1. An interstage separation device suitable for rocket cold separation, which is characterized by comprising a separation side thrust device (1) and a fuel gas generator (2) which are both arranged on a rocket substage, wherein the separation side thrust device (1) comprises an axial impulse generation mechanism (3) and a lateral impulse generation mechanism (4), and the fuel gas generator (2) and the lateral impulse generation mechanism (4) are both connected with the axial impulse generation mechanism (3);

the gas generator (2) is used for injecting gas into the axial impulse generating mechanism (3) and pressurizing the gas in the axial impulse generating mechanism (3), and the axial impulse generating mechanism (3) is used for converting internal energy of internal high-pressure gas into mechanical energy so as to enable the rocket stage to obtain axial impulse separated from the rocket parent stage;

the side thrust impulse generating mechanism is used for ejecting gas in the axial impulse generating mechanism (3) from the side surface of the rocket secondary stage after the rocket secondary stage is separated from the rocket primary stage, so that the rocket secondary stage obtains the side thrust impulse deviating from the flight orbit of the rocket primary stage.

2. An interstage separation device suitable for rocket cold separation according to claim 1, wherein said axial momentum generating mechanism (3) comprises an air bag (301) and an integrated pipeline (302), said air bag (301) is folded and extended along the axial direction of said rocket substage and said rocket substage, said air bag (301) is embedded and installed at the front end of said rocket substage facing said rocket substage, and said air bag (301) is connected with said gas generator (2) through said integrated pipeline (302).

3. An interstage separation device suitable for rocket cold separation according to claim 2, wherein said air bag (301) has a plurality of air inlets, a plurality of said air inlets are distributed at equal intervals along the circumference of said air bag (301), and said air bag (301) is connected and communicated with said integrated pipeline (302) through a plurality of said air inlets.

4. An interstage separation device suitable for rocket cold separation according to claim 2, wherein said integrated circuit (302) comprises a plurality of aeration pipes (3021), a plurality of said air inlets communicating with the output end of said gas generator (2) through a plurality of said aeration pipes (3021) connected in a one-to-one correspondence.

5. An interstage separation device suitable for rocket cold separation according to claim 2, wherein said lateral momentum generating means (4) comprises a side thrust electro-explosive valve (401) and a side thrust jet pipe (402), said side thrust jet pipe (402) is mounted on the side wall of the rocket substage, said side thrust jet pipe (402) is communicated with said air bag (301) through said side thrust electro-explosive valve (401).

6. An interstage separation device suitable for rocket cold separation as claimed in claim 5, wherein said integrated pipeline (302) further comprises an annular communicating pipe (3022), both ends of said annular communicating pipe (3022) are butted and communicated with each other, and a plurality of said gas charging pipes (3021) are connected and communicated with said gas generator (2) through the annular communicating pipe (3022).

7. An interstage separation device suitable for rocket cold separation according to claim 5, characterized in that said gas generator (2) is provided in plurality, a plurality of said gas generators (2) being in communication with said gas filling pipe (3021) through said annular communicating pipe (3022).

8. An interstage separation device suitable for rocket cold separation as claimed in claim 6, wherein said side thrust electric explosion valve (401) is mounted on said annular communicating pipe (3022), and said side thrust nozzle (402) is communicated with said air bag (301) through said side thrust electric explosion valve (401), said annular communicating pipe (3022) and said inflating pipe (3021) in turn.

9. An interstage separation device suitable for rocket cold separation according to claim 5, further comprising a sleeve (6) internally provided with a support (5), wherein said air bag (301) is folded in said sleeve (6), and said air bag (301) is supported and mounted on said support (5), and said sleeve (6) is embedded and mounted at the front end of said rocket substage;

pass through in sleeve (6) support (5) separate into install the direction chamber (7) of gasbag (301), and install gas generator (2) annular closed pipe (3022) with installation cavity (8) of gas tube (3021), run through on support (5) and seted up a plurality of through-holes (9), through-hole (9) internal fixation is pegged graft and is had the intercommunication gas tube (3021) with registration arm (10) of air inlet.

10. An interstage separation device suitable for rocket cold separation according to claim 9, wherein said positioning tube (10) is mounted on the inner wall of said sleeve (6) by means of a bracket (11) so that said positioning tube (10) is fixedly inserted in said through hole (9).

