阅读说明：本技术 一种偏置布局的星箭分离方法及星箭系统 (Satellite and arrow separation method with offset layout and satellite and arrow system ) 是由 梁纪秋 胡长伟 鲍永定 彭威 张林玉 李智 张榜 常子原 杜林霏 多乐乐 于 2021-08-03 设计创作，主要内容包括：本申请涉及一种偏置布局的星箭分离方法及星箭系统,该偏置布局包括在火箭末级的末端的火箭适配器、以及设置于火箭适配器的多个卫星,每个卫星与火箭适配器之间设置套筒装置,所述套筒装置内具有分离弹簧,且每个卫星通过相应的卫星适配器连接套筒装置。小刚度分离弹簧可以大大减小分离力对卫星和火箭适配器的冲击,姿控喷管在卫星分离的时候,向火箭的末端喷气,增加了星箭之间以及卫星之间的距离,从而解决卫星分离时星箭之间以及卫星之间安全间隙小、分离安全性较差的问题。(The application relates to a satellite-rocket separation method and a satellite-rocket system with an offset layout. The impact of the separating force on the satellite and the rocket adapter can be greatly reduced by the small-rigidity separating spring, the attitude control spray pipe sprays air to the tail end of the rocket when the satellite is separated, and the distances between the satellite and the rocket and between the satellites are increased, so that the problems of small safety gaps and poor separation safety between the satellite and the rocket and between the satellites when the satellite is separated are solved.)

1. A satellite-rocket separation method of an offset layout, the offset layout comprises a rocket adapter (11) arranged at the tail end of a rocket final stage (13) and a plurality of satellites (5) arranged on the rocket adapter (11), a sleeve device is arranged between each satellite (5) and the rocket adapter (11), a separation spring (10) is arranged in the sleeve device, and each satellite (5) is connected with the sleeve device through a corresponding satellite adapter (1), the satellite-rocket separation method is characterized by comprising the following steps:

s1, arranging attitude control spray pipes (12) at positions adjacent to two sides of the rocket final stage (13);

s2, in the initial state, the separation spring (10) is in a compressed state, and the attitude control spray pipe (12) is in a closed state;

s3, when a satellite (5) receives a separation instruction, the satellite (5) is unlocked, the corresponding satellite adapter (1) is disconnected with the rocket adapter (11), the separation spring (10) rebounds, and the satellite adapter (1) and the satellite (5) move in the direction far away from the rocket adapter (11) under the action of elastic force; meanwhile, the attitude control spray pipe (12) sprays air towards the tail end of the rocket final stage (13), and the rocket final stage (13) drives the rocket adapter (11) to actively keep away from the satellite (5);

s4, when the separation spring (10) is bounced to a preset position, rebounding is stopped, the satellite (5) is separated, and the attitude control spray pipe (12) is closed;

s5, and the rest satellites (5) finish separation according to the steps S2 to S4 in sequence according to a preset time sequence.

2. The star-rocket separation method with offset layout according to claim 1, wherein the attitude control nozzles (12) inject air toward the end of the rocket final stage (13), and the method comprises the following steps:

the attitude control spray pipe (12) vertically sprays air towards the tail end of the rocket final stage (13);

or the attitude control spray pipe (12) sprays air towards the tail end of the last rocket stage (13) by deviating a preset angle outwards, and the preset angle is 20 degrees.

3. The offset layout satellite-rocket separation method according to claim 1, wherein: the sleeve device comprises a push rod (6), a ball head (3) is arranged at one end of the push rod (6), and a ball head groove (2) corresponding to the ball head (3) is installed on the satellite adapter (1);

in the steps S2 and S3, the ball head (3) is positioned in the ball head groove (2);

in the step S4, the satellite (5) is separated, and the ball head (3) is removed from the ball head groove (2).

4. A satellite-rocket system, comprising:

the tail end of the rocket final stage (13) is provided with a rocket adapter (11), and the positions of the rocket final stage (13) adjacent to two sides are respectively provided with an attitude control spray pipe (12);

the number of the satellites (5) is multiple, each satellite (5) is connected with one satellite adapter (1) and is sequentially arranged on the side face of the rocket adapter (11);

the number of the sleeve devices is multiple, every two sleeve devices are arranged between each satellite adapter (1) and the rocket adapter (11), and a separation spring (10) is arranged in each sleeve device;

in the initial state, the separation spring (10) is in a compressed state, and the attitude control spray pipe (12) is in a closed state;

when a certain satellite (5) receives a separation instruction, the corresponding satellite adapter (1) is disconnected with the rocket adapter (11), the separation spring (10) rebounds, and the satellite adapter (1) and the satellite (5) move towards the direction far away from the rocket adapter (11); meanwhile, the attitude control spray pipe (12) sprays air towards the tail end of the rocket final stage (13), and the rocket final stage (13) drives the rocket adapter (11) to actively keep away from the satellite (5) together with other satellites.

