CN213832156U

CN213832156U - One-rocket-multi-star parallel opposite separation rocket adapter device

Info

Publication number: CN213832156U
Application number: CN202022851088.1U
Authority: CN
Inventors: 黄小青; 胡吉军; 翟海涛; 崔敏亮; 李义飞; 陈辰
Original assignee: CASIC Rocket Technology Co
Current assignee: CASIC Rocket Technology Co
Priority date: 2020-12-01
Filing date: 2020-12-01
Publication date: 2021-07-30
Anticipated expiration: 2030-12-01

Abstract

The invention relates to a rocket adapter device with one rocket and multiple satellites in parallel opposite separation, which comprises an adapter frame, multiple satellites and a connecting separator, wherein the adapter frame is provided with a plurality of connecting holes; the adapter frame is of an overlapped multilayer structure, and each layer is matched with and provided with a satellite; the connection separator connects the satellite to the adapter frame, and works to realize the separation of the satellite from the adapter frame when necessary; each layer of satellites arranged in the overlapped multilayer structure is parallel to each other, and the satellites in each adjacent layer move parallelly and oppositely to be separated when being separated from the adapter frame. The following beneficial effects can be obtained: 1. each satellite completes the separation action of the satellite and the arrow in sequence, the satellites do not interact with each other, the separation posture is controllable, and the collision risk is greatly reduced. 2. The satellite and the adapter are guided by the guide rail sliding block, so that a good contact state in the separation process is ensured, and the satellite separation attitude control is further enhanced.

Description

One-rocket-multi-star parallel opposite separation rocket adapter device

Technical Field

The invention relates to the field of satellite-rocket separation, in particular to a rocket adapter device for separating one rocket and multiple stars in parallel opposite directions.

Background

With the development of launch vehicle technology, the need to establish low cost space entry capability is ever stronger. The one-rocket multi-satellite system is a direct and effective method, and multiple satellites are placed in a limited rocket payload envelope space as much as possible, so that a rocket can send the multiple satellites into space, the carrying capacity can be obviously improved, and the launching cost can be reduced.

Generally, a satellite is connected with a rocket body through an adapter device, the adapter device has an unlocking ejection function, when the rocket reaches a specified orbital height, the satellite is in a weightless state, the satellite is unlocked with the adapter connecting device, the adapter ejection device ejects the satellite, and separation of the satellite and the rocket is realized.

The large-size flat structure satellite is limited by the space of the rocket fairing and is mostly placed in a stacking mode. For the satellite and satellite separation mode in a stacked mode, the mainstream separation scheme at present is an integral axial separation scheme adopted by SpaceX company, namely, a plurality of satellites are axially separated at the same time. This solution has the following drawbacks: 1. a plurality of satellites are axially separated at the same time, interaction exists among the satellites in the separation process, the separation posture is not controllable, and high collision risk exists. 2. The axial rigidity and strength of a large-size flat structure satellite are generally weaker, and the influence of axial impact in the separation process on the satellite is larger.

Disclosure of Invention

Aiming at the defects in the prior art and solving the problem of adapting to the one-rocket multi-satellite launching task of a large-size flat structure satellite, the invention provides a one-rocket multi-satellite parallel opposite separation rocket adapter device, which comprises an adapter frame, a plurality of satellites and a connection separator;

the adapter frame is of an overlapped multilayer structure, and each layer is matched with and provided with a satellite;

the connection separator connects the satellite to the adapter frame, and works to realize the separation of the satellite from the adapter frame when necessary;

each layer of satellites arranged in the overlapped multilayer structure is parallel to each other, and the satellites in each adjacent layer move parallelly and oppositely to be separated when being separated from the adapter frame.

Further, the adapter frame comprises four vertical beams, a plurality of pairs of side beams and a plurality of cross beams, the plurality of pairs of side beams and the plurality of cross beams are fixed on the four vertical beams, a satellite is installed on one pair of side beams and one cross beam in a matched mode, the satellite is installed on one cross beam through a connecting separator, the satellite and the pair of side beams slide in a matched mode, and when the connecting separator works, the satellite slides on the pair of side beams and is separated from the adapter frame.

Further, the connecting separator is an explosion bolt and a separation spring, the explosion bolt fixes the satellite on the beam, the separation spring abuts against the satellite and the beam simultaneously, the explosion bolt separates the satellite from the beam when in work, and the separation spring pushes the satellite and the adapter frame away.

Furthermore, the pair of side beams are provided with slide rails, and the satellite is fixedly provided with a pair of matched slide blocks.

Further, overlap multilayer structure and be the even number layer, every two-layer is a set of, two crossbeams in a set of stagger relative setting, guarantee that parallel opposite direction motion separates when two satellites in a set of and adapter frame separate.

Preferably, the satellite is a large-size flat structure satellite.

Compared with the prior art, the technical scheme of the invention can obtain the following beneficial effects:

1. each satellite completes the separation action of the satellite and the arrow in sequence, the satellites do not interact with each other, the separation posture is controllable, and the collision risk is greatly reduced.