Background

In the flight process of the multi-stage rocket, after the operation of the first-stage engine is finished, the part which is finished is required to be separated, and the process of the next-stage continuous flight is realized, namely the interstage separation. The separation mode can be divided into cold separation and hot separation according to the ignition time of the next-stage engine. The thermal separation process generates separation power through the work of the next-stage engine, other separation energy sources are not needed, and the problem of pursuing collision of the separation sublevel on the next-stage arrow body is not needed to be considered. The cold separation process realizes the separation movement of the next stage and the separation sub-stage through special separation energy, and the separation sub-stage is controlled to generate deviation movement after separation so as to avoid the pursuit collision with the next stage rocket.

The traditional interstage cold separation mainly realizes the separation of the sublevel and the rocket body through a forward thrust small rocket, a backward thrust small rocket, an initiating thrust device and a mechanical spring, wherein jet flow generated by the backward thrust rocket can cause certain pollution to the next stage, and the interstage cold separation cannot be applied to occasions with high requirements on environment cleanliness. The thrust peak value of the fire pushing and punching device is large, the requirement on the rigidity of the structure is high, the efficiency of the mechanical spring is low, and the structure is not beneficial to weight reduction. In addition, due to the need of avoiding pursuit collision, separate energy sources and sublevel deviation energy sources need to be arranged independently, the complexity of the system is increased, and the structural efficiency and the reliability are reduced.

Disclosure of Invention

The invention aims to provide an interstage separation device suitable for rocket cold separation, which aims to solve the technical problem that the structural efficiency and reliability of an interstage separation system are reduced due to the fact that separation energy sources and substage deviation energy sources need to be arranged independently in the prior art.

In order to solve the technical problems, the invention specifically provides the following technical scheme:

an interstage separation device suitable for rocket cold separation comprises a separation side thrust device and a fuel gas generator which are both arranged on a rocket sublevel, wherein the separation side thrust device comprises an axial impulse generation mechanism and a lateral impulse generation mechanism, and the fuel gas generator and the lateral impulse generation mechanism are both connected with the axial impulse generation mechanism;

the fuel gas generator is used for injecting fuel gas into the axial impulse generating mechanism and pressurizing the fuel gas in the axial impulse generating mechanism, and the axial impulse generating mechanism is used for converting internal energy of internal high-pressure fuel gas into mechanical energy so as to enable the rocket secondary stage to obtain axial impulse separated from the rocket primary stage;

the side thrust impulse generating mechanism is used for ejecting gas in the axial impulse generating mechanism from the side surface of the rocket secondary stage after the rocket secondary stage is separated from the rocket primary stage, so that the rocket secondary stage obtains side thrust impulse deviating from the flight orbit of the rocket primary stage.

As a preferable aspect of the present invention, the axial impulse generating mechanism includes an air bag and an integrated pipeline, the air bag is folded and extended in an axial direction of the rocket secondary stage and the rocket primary stage, the air bag is embedded in a front end of the rocket secondary stage facing the rocket primary stage, and the air bag is connected to the gas generator through the integrated pipeline.

In a preferred embodiment of the present invention, the airbag has a plurality of air inlets, the plurality of air inlets are distributed at equal intervals in a circumferential direction of the airbag, and the airbag is connected to and communicated with the integrated pipeline through the plurality of air inlets.

As a preferable scheme of the present invention, the integrated pipeline includes a plurality of gas-filled pipes, and the plurality of gas inlets are communicated with the output end of the gas generator through the plurality of gas-filled pipes connected in a one-to-one correspondence.

As a preferable scheme of the present invention, the lateral impulse generating mechanism includes a lateral thrust electro-explosive valve and a lateral thrust jet pipe, the lateral thrust jet pipe is installed on a side wall of the rocket stage, and the lateral thrust jet pipe is communicated with the airbag through the lateral thrust electro-explosive valve.

As a preferable scheme of the invention, the integrated pipeline further comprises an annular communicating pipe, two ends of the annular communicating pipe are mutually butted and communicated, and the plurality of gas filling pipes are connected and communicated with the gas generator through the annular communicating pipe.

As a preferable scheme of the present invention, the gas generator is provided in plurality, and the gas generator is communicated with the gas filling pipe through the annular communicating pipe.

As a preferable scheme of the present invention, the side-push electric explosion valve is installed on the annular communicating pipe, and the side-push nozzle is communicated with the airbag through the side-push electric explosion valve, the annular communicating pipe and the inflation pipe in sequence.

As a preferable scheme of the invention, the rocket further comprises a sleeve with a support arranged inside, the air bag is folded in the sleeve, the air bag support is arranged on the support, and the sleeve is embedded in the front end of the rocket substage;

the gas generator, the annular communicating pipe and the mounting cavity of the gas charging pipe are arranged in the sleeve through the support, a plurality of through holes are formed in the support in a penetrating mode, and positioning pipes communicated with the gas charging pipe and the gas inlet are fixedly inserted in the through holes.