5. The satellite arrow system according to claim 4 wherein: the air nozzle of the attitude control spray pipe (12) vertically faces the tail end of the rocket final stage (13), or the air nozzle of the attitude control spray pipe (12) deviates outwards from a preset angle, and the preset angle is 20 degrees.

6. The satellite arrow system according to claim 4 wherein: the sleeve device comprises a sleeve (7) and a push rod (6) arranged inside the sleeve (7), one end of the sleeve (7) is fixedly connected with the rocket adapter (11), the other end of the sleeve is abutted against the satellite adapter (1), one end of the push rod (6) is connected with the rocket adapter (11) through the separation spring (10), and the other end of the push rod is connected with the satellite adapter (1).

7. The satellite arrow system according to claim 6 wherein: a ball head support (4) is further arranged at one end, connected with the satellite adapter (1), of the push rod (6), a ball head (3) is mounted at the end of the ball head support (4), and a corresponding ball head groove (2) is formed in the satellite adapter (1);

before the satellite (5) is separated, the ball head (3) is positioned in the ball head groove (2); after the satellite (5) is separated, the ball head (3) is separated from the ball head groove (2).

8. The satellite arrow system according to claim 6 wherein: a strip-shaped groove (9) is formed in one end, close to the rocket adapter (11), of the side wall of the sleeve (7), and a push rod limiting pile (8) is arranged at one end, connected with the separation spring (10), of the push rod (6);

in an initial state, the push rod limiting pile (8) extends out of the strip-shaped groove (9);

after the satellite (5) is unlocked, the push rod limiting pile (8) moves along the strip-shaped groove (9), and when the push rod limiting pile (6) is to be moved to the end part of the strip-shaped groove (9), the push rod stops moving.

9. The satellite arrow system according to claim 4 wherein: the stiffness coefficient of the separation spring (10) in each sleeve device is smaller than 1N/mm, and the stiffness coefficient of each separation spring (10) is the same.

Technical Field

The application relates to the technical field of aerospace and aviation, in particular to a satellite and arrow separation method and a satellite and arrow system with a bias layout.

Background

With the development of aerospace technology, the application of multi-satellite networking technology directly promotes one-arrow multi-satellite launching technology, and the most critical one in the one-arrow multi-satellite launching technology is multi-satellite separation technology. In a conventional one-rocket-two-star or even one-rocket-multiple-star launching task, the satellite adopts a scheme of up-down serial arrangement and axial separation, the mass center of the satellite is basically coincident with the longitudinal axis of the rocket, and during separation, the satellite is sequentially unlocked and released along the axial direction, so that the safety is well guaranteed. In order to utilize the envelope and carrying capacity of the rocket fairing as much as possible, the multi-satellite tandem type offset layout is developed, in this case, the safety distance of the satellite is small, and when the satellite is sequentially separated along the circumferential direction or the axial direction, the mass center of the rocket deviates from the action line of separating force, so that the safety clearance is too small, the attitude interference is increased in the separation process, and the safety is poor.

Disclosure of Invention

The application provides a satellite and arrow separation method and a satellite and arrow system with offset layout, which aim to solve the problems of small safety clearance and poor separation safety during satellite separation in the related art.

The application provides a star and rocket separation method of offset layout, the offset layout includes a rocket adapter arranged at the tail end of a rocket final stage and a plurality of satellites arranged on the rocket adapter, a sleeve device is arranged between each satellite and the rocket adapter, a separation spring is arranged in the sleeve device, each satellite is connected with the sleeve device through the corresponding satellite adapter, and the star and rocket separation method comprises the following steps:

s1, arranging attitude control spray pipes at the positions adjacent to the two sides of the rocket final stage;

s2, in the initial state, the separation spring is in a compressed state, and the attitude control spray pipe is in a closed state;

s3, when a satellite receives a separation instruction, the satellite is unlocked, the satellite adapter corresponding to the satellite is disconnected with the rocket adapter, the separation spring rebounds, and the satellite adapter and the satellite move in the direction far away from the rocket adapter under the action of elastic force; meanwhile, the attitude control spray pipe sprays air towards the tail end of the rocket final stage, and the rocket final stage drives the rocket adapter to actively keep away from the satellite;

s4, when the separation spring is bounced to a preset position, rebounding is stopped, the satellite is separated, and the attitude control spray pipe is closed;

and S5, finishing the separation of the rest satellites according to the steps S2 to S4 in sequence according to a preset time sequence.

