CN218877604U

CN218877604U - Star and arrow separation release

Info

Publication number: CN218877604U
Application number: CN202223348846.3U
Authority: CN
Inventors: 许璟华; 张楼楼; 董家广; 张守辉
Original assignee: Zhongke Ruige Yantai Technical Service Co ltd
Current assignee: Zhongke Ruige Yantai Technical Service Co ltd
Priority date: 2022-12-13
Filing date: 2022-12-13
Publication date: 2023-04-18
Anticipated expiration: 2032-12-13

Abstract

The utility model relates to a spacecraft star-arrow separation technical field, in particular to a star-arrow separation release, the on-line screen storage device comprises a base, the four corners of base can all be rotated and is provided with the band pulley, the outside cover of four band pulleys is equipped with the hold-in range, equidistant a plurality of through-holes that are provided with on the hold-in range, the top of band pulley is provided with a plurality of follower balls that cooperate with the through-hole, hook-shaped portion that cooperates with satellite bottom slot is provided with on the top of band pulley, the lateral wall of band pulley has been seted up the slot, install the pin puller on the base, the pin puller can be pegged graft in the slot, the inboard of hold-in range is equipped with a plurality of driving plates, the driving plate is installed on the hold-in range through the bolt, be provided with a plurality of fixing bases on the base, fixing base and driving plate one-to-one correspond, be connected with first spring between fixing base and the driving plate, be provided with a plurality of separation promotion subassemblies on the base; the utility model discloses a hold-in range drives four band pulley synchronization motion and realizes the steady ejection of satellite.

Description

Star and arrow separation release

Technical Field

The utility model relates to a spacecraft satellite-rocket separation technical field, in particular to satellite-rocket separation release.

Background

In the aerospace field, payload to vehicle attachment and release is widespread, such as stages and stages of multi-stage rocket, satellite to launch vehicle, satellite to airship, solar wing to spacecraft, deployed antenna to spacecraft, and so forth. The mode that adopts at present has, the device based on initiating explosive device is connected and is released, the common initiating explosive device is connected and the release device has the seat that compresses tightly based on the explosion bolt, the band based on explosion bolt or initiating explosive cutter, the seat that compresses tightly based on initiating explosive separation bolt, the seat that compresses tightly based on initiating explosive cutter etc. of compressing tightly, these common characteristics that compress tightly the release device bear the joint force, for guaranteeing connection rigidity, the joint force often reaches thousands or even tens of thousands N, need utilize the huge explosion impact force of gunpowder to destroy initiating explosive device itself and realize the unblock, explosion impact during the unblock easily causes the damage to the spacecraft, disposable, lead to the cost higher.

When the separation device is in a separation state, 4 pressure springs push the guide rods, and 4 guide rods respectively push buckling surfaces on the satellite to push the satellite away from the base. Although the guide rail is arranged in the scheme to ensure the attitude, if the resultant moment generated by the ejection force to the satellite is large, the risk that the satellite is blocked on the guide rail or the unlocking is not smooth and the initial ejection speed is insufficient still exists, so that the load mass center needs to be accurately measured, and the accuracy of the elastic force of each spring is strictly required. For an ejection device without a guide rail, in order to stabilize the load posture in the ejection process, the thrust is required to exceed the load mass center, so that strict requirements are imposed on the thrust-deformation curve of each spring.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a satellite and rocket separation release drives four band pulley synchronization actions through the hold-in range and realizes the steady ejection of satellite.

In order to achieve the above purpose, the technical solution of the present invention is as follows:

the utility model provides a satellite and rocket separation release, includes the base, the four corners of base is all rotatable be provided with the band pulley, four the outside cover of band pulley is equipped with the hold-in range, equidistant a plurality of through-holes of being provided with on the hold-in range, fixed be provided with on the band pulley a plurality of with through-hole matched with follower ball, the top of band pulley is provided with the hook-like portion with satellite bottom slot matched with, the slot has been seted up on the lateral wall of band pulley, install on the base and pull out the round pin ware, the pin of pulling out the round pin ware can peg graft in the slot, the inboard of hold-in range is equipped with a plurality of driving plates, the driving plate passes through the bolt and installs on the hold-in range, be provided with a plurality of fixing bases on the base, fixing base and driving plate one-to-one, be connected with first spring between fixing base and the driving plate, be provided with a plurality of separation promotion subassemblies on the base.