As a preferable scheme of the present invention, the positioning tube is mounted on the inner wall of the sleeve through a bracket, so that the positioning tube is fixedly inserted into the through hole.

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

the invention inputs fuel gas into the axial impulse generating mechanism through the fuel gas generator and boosts the pressure, the axial impulse generating mechanism pushes the rocket primary stage to be separated from the rocket secondary stage in a mode of converting the internal energy of high-pressure fuel gas into mechanical energy, and the side thrust impulse generating mechanism enables the rocket secondary stage to obtain the side thrust impulse deviating from the flight orbit where the rocket primary stage is located in a mode of ejecting the fuel gas in the axial impulse generating mechanism from the side surface of the rocket secondary stage and igniting the fuel gas, namely the fuel gas output by the fuel gas generator is simultaneously used as the separation energy of the axial impulse generating mechanism and the secondary deviation energy of the side thrust impulse generating mechanism, thereby reducing the complexity of a rocket interstage separation system and having the advantages of improving the structural efficiency and the interstage separation reliability.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.

FIG. 1 is a schematic overall structure diagram of an embodiment of the present invention;

FIG. 2 is a schematic structural diagram of a separating side-pushing device according to an embodiment of the present invention;

FIG. 3 is a schematic structural diagram of an annular communicating pipe according to an embodiment of the present invention;

FIG. 4 is a schematic structural diagram of a support according to an embodiment of the present invention;

fig. 5 is a schematic structural diagram of a positioning tube according to an embodiment of the present invention.

The reference numerals in the drawings denote the following, respectively:

1-separating the side pushing device; 2-a gas generator; 3-an axial impulse generating mechanism; 4-a lateral impulse generating mechanism; 5-support; 6-a sleeve; 7-a guide cavity; 8-mounting a cavity; 9-a through hole; 10-a positioning tube; 11-a scaffold;

301-an air bag; 302-integrated circuit;

3021-inflation tube; 3022-ring-shaped communicating pipe;

401-side push electric explosion valve; 402-side thrust nozzle;

12-rocket parent stage; 13-rocket substage.

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 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 invention.

As shown in fig. 1 to 5, the invention provides an interstage separation device suitable for rocket cold separation, which comprises a separation side thrust device 1 and a gas generator 2 which are both arranged on a rocket substage 13, wherein the separation side thrust device 1 comprises an axial impulse generation mechanism 3 and a lateral impulse generation mechanism 4, and the gas generator 2 and the lateral impulse generation mechanism 4 are both connected with the axial impulse generation mechanism 3;

the fuel gas generator 2 is used for injecting fuel gas into the axial impulse generating mechanism 3 and pressurizing the fuel gas in the axial impulse generating mechanism 3, and the axial impulse generating mechanism 3 is used for converting internal energy of internal high-pressure fuel gas into mechanical energy so as to enable the rocket secondary stage 13 to obtain axial impulse separated from the rocket primary stage 12;

the side thrust impulse generating mechanism is used for ejecting the fuel gas in the axial impulse generating mechanism 3 from the side surface of the rocket secondary stage 13 after the rocket secondary stage 13 is separated from the rocket primary stage 12, so that the rocket secondary stage 13 obtains the side thrust impulse deviating from the flight orbit of the rocket primary stage 12.

In the embodiment of the invention, the gas generator 2 inputs gas into the axial impulse generating mechanism 3 and boosts the pressure, and the axial impulse generating mechanism 3 pushes the rocket primary stage 12 to be separated from the rocket secondary stage 13 in a mode of converting the internal energy of high-pressure gas into mechanical energy. And the side thrust impulse generating mechanism enables the rocket secondary stage 13 to obtain the side thrust impulse by ejecting gas in the axial impulse generating mechanism 3 from the side surface of the rocket secondary stage 13 and igniting the gas, so that the rocket secondary stage 13 deviates from the flight orbit of the rocket primary stage 12, and the purpose of preventing the rocket secondary stage 13 from rear-ending the rocket primary stage 12 is achieved. Namely, the gas output by the gas generator 2 is simultaneously used as the separation energy of the axial impulse generating mechanism 3 and the sublevel 13 deviation energy of the side thrust impulse generating mechanism, thereby reducing the complexity of the rocket interstage separation system, being beneficial to reducing the weight and the manufacturing cost of the rocket interstage separation system, and having the advantages of improving the structural efficiency and the interstage separation reliability.

