CN101486383B - Compacting release mechanism for on-board equipment - Google Patents

Abstract

A satellite-borne equipment compressing and releasing mechanism comprises a mounting base body, a shearing resistant pin, a compressing mechanism, an isolation mechanism and an unlocking device; the mounting base body is fixedly connected with a satellite, a target load, the compressing mechanism and the isolation mechanism are sequentially arranged on the upper end surface of the mounting base body, radial location is carried out to the target load by the shearing resistant pin arranged on the mounting base body, and the shearing resistant pin is used for bearing the shearing force generated by the target load; one end of the compressing mechanism contacts with and restricts the target load and the other end thereof contacts with one end of the isolation mechanism by surfaces; the acting force of the isolation mechanism to the compressing mechanism is converted to friction force; the other end of the isolation mechanism is connected with the unlocking device; the compressing and locking are realized by the balance of the pretightening force provided by the unlocking device and the friction force borne by the isolation mechanism; and when unlocking, the unlocking device releases the pretightening force, the isolation mechanism rotates, the friction force of the isolation mechanism to the compressing mechanism disappears, the compressing mechanism rotates, and the target load is axially released along the shearing resistant pin.

Description

Spaceborne equipment compression release mechanism

technical field

The invention relates to a pressing and releasing mechanism for space-borne equipment, which belongs to the technical field of satellites and aerospace.

Background technique

Satellites or other spacecraft often need to complete some compression and release actions according to mission requirements or due to some constraints, such as the on-orbit separation between the parent body and the daughter body, the individual and the main body, etc. The completion of such actions is through complex To achieve this, the mechanism system must not only ensure that the spacecraft provides reliable constraints for the target load on the ground and during flight, but also ensure that the spacecraft can safely and reliably separate the target load after it enters orbit.

Compression and release are the two most important functions in this type of mechanism system, and they are also the two most critical force-bearing links. Compression means that the spacecraft constrains the target load at a designated position on the ground or during launch and indirectly guarantees its mechanical environment. Because the mechanical environment of the spacecraft on the ground or during launch is very complex, and the target load has a large impact on the The requirements of the working environment are relatively harsh, which puts forward higher requirements for the reliability of the compression mechanism, resulting in a complex composition of the compression mechanism system; release means that the spacecraft provides the compression mechanism to the target after entering the predetermined orbit. The constraint reduction of the load is to complete the separation or partial separation of the target load from the spacecraft parent body. The release mechanism generally unlocks the compression mechanism through the pyrotechnic device, and then the release mechanism starts to separate the target load. Various mechanical environments are experienced during ground and flight, which also put forward high requirements for the reliability of the release mechanism, which also leads to a relatively complex composition of the release mechanism system.

The separation mechanism of the satellite and the launch vehicle (referred to as the satellite-rocket separation mechanism) is a common spacecraft compression and release mechanism, and the separation tape is the most commonly used one of the satellite-rocket separation mechanisms. Various ground and flight tests have proved that the separation Tape is a highly reliable and simple structure of the spacecraft compression release mechanism, however, the separation of the tape still exposed some design and use of the shortcomings, as follows:

(1) The use environment is limited. According to the working principle of the star-rocket separation tape, the shape of the connected spacecraft can only be a cylinder, which makes the shape and structure of the spacecraft at the connection strictly restricted, making the use of the separation tape The environment is restricted;

(2) The machining accuracy of the connection surface is too high. According to the current use of the star-rocket separation tape, it can be seen that it puts forward higher requirements for the machining accuracy of the star-rocket separation surface of satellites and rockets, which brings difficulties to the machining process;

(3) The versatility between products is poor. Due to the characteristics of the star-arrow separation tape's own structure, the versatility between different types of tape is poor;

(4) The system composition is complex. Due to the limitation of the design principle and the use environment, the composition of the star-arrow separation tape system is still very complicated, and the assembly and debugging process of the whole system before use will take a long time.

The above-mentioned shortcomings of spacer and rocket separation tapes are also common problems in various spacecraft compression and release mechanisms. With the development of aerospace technology and the continuous increase of space missions, spacecraft compression and release mechanisms will be used in large numbers.

