end face of the spring assembly 7 to be compressed.

[0062] Continue rotating the threaded push rod 4 until the spring assembly 7 to be compressed is compressed to the predetermined stroke (this can be determined by the observation window 6 or scale markings on the fixed sleeve 1, or until the spring assembly 7 is pressed to the limit). At this point, install the limit screw or pin that comes with the spring assembly 7 to maintain its compressed state. Finally, rotate the threaded push rod 4 in the opposite direction to allow it to rise, remove the threaded cover 2, and the compressed and locked spring assembly can be removed from the fixed sleeve 1, completing the entire process.

[0063] The beneficial effects achieved by this application are as follows:

[0064] (1) This application uses a trapezoidal thread pair and a thrust ball bearing. The high transmission efficiency of the trapezoidal thread pair and the low friction characteristics of the thrust ball bearing combine to allow the operator to compress a spring with a large stiffness with only a small torque. This makes it easy to achieve single-person operation, improves the operating speed, and thus improves the compression efficiency of the spring assembly.

[0065] (2) The trapezoidal thread pair of this application has high strength and wear resistance; the thrust ball bearing bears most of the friction and wear, protects the end of the threaded push rod and the end face of the spring assembly, and extends the service life of the core components of the device.

[0066] (3) The thrust ball bearing of this application makes the threaded push rod run reliably and smoothly during the pushing process, avoiding jamming and skew.

[0067] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0068] In the description of this application, the word "for example" is used to mean "used as an example, illustration, or description." Any embodiment described as "for example" in this application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is provided to enable any person skilled in the art to implement and use the present invention. Details are set forth in the following description for purposes of explanation. It should be understood that those skilled in the art will recognize that the present invention can be implemented without using these specific details. In other instances, well-known structures and processes will not be described in detail to avoid obscuring the description of the present invention with unnecessary detail. Therefore, the present invention is not intended to be limited to the embodiments shown, but is consistent with the broadest scope of the principles and features disclosed in this application.

[0069] The above description is merely an embodiment of this utility model and is not intended to limit the scope of this utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of this utility model should be included within the scope of the claims of this utility model.

Claims

1. A spacecraft separation spring compression device, characterized in that, include: Powering rod, threaded push rod, threaded cap, thrust ball bearing and retaining sleeve; The bottom of the fixed sleeve is provided with a mounting part for fixed connection with the ground or a vise, the top is an opening, and the inside is a cavity for accommodating the spring assembly to be compressed. The threaded cap is fixedly connected to the opening of the fixed sleeve, and the threaded cap is provided with a trapezoidal internal thread through hole; The threaded push rod is inserted into the fixed sleeve and is threadedly connected to the trapezoidal internal thread through hole of the threaded cover through the trapezoidal external thread on its outer periphery to form a trapezoidal thread pair; The thrust ball bearing is fitted onto the end of the threaded push rod that extends into the fixed sleeve. The shaft ring of the thrust ball bearing is fixedly connected to the threaded push rod and rotates synchronously with the threaded push rod. Its seat ring contacts the end face of the spring assembly to be compressed. The assist rod is laterally positioned at one end of the threaded push rod located outside the fixed sleeve. The assist rod applies a rotational torque to the threaded push rod, causing the threaded push rod to rotate. Under the action of the trapezoidal thread pair, the threaded push rod converts the rotational motion into linear motion, generating an axial thrust force for compressing the spring assembly to be compressed.

2. The spacecraft separation spring compression device according to claim 1, characterized in that, The thrust ball bearing includes a shaft ring, balls, a cage, and a housing ring; The ball bearings are tactilely connected between the shaft ring and the seat ring via the cage; The seat ring contacts the end face of the spring assembly to be compressed; After the threaded push rod rotates, it drives the shaft ring to rotate, and the ball rolls between the shaft ring and the seat ring; The axial thrust is transmitted to the shaft ring through the threaded push rod, then to the seat ring through the ball bearings, and finally acts on the spring assembly to be compressed, thus compressing the spring assembly.

3. The spacecraft separation spring compression device according to claim 2, characterized in that, The bottom end of the threaded push rod is provided with a shoulder; The axial end face of the shoulder fits against one side of the shaft ring, restricting the shaft ring from moving axially along the threaded push rod; The radial cylindrical surface of the shoulder is connected to the inner hole of the shaft ring.

4. The spacecraft separation spring compression device according to claim 1, characterized in that, The side wall of the fixed sleeve is provided with an observation window for observing the compression amount of the spring assembly to be compressed.

5. The spacecraft separation spring compression device according to claim 1, characterized in that, The bottom of the fixed sleeve is provided with a mounting flange or clamping part for fixed connection with the ground or a vise.

6. The spacecraft separation spring compression device according to claim 1, characterized in that, The tooth angle of the trapezoidal external thread is 30°; The trapezoidal internal thread angle of the trapezoidal internal thread through hole is 30°.

7. The spacecraft separation spring compression device according to claim 1, characterized in that, The fixing sleeve is a hollow cylindrical structure.

8. The spacecraft separation spring compression device according to claim 1, characterized in that, The top end of the threaded push rod is provided with a radial insertion hole. The assist rod is disposed inside the socket.

9. The spacecraft separation spring compression device according to claim 8, characterized in that, The assist rod includes multiple rods. The top of the threaded push rod has multiple insertion holes; The plurality of the assist rods are inserted into the plurality of the insertion holes respectively, perpendicular to the axial direction of the threaded push rod.

10. The spacecraft separation spring compression device according to claim 1, characterized in that, The threaded cap is fixedly connected to the end of the fixed sleeve by bolts.

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