The axial impulse generating mechanism 3 comprises an air bag 301 and an integrated pipeline 302, the air bag 301 is folded and extended along the axial direction of the rocket secondary stage 13 and the rocket primary stage 12, the air bag 301 is embedded and installed at the front end of the rocket secondary stage 13 facing the rocket primary stage 12, and the air bag 301 is connected with the gas generator 2 through the integrated pipeline 302.

On one hand, the flexible air bag 301 pushes the rocket primary stage 12 to be separated from the rocket secondary stage 13 after being expanded, the separation mode is soft, and damage to rocket bodies of the rocket primary stage 12 and the rocket secondary stage 13 is avoided. On the other hand, compared with devices for realizing rocket stage cold separation such as a reverse thrust small rocket, an initiating explosive thrust device, a mechanical spring air bag 301 and the like, the air bag 301 not only has the advantages of light structure and low cost, but also can ensure that the air bag 301 is extruded by negative pressure in space after completing the stage separation of the rocket primary stage 12 and the rocket secondary stage 13, so that the gas in the air bag 301 can be directly supplied to a side thrust impulse generation mechanism without an additional gas transmission mechanism for conveying. The air bag 301 can not only separate the rocket primary stage 12 and the rocket secondary stage 13 softly, but also stably convey the stored fuel gas to the side thrust impulse generating mechanism under the condition of no external power intervention by utilizing the vacuum environment of the outer space, so that the axial impulse generating mechanism 3 (an interstage separation unit) of the interstage separation system and the side thrust impulse generating mechanism (a secondary deviation unit) can realize simple and efficient butt joint and matching.

It is further optimized in the above embodiment that the airbag 301 has a plurality of air inlets, the plurality of air inlets are distributed at equal intervals along the circumferential direction of the airbag 301, and the airbag 301 is connected and communicated with the integrated pipeline 302 through the plurality of air inlets.

The shape of the air bag 301 is generally cylindrical, and the plurality of air inlets distributed at equal intervals in the circumferential direction are arranged, so that on one hand, the speed of gas input into the air bag 301 is improved, and therefore when the rocket secondary stage 13 and the rocket primary stage 12 need to be separated, sufficient gas can be timely filled into the air bag 301. On the other hand, the air inflow in each direction in the air bag 301 tends to be consistent, so that the air pressure in each circumferential region in the air bag 301 tends to be consistent, the air bag 301 can be conveniently and stably extended in the axial direction, and the deviation of the rocket secondary stage 13 and the rocket primary stage 12 caused by the inclination in the extension process of the air bag 301 due to the stress state is prevented, so that negative effects are caused on the precise control of the flight tracks of the rocket primary stage 12 and the rocket secondary stage 13, and even the rocket primary stage 12 and the rocket secondary stage 13 collide after separation.

Accordingly, the integrated circuit 302 includes a plurality of charging pipes 3021, and a plurality of gas inlets are communicated with the output end of the gas generator 2 through the plurality of charging pipes 3021 connected in a one-to-one correspondence.

The lateral impulse generating mechanism 4 comprises a lateral thrust electro-explosive valve 401 and a lateral thrust jet pipe 402, the lateral thrust jet pipe 402 is installed on the side wall of the rocket stage 13, and the lateral thrust jet pipe 402 is communicated with the air bag 301 through the lateral thrust electro-explosive valve 401.

After the rocket primary stage 12 is separated from the rocket secondary stage 13, the control side thrust electric explosion valve 401 is ignited and switched to a conducting state, so that the gas in the air bag 301 is ignited when passing through the electric explosion valve, and flames are sprayed outwards through the side thrust jet pipe 402, so that the rocket secondary stage 13 obtains side thrust impulse.

As further optimized in the above embodiment, the integrated pipeline 302 further includes an annular communicating pipe 3022, two ends of the annular communicating pipe 3022 are butted and communicated with each other, and a plurality of gas charging pipes 3021 are connected and communicated with the gasifier 2 through the annular communicating pipe 3022.