Contents of the invention

The technical problem of the present invention is: to overcome the deficiencies of the prior art, to provide a compression and release mechanism for spaceborne equipment, which has a simple structure, simple machining, assembly and debugging, high reliability and can be widely used.

The technical solution of the present invention is: the compression release mechanism of the spaceborne equipment, including the installation base body, the shear pin, the compression mechanism, the isolation mechanism and the unlocking device; the installation base body is firmly connected with the satellite, and the target load, compression The mechanism and the isolation mechanism are installed on the upper end surface of the installation base body in turn, and the target load is positioned radially through the shear pins installed on the installation base body, and the shear pins bear the shear force generated by the target load; the compression mechanism One end is in contact with the target load and constrained, and the other end is in surface contact with one end of the isolating mechanism to convert the force generated by the target load on the pressing mechanism into friction force. The other end of the isolating mechanism is connected to the unlocking device. The tightening force is balanced with the friction force on the isolation mechanism to achieve the compression and locking of the target load; when unlocking, the unlocking device releases the pre-tightening force, the isolation mechanism rotates, and the friction force of the isolation mechanism on the compression mechanism disappears. The compression mechanism rotates to release the constraint on the target load, and the target load is released along the axial direction of the shear pin.

A limiting boss is arranged under the end of the isolating mechanism in surface contact with the pressing mechanism to limit the displacement of the pressing mechanism along the friction direction during the pressing process.

The acting direction of the frictional force passes through the axis of the isolation mechanism at the installation position of the installation base.

The pressing mechanism includes a pressing lever, an adjustment screw, and a first connecting shaft. The pressing lever is installed on the installation base through the first connecting shaft. The pressing lever rotates around the first connecting shaft. One end of the pressing lever is opposite to the The target load is pressed, and the other end is restrained by surface contact with the isolation mechanism. The adjustment screw is installed on the installation base above the first connecting shaft, and the restraint force of the compression lever on the target load is adjusted through the adjustment screw.

The isolating mechanism includes a second connecting shaft and an isolating lever, the isolating lever is installed on the installation base through the second connecting shaft, the isolating lever rotates around the second connecting shaft, and one end of the isolating lever is in surface contact with one end of the pressing mechanism , and the other end is connected to the unlocking device.

The unlocking device includes a pretension spring, a connecting rope and a pyrotechnic unlocker; the pretension spring is installed between the isolation mechanism and the installation base, one end of the connection rope passes through the pretension spring and is connected to the isolation mechanism, and the other end is connected to the pyrotechnic mechanism. Unlocker connection.

The principle of the present invention is: through the cooperation of the compression lever and the shear pin, the compression of the target load of various structural forms can be completed; by setting the isolation lever, the preload force of the system can be isolated from the compression lever, effectively reducing The restraining force and displacement during the unlocking process that the small pressing lever bears. In addition, the requirements of larger and more complex target loads can be met through the cooperation of multiple sets of pressing and releasing mechanisms.

The process of compressing the target load is the process of static balance of the system. The compression lever is a component that directly produces a restraint force on the target load. The value of the restraint force will be very large. It is to balance this binding force. If the pre-tightening force is directly applied to the compression lever, the internal stress of the compression lever will increase sharply, seriously endangering its strength. Therefore, an isolation lever is provided. The setting of the isolation lever first changes the direction of the pre-tightening force that the mechanism should act on the compression lever, and secondly transfers the pre-tightening force from the compression lever to the isolation lever, and one end of the isolation lever is in contact with the pre-tension spring and bears its pre-tension. The other end is matched with the pressing lever. This matching design makes the pressing lever and the isolating lever only contact with one end surface when the system is in the initial equilibrium position, that is, there is only friction between the two levers, and the isolating lever can be pressed against each other. The micro-displacement of the lever is constrained, so that the friction and displacement constraints between the two can make each of them in a state of static equilibrium, reducing the internal stress of the lever, and at the same time isolating the setting of the lever during and after the mechanism is unlocked The displacement of the compression lever can be constrained.

