CN115108048A - Damping speed stabilizing mechanism for controlling unfolding speed of passive unfolding device - Google Patents

Abstract

The invention relates to a damping speed stabilizing mechanism for controlling the unfolding speed of a passive unfolding device, which comprises an unfolding mechanism, a speed increasing mechanism and a damper; the unfolding mechanism is a passive unfolding mechanism, an input shaft of the speed increasing mechanism is connected with a rotating part of the unfolding mechanism, and an output shaft of the speed increasing mechanism is connected with the damper; the attenuator includes pivot, sleeve and damping subassembly, and the pivot links to each other with speed increasing mechanism's output shaft, and the coaxial setting of sleeve is in the outside of pivot, and damping subassembly is located the cavity that forms between pivot and the sleeve, and quantity is 2 at least, along the circumference evenly distributed of pivot. Compared with the prior art, the invention can ensure that the speed tends to be stable in the unfolding process of the unfolding mechanism, thereby reducing the impact generated during unfolding, ensuring the safety of the spacecraft and avoiding the on-orbit damage of the spacecraft.

Description

A damping speed-stabilizing mechanism for controlling the deployment speed of a passive deployment device

technical field

The invention relates to the field of space mechanisms, in particular to a damping speed stabilization mechanism for controlling the deployment speed of a passive deployment device.

Background technique

The spacecraft has many deployment mechanisms, such as antenna arrays, solar cell arrays, and deployable magnetometers, which are all folded on both sides of the spacecraft during launch, and deployed and locked in place after the spacecraft enters orbit. Spacecraft deployment mechanisms can be divided into active deployment mechanisms and passive deployment mechanisms.

The active deployment mechanism uses a motor as a power source, and the passive deployment mechanism uses a hinge (with a torsion spring inside), etc. The active deployment mechanism is safe, reliable and stable, but it consumes electricity, has a complex structure and is expensive. The passive unfolding mechanism is cheap and reliable, but the speed of the unfolding process is not stable, and the locking moment when unfolding in place has a large impact, and there are certain safety hazards.

At present, most spacecraft use passive deployment mechanisms, and the impact generated when they are deployed in place and locked is relatively large. The impact is borne by the spacecraft body, which poses a great safety hazard to the spacecraft, and the spacecraft body is easily damaged. The current passive deployment mechanism mainly adopts the mechanical deployment method and the shape memory deployment method. The mechanical deployment mechanism has the disadvantages of complex mechanical structure, easy impact damage, high quality and high cost. The shape memory unfolding mechanism is a newly developed unfolding mechanism in recent years, which uses shape memory alloys. Although this type of unfolding mechanism has a simple structure, it is difficult to control the temperature of the material. The temperature control is very important for these materials. It is related to the toughness and service life of the material.

When the above two passive deployment mechanisms are deployed in place for locking, they will generate shocks, which will affect the safety of the spacecraft.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a damping speed stabilization mechanism for controlling the deployment speed of a passive deployment device in order to overcome the above-mentioned defects of the prior art.

The object of the present invention can be realized through the following technical solutions:

A damping and speed-stabilizing mechanism for controlling the deployment speed of a passive deployment device, comprising a deployment mechanism, a speed-increasing mechanism and a damper;

The unfolding mechanism is a passive unfolding mechanism, the input shaft of the speed-increasing mechanism is connected with the rotating part of the unfolding mechanism, the structural form of the input shaft is the same as that of the original plate hinge, and the output shaft of the speed-increasing mechanism is connected to the damper. connected to the device;

The damper includes a rotating shaft, a sleeve and a damping assembly, the rotating shaft is connected with the output shaft of the speed-increasing mechanism, the sleeve is coaxially arranged on the outside of the rotating shaft, and the damping assembly is located between the rotating shaft and the sleeve. In the cavity, the number is at least 2, which are evenly distributed along the circumference of the rotating shaft.