Furthermore, the separation pushing assembly comprises a fixed cylinder fixedly connected to the base, a sliding rod slidably connected to the inside of the fixed cylinder, a pressing block fixedly connected to the top end of the sliding rod, and a second spring connected between the bottom end of the pressing block and the base.

Furthermore, a groove is formed in the bottom of the belt wheel, a baffle is arranged in the groove, and the baffle is fixedly connected to the base.

Furthermore, an assembly guide rod is vertically and fixedly connected to the base.

The utility model has the advantages that:

1. the four belt wheels are driven by the synchronous belt to synchronously rotate, so that linkage synchronous unlocking of the four hook-shaped parts is realized, and stable release and separation of the satellite are ensured;

2. the hold-in range is as a whole driving medium, and the first spring that uses can increase and decrease quantity and change the hookup location according to the demand, does not have strict requirement to first spring parameter uniformity.

Drawings

Fig. 1 is a schematic perspective view of the present invention;

fig. 2 is a schematic perspective view of the belt wheel of the present invention;

fig. 3 is a cross-sectional view of the separation pushing assembly of the present invention.

Reference numerals are as follows: a base 1; a pulley 2; a slot 201; a groove 202; a synchronous belt 3; a through hole 301; separating the pushing assembly 4; a fixed barrel 401; a slide bar 402; a briquetting 403; a second spring 404; a driven ball 5; a hook portion 6; a pin puller 7; a drive plate 8; a bolt 9; a fixed seat 10; a first spring 11; a baffle plate 12; the guide bar 13 is assembled.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

As shown in fig. 1 to 3, a satellite-rocket separation release device comprises a base 1, four corners of the base 1 are rotatably provided with belt pulleys 2, four synchronous belts 3 are sleeved outside the belt pulleys 2, a plurality of through holes 301 are equidistantly arranged on the synchronous belts 3, a plurality of driven balls 5 matched with the through holes 301 are fixedly arranged on the belt pulleys 2, hook-shaped portions 6 matched with grooves at the bottom of a satellite are arranged at the top ends of the belt pulleys 2, slots 201 are formed in the side walls of the belt pulleys 2, pin pulling devices 7 are installed on the base 1, pins of the pin pulling devices 7 can be inserted into the slots 201, a plurality of transmission plates 8 are arranged on the inner sides of the synchronous belts 3, the transmission plates 8 are installed on the synchronous belts 3 through bolts 9, a plurality of fixing seats 10 are arranged on the base 1, the fixing seats 10 correspond to the transmission plates 8 one to one another, first springs 11 are connected between the fixing seats 10 and the transmission plates 8, and a plurality of separation pushing assemblies 4 are arranged on the base 1.

The separation pushing assembly 4 comprises a fixed cylinder 401 fixedly connected to the base 1, a sliding rod 402 slidably connected to the inside of the fixed cylinder 401, a pressing block 403 fixedly connected to the top end of the sliding rod 402, and a second spring 404 connected between the bottom end of the pressing block 403 and the base 1.

A groove 202 is formed in the bottom of the belt pulley 2, a baffle plate 12 is arranged in the groove 202, and the baffle plate 12 is fixedly connected to the base 1; the rotation angle of the pulley 2 is restricted by providing the damper 12.

An assembly guide rod 13 is vertically and fixedly connected to the base 1; the satellite is inserted on the assembly guide rod 13, and the inaccurate installation position of the satellite can be prevented by arranging the assembly guide rod 13.