During the assembly process of the whole mechanism, the adjustment screw can be adjusted to meet the pressure required by the target load, and other matching links can also be adjusted according to the characteristics of the target load and the mechanical environment in which it is located.

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

(1) The present invention is provided with an isolation lever. The setting of the isolation lever first changes the direction of the pre-tightening force that the mechanism should have acted on the compression lever, so that the direction of the pre-tightening force is downward, which is easy to realize; secondly, the pre-tightening force is transferred from the compression lever to the isolation lever, One end of the isolation lever is in contact with the pre-tightening spring and bears its pre-tightening force, and the other end is matched with the compression lever. This coordination design makes the compression lever and the isolation lever only have one end surface in contact with the isolation lever when the system is in the initial equilibrium position, that is, the distance between the two levers. There is only friction between them, which reduces the internal stress of the lever.

(2) It effectively reduces the difficulty of machining the spacecraft or target load at the separation joint. The press fit method adopted in the present invention does not require the spacecraft or the target load to have too high precision at the separation connection, which effectively reduces the difficulty of machining the spacecraft or the target load at the separation connection;

(3) The versatility between products is improved. Since the present invention can work in a mode of multi-group cooperation, it can well meet the requirements of generalization, modularization and serialization.

(4) The use environment of the compression and release mechanism of the entire set of spaceborne equipment is not restricted. Since the present invention can be used in a multi-group mode, this mechanism can meet the compression and release of various structural forms of spacecraft or target loads;

(5) The mechanism is simple in composition, and the time required for the assembly and debugging process before use is very short.

(6) The carrying capacity of the mechanism is relatively large. Since the present invention can work in a multi-group mode, the mechanism can theoretically carry various loads;

(7) Institutional security is improved. The use of the connecting rope and the pyrotechnic unlocker effectively improves the safety of the traditional explosive bolt in the unlocking process.

Description of drawings

Fig. 1 is the front view of four groups of spaceborne equipment pressing and releasing mechanisms of the present invention when they are used together in a balanced position;

Fig. 2 is a top view of Fig. 1;

Fig. 3 is a front view of the pressing and releasing mechanism of the spaceborne equipment of the present invention when it is in a balanced position;

Fig. 4 is the top view of Fig. 3;

Fig. 5 is a schematic diagram of four groups of spaceborne equipment pressing and releasing mechanisms used in conjunction with unlocking in the present invention; 5a front view, 5b top view;

Fig. 6 is a schematic diagram of the pressing and releasing mechanism of the spaceborne equipment of the present invention when it is unlocked.

Detailed ways

The following is a detailed description of the entire invention in the form of four typical groups of compression and release mechanisms for spaceborne equipment used in conjunction. As for the specific selection of several groups of compression and release mechanisms in the specific application process, it should be determined according to the shape of the target load.

As shown in Figures 1 and 2, the structure inside the dotted circle in Figure 2 is the compression and release mechanism of the spaceborne equipment of the present invention. In this embodiment, since the shape of the target load is a cuboid with little difference in length and width ratio, it is selected Four sets of pressing and releasing mechanisms are used for locking, and the target load is placed on the upper end of the box structure in the center of the installation base body shown in Figure 2.

The above-mentioned compression release mechanism for spaceborne equipment, as shown in Figures 3 and 4, mainly includes an installation base body 1, a shear pin 9, a compression mechanism, an isolation mechanism and an unlocking device, wherein the compression mechanism includes a first connecting shaft 6 , adjusting screw 7, compression lever 8, isolating mechanism comprises isolating lever 4, second connecting shaft 5, and unlocking device comprises connecting rope 2, pretension spring 3, pyrotechnic unlocker 10 (shown in Figure 2);