The working principle of the present invention is:

When the unfolding mechanism is started, the rotating parts will rotate, the rotational speed will be transmitted to the speed-increasing mechanism, and after the speed-up is transmitted to the damper, the rotating shaft will rotate. The pressing force generates damping torque, and the higher the rotational speed, the greater the damping torque. When the rotational speed is lower than the critical rotational speed, the damping component is disengaged from the sleeve. Therefore, during the deployment process of the passive deployment mechanism, the damper can generate a damping torque when the rotational speed is high, so as to control the speed during deployment, reduce the impact generated during deployment, and ensure the safety of the spacecraft.

Preferably, the damping assembly includes a spring and a damping block, a shaft sleeve is fixed on the rotating shaft, a guide sleeve slidingly matched with the shaft sleeve is arranged on the damping block, the spring is installed in the shaft sleeve and the guide sleeve, and the two ends are respectively connected with the shaft sleeve. The bottom of the shaft is connected with the damping block; when the shaft rotates, the shaft sleeve-guide sleeve forms a guide groove, when accelerating, the damping block slides outward under the action of centrifugal force, stretches the spring, and rubs against the inner wall of the sleeve; when decelerating, The damping block moves concentrically under the action of the spring tension and is disengaged from the sleeve.

Preferably, the damping assembly further includes a limiting mechanism, which is installed on the rotating shaft and includes an upper sealing plate and a lower sealing plate, which are used to limit the displacement of the damping block in the axial direction of the rotating shaft.

Preferably, a damping sheet is provided at the end of the damping block close to the sleeve.

Preferably, the curvature of the damping sheet is consistent with the curvature of the inner wall of the sleeve, which can increase the contact area between the damping sheet and the inner wall of the sleeve as much as possible and improve the damping effect; the damping sheet is made of non-asbestos resin composite material, non-asbestos resin composite material. Asbestos resin composite material is a material used in brake pads, which has good friction performance and heat dissipation performance, and is a mature commercial product.

Preferably, the number of the damping components is 4, which are evenly distributed along the circumferential direction of the rotating shaft.

Preferably, the speed increasing mechanism adopts a harmonic gear as a transmission pair.

Preferably, the gear ratio of the harmonic gear is 80.

Preferably, the output shaft of the speed-increasing mechanism and the rotating shaft of the damper are connected in the form of a shaft key.

Preferably, the speed-increasing mechanism is provided with mounting holes, the sleeve is mounted on the speed-increasing mechanism through connectors, such as bolts, etc., the sleeve is fixed on the speed-increasing mechanism, and the rotating shaft is connected to the output shaft of the deceleration mechanism.

Compared with the prior art, the present invention has the following beneficial effects:

(1) The damping speed stabilization mechanism is designed. When the rotational speed is lower than the critical rotational speed, the damping component does not contact the sleeve and does not generate damping torque; when the rotational speed is higher than the critical rotational speed, the damping component contacts the inner wall of the sleeve and generates damping torque , the higher the rotational speed, the greater the damping torque; thus ensuring that the speed tends to be stable during the deployment process, reducing the impact generated during deployment, ensuring the safety of the spacecraft and avoiding on-orbit damage to the spacecraft.

(2) The damping assembly includes a spring and a damping block. The shaft sleeve on the rotating shaft and the guide sleeve on the damping block are slidingly matched. The spring extends and contracts along the shaft sleeve and the guide sleeve, and the movement is smoother.

(3) A damping sheet is provided, and the curvature of the damping sheet is consistent with the curvature of the inner wall of the sleeve, which can increase the contact area between the damping sheet and the inner wall of the sleeve as much as possible, and improve the damping effect.

Description of drawings

Figure 1 is a schematic structural diagram of a damping speed stabilization mechanism;

Fig. 2 is the configuration diagram of the speed-increasing mechanism;

Figure 3 is a configuration diagram of a damper;

Figure 4 is a schematic diagram of the butt installation of the damper and the speed-increasing mechanism;

Reference numerals: 1. Unfolding mechanism, 2. Speed-increasing mechanism. 3. Damper, 31, shaft, 32, sleeve, 33, damping component.

Detailed ways

The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. This embodiment is implemented on the premise of the technical solution of the present invention, and provides a detailed implementation manner and a specific operation process, but the protection scope of the present invention is not limited to the following embodiments.