The working principle is as follows:

during installation, four grooves at the bottom of a satellite are installed in a matching manner with the hook-shaped part 6 at the top end of the belt wheel 2, the hook-shaped part 6 is vertically inserted into the grooves, pressure is applied to the top of the satellite, the four second springs 404 are compressed until the bottom of the satellite is pushed against the upper surface of the belt wheel 2, the belt wheel 2 is rotated by using a wrench, the hook-shaped part 6 at the top end of the belt wheel 2 forms an included angle with the grooves at the bottom of the satellite to hook the bottom of the satellite, so that the satellite is locked, the belt wheel 2 rotates, meanwhile, the synchronous belt 3 is driven to drive the synchronous belt 3 to drive the first spring 11 through the meshing relationship between the driven ball 5 and the through hole 301, the first spring 11 is in a stretching state, the pin puller 7 is started, the pin of the pin puller 7 is inserted into the slot 201 in the belt wheel 2 to prevent the belt wheel 2 from rotating, and the satellite is fixedly locked on the base 1 at the moment;

during separation, the pin puller 7 is started, the pin of the pin puller 7 leaves the slot 201 of the belt wheel 2, under the action of the restoring force of the first spring 11, the first spring 11 pulls the transmission plate 8 to move horizontally, the transmission plate 8 drives the synchronous belt 3 to transmit, the synchronous belt 3 drives the belt wheel 2 to rotate, the rotation angle of the belt wheel 2 is limited by the baffle 12, the hook-shaped part 6 can rotate to a position aligned with the groove at the bottom of the satellite, under the action of the restoring force of the second spring 404, the pressing block 403 moves upwards to push the satellite, the hook-shaped part 6 is separated from the groove at the bottom of the satellite, and the separation action of the satellite is completed; the utility model discloses a hold-in range 3 drives four 2 synchronous rotations of band pulley, realizes the synchronous unblock of 6 linkages of four hook-like portions, guarantees the separation of the steady release of satellite, and the first spring 11 that uses can increase and decrease quantity and change hookup location according to the demand, does not have strict demand to 11 numbers of first spring uniformity.

Finally, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the present invention can be modified or replaced by other means without departing from the spirit and scope of the present invention, which should be construed as limited only by the appended claims.

Claims

1. A satellite-rocket separation release device is characterized in that: including base (1), the four corners of base (1) all can be rotated and be provided with band pulley (2), four the outside cover of band pulley (2) is equipped with hold-in range (3), the equidistant a plurality of through-holes (301) that are provided with in hold-in range (3), fixed on band pulley (2) be provided with a plurality of with through-hole (301) matched with follower ball (5), the top of band pulley (2) is provided with hook portion (6) with satellite bottom slot matched with, slot (201) have been seted up on the lateral wall of band pulley (2), install on base (1) and pull out round pin ware (7), the pin of pulling out round pin ware (7) can be pegged graft in slot (201), the inboard of hold-in range (3) is equipped with a plurality of driving plates (8), driving plate (8) are installed through bolt (9) on hold-in range (3), be provided with a plurality of fixing bases (10) on base (1), fixing base (10) and driving plate (8) one-to-one, be connected with first spring (11) between fixing base (10) and driving plate (8), be provided with a plurality of separation subassembly (4).

2. The star-arrow separation release device according to claim 1, characterized in that: the separation pushing assembly (4) comprises a fixed cylinder (401) fixedly connected to the base (1), a sliding rod (402) slidably connected to the fixed cylinder (401), a pressing block (403) fixedly connected to the top end of the sliding rod (402), and a second spring (404) connected between the bottom end of the pressing block (403) and the base (1).

3. The star-arrow separation release device according to claim 1, characterized in that: the bottom of the belt wheel (2) is provided with a groove (202), a baffle (12) is arranged in the groove (202), and the baffle (12) is fixedly connected to the base (1).

4. The star-arrow separation release device according to claim 1, characterized in that: the base (1) is vertically and fixedly connected with an assembly guide rod (13).