”；压紧锁定时，目标载荷放置在安装基座本体1中心的方框结构上端，目标载荷的四个角加工有与抗剪销钉9配合的孔，通过安装在安装基座本体1上的抗剪销钉9进行径向定位，由抗剪销钉9承受目标载荷产生的剪切力；每组压紧机构、隔离机构和解锁装置依次从方框结构向外安装在安装基座本体1的上端面，压紧杠杆8通过第一连接轴6安装在安装基座本体1上，压紧杠杆8可以围绕第一连接轴6旋转，根据目标载荷的大小等，第一连接轴6可以与压紧杠杆8做成一体，安装在安装基座本体1上。压紧杠杆8的一端对目标载荷进行压紧，该端的形状与目标载荷接触处的形状相配合，另一端与隔离杠杆4通过面接触进行约束，将整个机构对压紧杠杆8的预紧力转换为压紧杠杆8与隔离杠杆4之间的摩擦力，为了避免压紧杠杆8承受过大的外部载荷，从而导致压紧杠杆8内部应力过大，该摩擦力要通过第二连接轴5的轴心。隔离杠杆4围绕第二连接轴5旋转，隔离杠杆4的一端与压紧杠杆8的一端进行面接触，对压紧杠杆8施加作用力使其处于受力平衡状态，调整螺钉7配合压紧杠杆8对目标载荷进行约束，调整螺钉7可以调整压紧杠杆8的压紧状态，预紧弹簧3安装在隔离杠杆4和安装基座本体1之间，连接绳2一端穿过预紧弹簧3与隔离杠杆4连接，另一端与火工解锁器10连接，连接绳2拉动隔离杠杆4围绕第二连接轴5旋转使其处于受力平衡状态同时将预紧弹簧3压缩使其为整个机构提供所需的预紧力，此时整套机构就处于初始位置的受力平衡状态。The shape of the installation base body 1 is determined according to the shape of the target load. In this embodiment, the shape of the installation base body 1 is "

”; when pressing and locking, the target load is placed on the upper end of the frame structure at the center of the installation base body 1, and the four corners of the target load are processed with holes that match the shear pins 9, and through the holes installed on the installation base body 1 The shear pins 9 perform radial positioning, and the shear pins 9 bear the shear force generated by the target load; each set of pressing mechanism, isolation mechanism and unlocking device is installed on the mounting base body 1 from the box structure outwards in sequence. On the end face, the compression lever 8 is installed on the installation base body 1 through the first connecting shaft 6. The compression lever 8 can rotate around the first connection shaft 6. According to the size of the target load, the first connection shaft 6 can be connected with the compression The lever 8 is integrated and installed on the installation base body 1. One end of the compression lever 8 compresses the target load, the shape of this end matches the shape of the contact point of the target load, and the other end is in surface contact with the isolation lever 4 Constraint, the preload of the entire mechanism on the compression lever 8 is converted into the friction between the compression lever 8 and the isolation lever 4, in order to avoid the compression lever 8 from being subjected to excessive external loads, resulting in the compression of the compression lever 8 The internal stress is too large, and the frictional force will pass through the axis of the second connecting shaft 5. The isolating lever 4 rotates around the second connecting shaft 5, and one end of the isolating lever 4 is in surface contact with one end of the pressing lever 8, and the pressing lever 8 apply force to make it in a state of force balance, the adjustment screw 7 cooperates with the compression lever 8 to constrain the target load, the adjustment screw 7 can adjust the compression state of the compression lever 8, and the pretension spring 3 is installed on the isolation lever 4 and Between the installation base body 1, one end of the connecting rope 2 passes through the pretension spring 3 and is connected to the isolation lever 4, and the other end is connected to the pyrotechnic unlocker 10, and the connecting rope 2 pulls the isolation lever 4 to rotate around the second connecting shaft 5 to make it At the same time, the pre-tightening spring 3 is compressed to provide the required pre-tightening force for the whole mechanism, and the whole set of mechanisms is in the force-balanced state of the initial position at the same time.