According to the characteristic of fluid flowing in the direction with low resistance, the annular communicating pipe 3022 and the plurality of gas-filled pipes 3021 form a distribution valve-like structure, that is, when the gas generator 2 inputs gas into the annular communicating pipe 3022, the gas-filled pipe 3021 near the connection between the gas generator 2 and the annular communicating pipe 3022 is preferentially filled with gas, but when one or more gas-filled pipes 3021 are preferentially filled with gas, the gas pressure in the gas-filled pipe 3021 that is preferentially filled with gas is increased under the resistance of the folded airbag 301 against expansion, so that the gas in the annular communicating pipe is supplied to the gas-filled pipe 3021 that is not filled with gas or is filled with gas only in a small amount until the gas pressures in the gas-filled pipes 3021 are consistent or nearly consistent. The problem that the gas generator 2 is limited and inconvenient to install and the problem that the stability of the gas bag 301 supported on the rocket stage 13 is negatively affected due to the fact that the gas generator is limited and inconvenient because the gas generator is required to be arranged on the axis of the connecting line of the gas tubes 3021 and the axis of the gas bag 301 because the gas tubes 3021 are not consistent in length due to the fact that the gas tubes 3021 are directly connected with the gas generator 2 is solved. Therefore, the cooperation of the plurality of inflation tubes 3021 and the annular communicating tube 3022 not only has the advantage of facilitating the flexible installation of the gas generator 2, but also facilitates the stable support of the airbag 301, and provides a foundation for the stable extension of the airbag 301.

In addition, a plurality of gas generators 2 are arranged, and the plurality of gas generators 2 are communicated with the inflation pipe 3021 through the annular communicating pipe 3022, so that the condition that the interstage separation device cannot work due to the failure of a certain gas generator 2 is avoided, meanwhile, the rate of inputting gas into the air bag 301 is increased, and the air bag 301 can be further stretched in time when the rocket secondary stage 13 and the rocket primary stage 12 need to be separated. And preferably, the plurality of gas-filling pipes 3021 are equally spaced from the adjacent gas generator 2 to the junction of the annular communicating pipe 3022 to further ensure that the gas flow rates of the respective gas inlets of the air bag 301 are uniform.

Based on the annular linkage pipe, the communication mode of the electric explosion valve and the air bag 301 is optimized, specifically, the side-push electric explosion valve 401 is installed on the annular communication pipe 3022, and the side-push nozzle 402 is communicated with the air bag 301 through the side-push electric explosion valve 401, the annular communication pipe 3022 and the inflation pipe 3021 in sequence. The fixedly arranged electric explosion valve is prevented from negatively influencing the folding and the stretching of the air bag 301, so that the side of factors influencing the normal stretching of the air bag 301 is further eliminated.

In addition, the embodiment of the invention also comprises a sleeve 6 internally provided with a support 5, the air bag 301 is folded in the sleeve 6, the air bag 301 is supported and arranged on the support 5, and the sleeve 6 is embedded and arranged at the front end of the rocket stage 13. The sleeve 6 is internally divided into a guide cavity 7 provided with an air bag 301 and an installation cavity 8 provided with a fuel gas generator 2, an annular communicating pipe 3022 and an inflation pipe 3021 by a support 5, a plurality of through holes 9 are formed in the support 5 in a penetrating manner, and a positioning pipe 10 communicated with the inflation pipe 3021 and an air inlet is fixedly inserted in each through hole 9.

The sleeve 6 serves to axially guide and radially limit the airbag 301, and the root of the airbag 301, which is supported on the support 5 and surrounded by the sleeve 6, facilitates stable extension of the airbag 301 out of the front end of the guide chamber 7 when the airbag 301 is extended. The support 5 has the function of stably supporting the air bag 301 by separating the space in the sleeve 6, and meanwhile, the components such as the gas generator 2, the reversing communication pipeline, the inflation pipe 3021 and the like can be arranged below the air bag 301, so that the concentration and the arrangement of each component of the interstage separation device are facilitated.

The fixed positioning tube 10 is used for fixing the air bag 301 by connecting the air inlet and the fixed positioning tube 10, and the air inlet of the air bag 301 is prevented from being directly connected with the inflation tube 3021, so that the bottom of the air bag 301 is prevented from being swelled under the action of internal air pressure to drive the inflation tube 3021 to shake when the air bag 301 is expanded, and the hidden danger that the joint of the inflation tube 3021 and the annular communicating tube 3022 is broken due to the unreasonable connection mode of the inflation tube 3021 and the air bag 301 is eliminated.

Preferably, the positioning tube 10 is mounted on the inner wall of the sleeve 6 through the bracket 11, so that the positioning tube 10 is fixedly inserted into the through hole 9, and the situation that the positioning tube 10 moves axially due to poor axial positioning effect in the insertion manner is avoided.

The above embodiments are only exemplary embodiments of the present application, and are not intended to limit the present application, and the protection scope of the present application is defined by the claims. Various modifications and equivalents may be made by those skilled in the art within the spirit and scope of the present application and such modifications and equivalents should also be considered to be within the scope of the present application.