Further, the attitude control nozzle jets air toward the end of the rocket final stage, and comprises:

the attitude control spray pipe vertically sprays air towards the tail end of the rocket final stage;

or the attitude control spray pipe outwards deviates from the tail end of the last stage of the rocket and sprays air at a preset angle, and the preset angle is 20 degrees.

Furthermore, the sleeve device comprises a push rod, a ball head is arranged at one end of the push rod, and a ball head groove corresponding to the ball head is installed on the satellite adapter;

in the steps S2 and S3, the ball head is positioned in the ball head groove;

in step S4, the satellite completes separation, and the ball head comes out of the ball head groove.

The present application further relates to a satellite-rocket system, comprising:

the tail end of the rocket final stage is provided with a rocket adapter, and the positions of the rocket final stage, which are adjacent to two sides, are respectively provided with an attitude control spray pipe;

the number of the satellites is multiple, each satellite is connected with one satellite adapter, and the satellites are sequentially arranged on the side face of the rocket adapter;

the number of the sleeve devices is multiple, every two sleeve devices are arranged between each satellite adapter and the rocket adapter, and a separation spring is arranged in each sleeve device;

in the initial state, the separation spring is in a compressed state, and the attitude control spray pipe is in a closed state;

when a certain satellite receives a separation instruction, the satellite adapter corresponding to the certain satellite is disconnected with the rocket adapter, the separation spring rebounds, and the satellite adapter and the satellite move towards the direction far away from the rocket adapter; meanwhile, the attitude control spray pipe sprays air towards the tail end of the rocket final stage, and the rocket final stage drives the rocket adapter to actively keep away from the satellite together with other satellites.

Further, the air nozzle of the attitude control spray pipe vertically faces the tail end of the last stage of the rocket, or the air nozzle of the attitude control spray pipe deviates outwards by a preset angle which is 20 degrees.

Furthermore, the sleeve device comprises a sleeve and a push rod arranged in the sleeve, one end of the sleeve is fixedly connected with the rocket adapter, the other end of the sleeve is abutted against the satellite adapter, one end of the push rod is connected with the rocket adapter through the separation spring, and the other end of the push rod is connected with the satellite adapter.

Furthermore, a ball head support is further arranged at one end of the push rod, which is connected with the satellite adapter, a ball head is mounted at the end part of the ball head support, and the satellite adapter is provided with a corresponding ball head groove;

before the separation of the satellite, the ball head is positioned in the ball head groove; after the satellite is separated, the ball head is separated from the ball head groove.

Further, a strip-shaped groove is formed in one end, close to the rocket adapter, of the side wall of the sleeve, and a push rod limiting pile is arranged at one end, connected with the separation spring, of the push rod;

in an initial state, the push rod limiting pile extends out of the strip-shaped groove;

after the satellite is unlocked, the push rod limiting pile moves along the strip-shaped groove, and when the push rod limiting pile moves to the end part of the strip-shaped groove, the push rod stops moving.

Further, the stiffness coefficient of the separation spring in each sleeve device is smaller than 1N/mm, and the stiffness coefficient of each separation spring is the same.

The beneficial effect that technical scheme that this application provided brought includes:

the application provides a satellite and rocket separation method and a satellite and rocket system in a bias layout, the separation spring in the method is low in rigidity, and the impact of separation force on a satellite and a rocket adapter can be greatly reduced, so that the interference of attitude angular velocity on the separation of the satellite and the rocket is reduced, and the safety of the separation of the satellite and the rocket is improved.

Meanwhile, the attitude control spray pipe is opened when the satellites are separated, and air is sprayed to the tail end of the last stage of the rocket, so that the distances between the satellites and between the satellites are increased, and the safety of the satellites during separation is further guaranteed.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a general schematic diagram of a satellite-rocket separation method in an offset layout.

Fig. 2 is a schematic diagram of a state after the satellite separation in fig. 1 is finished.