In the drawings, structurally identical components are denoted by the same numerals, and structurally or functionally similar components are denoted by like numerals throughout. The size and thickness of each component shown in the drawings are arbitrarily shown, and the present invention does not limit the size and thickness of each component. Parts in the drawings have been appropriately exaggerated in some places for clarity of illustration.

Example 1:

A damping speed stabilization mechanism for controlling the deployment speed of a passive deployment device, as shown in FIG. 1 , includes a deployment mechanism 1 , a speed increasing mechanism 2 and a damper 3 ;

The unfolding mechanism 1 is a passive unfolding mechanism. The configuration diagram of the speed-increasing mechanism 2 is shown in Figure 2. The input shaft of the speed-increasing mechanism 2 is connected to the rotating part of the unfolding mechanism 1, and the structure of the input shaft is the same as that of the original plate hinge. The form is the same, the output shaft of the speed-increasing mechanism 2 is connected with the damper 3;

The configuration diagram of the damper 3 is shown in FIG. 3 . The damper 3 includes a rotating shaft 31 , a sleeve 32 and a damping assembly 33 . Outside, the damping components 33 are located in the cavity formed between the rotating shaft 31 and the sleeve 32 , and the number is at least two, evenly distributed along the circumferential direction of the rotating shaft 31 . In this embodiment, the number of damping components 33 is four.

The working principle of the present invention is:

When the unfolding mechanism 1 is started, the damper 3 does not work when the unfolding mechanism 1 starts, and the rotational speed of the rotating part is transmitted to the speed-increasing mechanism 2, and then transferred to the damper 3 after the speed-up, and the rotating shaft 31 rotates. When the rotational speed rises and reaches the critical rotational speed Then, under the action of centrifugal force, the damping component 33 contacts the inner wall of the sleeve 32 and forms a pressing force to generate a damping torque. The higher the rotational speed, the greater the damping torque. When the rotational speed is lower than the critical rotational speed, the damping component 33 is disengaged from the sleeve 32. open. Therefore, during the deployment process of the passive deployment mechanism 1, the damper 3 can generate a damping torque when the rotational speed is high, so as to control the speed during deployment, reduce the impact generated during deployment, and ensure the safety of the spacecraft.

The unfolding mechanism 1 only transmits rotational speed and does not provide torque. In order to reduce the damage to the spacecraft satellite caused by the impact of the deployment mechanism 1 when it is deployed in place, it can be achieved by modifying the inter-plate deployment locking mechanism, removing the cable pulley, deployment spring and related parts of the original inter-plate deployment mechanism 1 , connect its rotating shaft with the speed-increasing mechanism 2, and the speed-increasing mechanism 2 is connected with the damper 3, which can achieve the purpose of normal operation of the damper 3 by controlling the speed.

The speed-increasing mechanism 2 uses a harmonic gear with a transmission ratio of 80 as the transmission pair, and the rotational speed of the output shaft is greater than the rotational speed of the input shaft. can be consumed in large quantities. The structure of the input shaft is the same as that of the original plate hinge, and the output shaft of the speed-increasing mechanism 2 and the rotating shaft 31 of the damper 3 are connected by a shaft key, as shown in Figures 3 and 4.

The speed-increasing mechanism 2 is provided with a mounting hole, the sleeve 32 is installed on the speed-increasing mechanism 2 through connectors, such as bolts, etc., the sleeve 32 is fixed on the speed-increasing mechanism 2, and the rotating shaft 31 is connected with the output shaft of the speed-increasing mechanism 2 .

As shown in FIG. 4 , the damping assembly 33 includes a spring and a damping block. A shaft sleeve is fixed on the rotating shaft 31 . The damping block is provided with a guide sleeve slidably matched with the shaft sleeve. The spring is installed in the shaft sleeve and the guide sleeve. It is connected with the bottom of the shaft sleeve and the damping block; when the rotating shaft 31 rotates, the shaft sleeve-guide sleeve forms a guide groove, and when accelerating, the damping block slides outward under the action of centrifugal force, stretches the spring, and rubs against the inner wall of the sleeve 32 ; During deceleration, the damping block moves concentrically under the action of the spring tension, and disengages from the sleeve 32. The damping assembly 33 further includes a limiting mechanism, which is installed on the rotating shaft 31 and includes an upper sealing plate and a lower sealing plate, and is used to limit the displacement of the damping block in the axial direction of the rotating shaft 31 .