2. The satellite and the adapter are guided by the guide rail sliding block, so that a good contact state in the separation process is ensured, and the satellite separation attitude control is further enhanced.

3. The separation direction is along the width direction (radial direction) of the satellite, the problem that the large-size flat satellite is weak in axial impact resistance is solved, and the influence of axial impact on the satellite structure in the separation process is avoided.

Drawings

FIG. 1 is a view of the assembly of the apparatus of the present invention;

FIG. 2 is a block diagram of an adapter rail of the present invention;

FIG. 3 is a diagram of a satellite slider structure of the present invention;

fig. 4 is a sectional view a-a of fig. 1.

Wherein: 1-adapter frame, 11-vertical beam, 12-side beam, 121-slide rail, 13-cross beam, 2-multiple satellites, 20-slide block, 21-first satellite, 22-second satellite, 23-third satellite, 24-fourth satellite, 25-fifth satellite, 26-sixth satellite, 3-connection separator, 31-explosion bolt, 32-separation spring,

-a separation direction to the right,

-a direction of separation to the left,

-rocket axial direction.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.

As shown in FIG. 1, the invention provides a rocket adapter device with one rocket and multiple satellites in parallel opposite directions, which comprises an adapter frame, multiple satellites and a connecting separator;

the adapter frame is of an overlapped multilayer structure, the number of the layers is 6 in the embodiment, and each layer is matched with one satellite; 6 satellites are stacked in this way.

Example 2

As shown in fig. 2 and 3, the difference from embodiment 1 is that, specifically, the adapter frame includes four vertical beams, a plurality of pairs of side beams and a plurality of cross beams, the plurality of pairs of side beams and the plurality of cross beams are fixed on the four vertical beams, one pair of side beams and one cross beam are matched to mount a satellite, the satellite is mounted on the one cross beam through a connector-separator, the satellite is matched with the pair of side beams to slide, and when the connector-separator works, the satellite slides on the pair of side beams to separate from the adapter frame. In this embodiment, the pair of side beams are both provided with a slide rail, and the satellite is fixedly provided with a pair of matched slide blocks.

The rest is the same as in example 1.

Example 3

As shown in fig. 4, the difference from embodiment 2 is that, specifically, the connection separator is an explosive bolt that fixes the satellite on a beam and a separation spring that abuts both the satellite and the beam, the explosive bolt operates to separate the satellite and the beam, and the separation spring pushes the satellite and the adapter frame apart.

Overlap multilayer structure and be the even number layer, 6 layers, every two-layer is a set of, two crossbeams in a set of stagger relative setting, guarantee that parallel opposite direction motion separates when two satellites in a set of and adapter frame separation. When the separation action is controlled, according to group control, two satellites of each group are separated at the same time, and the two satellites are separated in parallel and opposite movement when being separated from the adapter frame.

The satellite is a large-size flat structure satellite.

The satellite installation process is as follows:

and placing the sliding blocks on the two sides of the satellite in the guide rail of the adapter, pushing the satellite to be in contact with the guide rail, and screwing the explosive bolt and the explosive nut to connect the satellite to the cross beam.

The separation process is as follows: the first satellite and the second satellite are used as a group, the explosion bolt is detonated to unlock, and the two satellites are separated in the horizontal opposite direction under the action of the compression spring. After separation is finished, the rocket final stage adjusts the attitude to a stable state, the third satellite and the fourth satellite are used as a group of explosive bolts for detonation and unlocking to realize horizontal opposite separation, then final stage attitude adjustment is sequentially finished, the fifth satellite and the sixth satellite are used as a group, and finally separation is carried out.

The rest is the same as example 2.

Claims

1. A rocket adapter device with one rocket and multiple satellites in parallel opposite separation is characterized by comprising an adapter frame, multiple satellites and a connecting separator;

2. A rocket adapter device for parallel-split one-arrow-multi-star rocket according to claim 1 wherein said adapter frame comprises four vertical beams, pairs of side beams and a plurality of cross beams, said pairs of side beams and said plurality of cross beams being secured to said four vertical beams, one of said pairs of side beams and one of said cross beams being adapted to receive a satellite, said satellite being adapted to be mounted to said one of said cross beams by means of a connector-splitter, said satellite being adapted to slide along said pair of side beams away from said adapter frame when said connector-splitter is in operation.

3. A rocket adapter device as recited in claim 2, wherein said connection decouplers are explosive bolts securing said satellites to said beam and decoupling springs abutting said satellites and said beam simultaneously, said explosive bolts operating to decouple said satellites from said beam, said decoupling springs pushing said satellites and said adapter frame apart.

4. A rocket adapter device for parallel opposite separation of rocket launchers according to claim 2 or 3, wherein said pair of side beams are each provided with a slide rail, and said satellites are fixedly provided with a pair of cooperating slide blocks.

5. A rocket adapter device for parallel opposite separation of rocket satellites according to claim 4 wherein said overlapping multi-layer structure is a double layer, each two layers are a group, two beams of said group are staggered and oppositely arranged to ensure that two satellites of said group are separated from the adapter frame by parallel opposite movement.

6. A rocket adapter device as recited in claim 5, wherein said satellites are large flat structure satellites.