Reference numerals:

1. a satellite adapter; 2. a ball head groove; 3. a ball head; 4. a ball head support; 5. a satellite; 6. a push rod; 7. a sleeve; 8. a push rod limiting pile; 9. a strip-shaped groove; 10. a separation spring; 11. a rocket adapter; 12. an attitude control spray pipe; 13. and (5) rocket final stage.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

The embodiment of the application provides a satellite and arrow separation method with a bias layout, which can solve the problems of small safety clearance and poor separation safety during satellite separation.

As shown in fig. 1, there is provided a satellite-rocket separation method in an offset layout, first, the offset layout includes a rocket adapter 11 disposed at the end of a rocket final stage 13, and a plurality of satellites 5 disposed at the side of the rocket adapter 11, a sleeve device is disposed between each satellite 5 and the rocket adapter 11, and the sleeve device is disposed vertically at the side of the rocket adapter 11, the sleeve device has a separation spring 10 inside, and each satellite (5) is connected to the sleeve device through a corresponding satellite adapter (1).

The satellite-rocket separation method comprises the following steps:

in the first step, one attitude control nozzle 12 is respectively arranged at the positions adjacent to two sides of the rocket final stage 13, and the two attitude control nozzles 12 are symmetrically arranged about the longitudinal axis of the rocket final stage 13.

And secondly, in an initial state, the satellite 5 is connected with the rocket adapter 11 through a separation bolt, the separation spring 10 is in a compressed state, and the attitude control nozzle 12 is in a closed state.

Thirdly, when a satellite 5 receives a separation instruction, the satellite 5 is unlocked, the corresponding satellite adapter 1 is disconnected from the rocket adapter 11, the separation spring 10 is bounced off from the compressed state, and the satellite adapter 1 and the satellite 5 move together in the direction away from the rocket adapter 11 under the action of elastic force.

Meanwhile, the attitude control spray pipe 12 is opened and works, and sprays air towards the tail end of the rocket final stage 13, so that reverse thrust can be formed on the rocket final stage 13, and under the action of the reverse thrust, the rocket final stage 13 drives the rocket adapter 11 to actively keep away from the satellite 5, so that the distances between the satellites and the arrows and between the satellites are increased, collision is avoided, and the safety of separating the satellites and the arrows is improved.

And fourthly, stopping rebounding when the separation spring 10 bounces to a preset position, and at the moment, flying out the satellite 5 and the satellite adapter 1 together to complete separation. At the same time, both attitude control jets 12 are closed.

And fifthly, after the first satellite 5 finishes the separation, the other satellites finish the separation according to the steps from the second step to the fourth step in sequence according to a preset time sequence.

Specifically, the preset position in the fourth step of the above steps may be specifically set according to actual conditions.

In addition, for the above steps, after each satellite 5 is separated, the attitude control nozzles 12 are closed, and after the next satellite 5 receives a separation instruction and unlocks, the two attitude control nozzles 12 are opened again to work, and so on until all satellites 5 are separated.

Further, the attitude control nozzle 12 jets air toward the end of the rocket final stage 13, and in the present embodiment, the attitude control nozzle 12 jets air toward the end of the rocket final stage 13 by a preset angle, which is an included angle between the longitudinal axis of the attitude control nozzle 12 and the longitudinal axis of the rocket final stage 13, and the included angle is preferably 20 °. The angle can avoid the plume of the attitude control spray pipe from polluting the satellite, and simultaneously, the thrust of the attitude control spray pipe is utilized to the maximum extent.

In other embodiments, the attitude control nozzles 12 can also jet air vertically towards the end of the rocket final stage 13, or the attitude control nozzles 12 jet air outwards towards the end of the rocket final stage 13 at other angles of 0-20 degrees.

Further, above-mentioned sleeve device includes push rod 6, and push rod 6 is provided with bulb support 4 in the one end of being connected with satellite adapter 1, and the top of bulb support 4 is provided with bulb 3, installs the bulb groove 2 that corresponds with bulb 3 on satellite adapter 1. The size of the ball head groove 2 is matched with that of the ball head 3, the ball head groove 2 and the ball head 3 together restrain the satellite 5, the satellite 5 can be prevented from sliding to a certain extent, and therefore the angular speed of separation of the satellite 5 is restrained.

In the second step and the third step, the satellite 5 is not separated, and the ball head 3 is butted with the ball head groove 2, namely the ball head 3 is positioned in the ball head groove 2; in the fourth step, the satellite 5 is separated, and the ball head 3 is separated from the ball head groove 2, as shown in fig. 2.