As shown in Figure 5, when the pyrotechnic unlocker 10 is unlocked, the connecting rope 2 is unlocked and the binding force provided to the isolation lever 4 is relieved, at this time the isolation lever 4 will rotate counterclockwise around the second connecting shaft 5 Simultaneously, the restraining force added on the pretension spring 3 is subtracted, and the pretension spring 3 will further promote the isolation lever 4 to rotate counterclockwise around the second connecting shaft 5, so that the isolation lever 4 will add it on the compression lever 8. The binding force is subtracted, and the compression lever 8 rotates clockwise around the first connecting shaft 6 to be in a free state. 15 °) has just completed the release of this mechanism to the unlocking of the target load, and the displacement of the compression lever 8 will be limited by the isolation lever 4.

In order to increase the reliability of the compression release mechanism, a limit boss is provided under the end of the isolation lever 4 in surface contact with the compression lever 8 to limit the friction direction of the compression lever 8 during the compression process. the amount of displacement.

The material of the compression lever 8 in the present invention can adopt materials such as aluminum, steel, or titanium alloy according to the acting force it bears, and according to specific conditions, its strength can be enhanced by increasing the thickness of the compression lever 8.

Of course, the functions of the pressing mechanism and the isolating mechanism in the present invention can also be realized by adopting other structural forms, for example, the pressing lever 8 and the isolating lever 4 can be combined into one lever; Increase the intermediate transition lever between; or change the contact form between the pressing lever 8 and the target load from surface contact to point contact, etc.

Parts not described in detail in the present invention belong to the common knowledge of those skilled in the art.

Claims (6)

1. compacting release mechanism for on-board equipment is characterized in that: comprise mounting base body, shearing resistance pin, hold-down mechanism, interrupter and tripper;

Mounting base body and satellite are connected, target load, hold-down mechanism, interrupter are installed in mounting base body upper surface successively, target load carries out radial location by the shearing resistance pin that is installed on the mounting base body, bears the shearing force that target load produces by the shearing resistance pin; One end of hold-down mechanism contacts the row constraint of going forward side by side with target load, the other end contacts by face with interrupter one end, target load is converted to friction force to the application force that hold-down mechanism produces, the interrupter other end is connected with tripper, the suffered friction force of predetermincd tension that provides by tripper and interrupter carries out balance, realizes the locking that compresses to target load; During release, tripper discharges described predetermincd tension, and interrupter rotates, and interrupter disappears to the friction force of hold-down mechanism, and hold-down mechanism rotates, and removes the constraint to target load, and target load axially discharges along the shearing resistance pin; Described hold-down mechanism comprises clamping lever (8), trimming screw (7), first adapter shaft (6); Clamping lever (8) is installed on the mounting base by first adapter shaft (6), clamping lever (8) is around first adapter shaft (6) rotation, one end of clamping lever (8) compresses target load, the other end contacts by face with interrupter and retrains, trimming screw (7) is installed on the mounting base of top of first adapter shaft (6), adjusts the constrained force of clamping lever (8) to target load by trimming screw (7); Described interrupter comprises second adapter shaft (5), divided lever (4), divided lever (4) is installed on the mounting base by second adapter shaft (5), divided lever (4) rotates around second adapter shaft (5), one end of divided lever (4) carries out face with an end of hold-down mechanism and contacts, and the other end is connected with tripper.

2. compacting release mechanism for on-board equipment according to claim 1 is characterized in that: the end below that described interrupter contacts with the hold-down mechanism face is provided with a positive stop lug boss, in order to restriction hold-down mechanism displacement along the friction force direction in compaction process.

3. compacting release mechanism for on-board equipment according to claim 1 and 2 is characterized in that: described friction force action direction is by the installed position axis of interrupter at mounting base.

4. compacting release mechanism for on-board equipment according to claim 1 is characterized in that: described clamping lever (8) adopts aluminium, or steel, or titanium alloy material.

5. compacting release mechanism for on-board equipment according to claim 1 and 2 is characterized in that: described tripper comprises preloading spring (3), connection cord (2) and firer's unlocking device (10); Preloading spring (3) is installed between interrupter and the mounting base, and connection cord (2) one ends pass preloading spring (3) and are connected with interrupter, and the other end is connected with firer's unlocking device (10).

6. compacting release mechanism for on-board equipment according to claim 1 and 2 is characterized in that: the end shape that described hold-down mechanism contacts with target load matches with the target load shape.

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