The end of the damping block close to the sleeve 32 is provided with a damping sheet. The curvature of the damping sheet is consistent with the curvature of the inner wall of the sleeve 32, which can increase the contact area between the damping sheet and the inner wall of the sleeve 32 as much as possible, and improve the damping effect; the damping sheet is made of non-asbestos resin composite material, and the non-asbestos resin composite material is A material used in brake pads with good friction and heat dissipation properties, and is a mature commercial product.

The preferred embodiments of the present invention have been described in detail above. It should be understood that those skilled in the art can make many modifications and changes according to the concept of the present invention without creative efforts. Therefore, all technical solutions that can be obtained by those skilled in the art through logical analysis, reasoning or limited experiments on the basis of the prior art according to the concept of the present invention shall fall within the protection scope determined by the claims.

Claims (10)

1. A damping speed-stabilizing mechanism for controlling the deployment speed of a passive deployment device, characterized in that it comprises a deployment mechanism, a speed-increasing mechanism and a damper; The unfolding mechanism is a passive unfolding mechanism, the input shaft of the speed-increasing mechanism is connected with the rotating part of the unfolding mechanism, and the output shaft of the speed-increasing mechanism is connected with the damper; The damper includes a rotating shaft, a sleeve and a damping assembly, the rotating shaft is connected with the output shaft of the speed-increasing mechanism, the sleeve is coaxially arranged on the outside of the rotating shaft, and the damping assembly is located between the rotating shaft and the sleeve. In the cavity, the number is at least 2, which are evenly distributed along the circumference of the rotating shaft. 2. A damping speed stabilization mechanism for controlling the deployment speed of a passive deployment device according to claim 1, wherein the damping assembly comprises a spring and a damping block, a shaft sleeve is fixed on the rotating shaft, and the damping block is A guide sleeve is provided for sliding cooperation with the shaft sleeve, the spring is installed in the shaft sleeve and the guide sleeve, and the two ends are respectively connected with the bottom of the shaft sleeve and the damping block. 3 . The damping speed stabilization mechanism for controlling the deployment speed of the passive deployment device according to claim 2 , wherein the damping assembly further comprises a limit mechanism, and the limit mechanism is installed on the rotating shaft, 4 . It includes an upper sealing plate and a lower sealing plate, which are used to limit the deflection of the damping block in the axial direction of the rotating shaft. 4 . The damping speed stabilization mechanism for controlling the deployment speed of a passive deployment device according to claim 2 , wherein a damping sheet is provided at the end of the damping block close to the sleeve. 5 . 5 . The damping speed stabilization mechanism for controlling the deployment speed of a passive deployment device according to claim 4 , wherein the curvature of the damping sheet is consistent with the curvature of the inner wall of the sleeve. 6 . 6 . The damping speed stabilization mechanism for controlling the deployment speed of a passive deployment device according to claim 1 , wherein the number of the damping components is 4. 7 . 7 . The damping speed stabilization mechanism for controlling the deployment speed of a passive deployment device according to claim 1 , wherein the speed increasing mechanism adopts a harmonic gear as a transmission pair. 8 . 8 . The damping speed stabilization mechanism for controlling the deployment speed of a passive deployment device according to claim 7 , wherein the transmission ratio of the harmonic gear is 80. 9 . 9 . The damping speed stabilization mechanism for controlling the deployment speed of the passive deployment device according to claim 7 , wherein the output shaft of the speed increasing mechanism and the rotating shaft of the damper are connected in the form of a shaft key. 10 . . 10 . The damping speed stabilization mechanism for controlling the deployment speed of a passive deployment device according to claim 7 , wherein the speed increasing mechanism is provided with a mounting hole, and the sleeve is installed on the speed increasing device through a connecting piece. 11 . institution.

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