In this embodiment, the ball 3 is spherical, and the corresponding ball groove 2 is hemispherical, in other embodiments, the ball 3 may be hemispherical or in other shapes, and the shape of the corresponding ball groove 2 also corresponds to that, so as to ensure that the satellite 5 does not slide.

The application also provides an embodiment of a satellite and rocket system, which can realize satellite and rocket separation by adopting the method embodiment, and the satellite and rocket system comprises a rocket final stage 13, a satellite 5 and a sleeve device.

Wherein, the end of rocket final stage 13 is equipped with rocket adapter 11, and the position that rocket final stage 13 is close to both sides sets up an attitude control spray tube 12 respectively, and in this embodiment, rocket adapter 11 sets up the position that the end of rocket final stage 13 is close to the side, and two attitude control spray tubes 12 are the longitudinal axis symmetrical arrangement about rocket final stage 13.

The number of satellites 5 is plural, and one satellite adapter 1 is connected to each satellite 5, and is disposed in turn on the side of the rocket adapter 11.

The number of the sleeve devices is multiple, two sleeve devices are arranged between each satellite adapter (1) and the rocket adapter 11, the sleeve devices are perpendicular to the side face of the rocket adapter 11, and a separation spring 10 is arranged inside each sleeve device.

In the initial state, that is, before the satellite 5 receives the detach command, the satellite 5 and the rocket adapter 11 are connected by the detach bolt. At this time, the separation spring 10 is in a compressed state, and the attitude control nozzle 12 is in a closed state. When a satellite 5 receives a separation command from the control system, the satellite adapter 1 corresponding to the satellite is disconnected from the rocket adapter 11, the separation spring 10 rebounds, and the satellite adapter 1 moves together with the satellite 5 in a direction away from the rocket adapter 11. Meanwhile, the two attitude control nozzles 12 jet air towards the tail end of the rocket final stage 13, and the thrust generated on the rocket final stage 13 enables the rocket final stage 13 to actively move away from the satellite 5 together with the rocket adapter 11 and other satellites, so that the safety distance between the satellites and between the satellites is increased.

Further, in the present embodiment, the air outlet of the attitude control nozzle 12 is outwardly deviated by a preset angle, and the preset angle is preferably 20 °. In other embodiments, the jet ports of the attitude control nozzle 12 may be directed vertically toward the end of the rocket final stage 13.

Further, the sleeve device comprises a sleeve 7 and a push rod 6 arranged inside the sleeve 7 besides the separation spring 10, one end of the sleeve 7 is fixedly connected with the side surface of the rocket adapter 11, and the other end of the sleeve 7 abuts against the satellite adapter 1. During the detachment of the satellite 5, the sleeve 7 is always connected to the rocket adapter 11. One end of the separation spring 10 is connected to the rocket adapter 11, and the other end thereof is connected to one end of the push rod 6, and the other end of the push rod 6 is connected to the satellite adapter 1. During the separation of the satellite 5, the separation spring 10 can push the push rod 6 to further push the satellite 5 to move.

Specifically, a ball head support 4 is further arranged at one end, connected with the satellite adapter 1, of the push rod 6, a ball head 3 is mounted at the end of the ball head support 4, and a ball head groove 2 matched with the size of the ball head 3 is formed in the corresponding position of the satellite adapter 1. In other embodiments, the ball head 3 may be directly mounted to the end of the push rod 6 connected to the satellite adapter 1.

Before the satellite 5 is separated, the ball head 3 is positioned in the ball head groove 2; after the satellite 5 is separated, the ball 3 is separated from the ball groove 2, as shown in fig. 2.

Further, a part of the side wall of the sleeve 7, which is close to the rocket adapter 11, is provided with a strip-shaped groove 9, and one end of the push rod 6, which is connected with the separation spring 10, is provided with a push rod limiting pile 8. During initial state, the spacing stake 8 of push rod stretches out bar groove 9, does not take place to remove. After the satellite 5 is unlocked, under the elastic force action of the separation spring 10, the push rod limiting pile 8 on the push rod 6 moves along the strip-shaped groove 9, when the push rod 6 moves to the top end of the strip-shaped groove 9, the push rod 6 stops moving, and the separation spring 10 stops rebounding.

The length of the strip-shaped groove 9 can be specifically set according to actual conditions.

Further, the stiffness coefficient of the separation spring 10 inside each sleeve device is less than 1N/mm, so that the push rod 6 is extended at a slow speed. And the stiffness coefficients of all the separation springs 10 are the same, so that the stress of the satellite can be ensured to be uniform to a certain extent.

In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.