阅读说明：本技术 一种级间段气动保形的固体火箭及分离方法 (Stage section pneumatic shape-preserving solid rocket and separation method ) 是由 杨毅强 史晓宁 李新宇 李秦峰 于 2021-09-18 设计创作，主要内容包括：本发明公开了一种级间段气动保形的固体火箭及分离方法,包括多个固体动力装置,相邻固体动力装置之间通过级间段连接,并在固体动力装置和级间段外形呈火箭外形体,在火箭外形体表面设置有保形装置,保形装置包括气动合力差发生装置、连接解锁装置以及至少两个柱状面；连接解锁装置用于实现柱状面与火箭外形体之间的连接和分离；气动合力差发生装置的第一舵面和第二舵面使柱状面两端之间产生气动合力差,连接解锁装置在柱状面的端部存在气动合力差的状态下分离柱状面和火箭外形体之间的连接。本发明在火箭飞至最大动压点后,通过气动合力差发生装置和连接解锁装置控制柱状面和火箭外形体的分离动作,将火箭外形体自身结构对运力的影响降至最低。(The invention discloses a stage section pneumatic shape-preserving solid rocket and a separation method, wherein the separation method comprises a plurality of solid power devices, adjacent solid power devices are connected through a stage section, the shapes of the solid power devices and the stage section are rocket outer bodies, a shape-preserving device is arranged on the surface of each rocket outer body, and the shape-preserving device comprises a pneumatic resultant force difference generating device, a connecting unlocking device and at least two columnar surfaces; the connecting and unlocking device is used for realizing the connection and the separation between the columnar surface and the rocket outer body; the first control surface and the second control surface of the aerodynamic resultant force difference generating device enable aerodynamic resultant force difference to be generated between two ends of the columnar surface, and the connecting and unlocking device separates the columnar surface from the rocket outer body under the condition that the aerodynamic resultant force difference exists at the end part of the columnar surface. After the rocket flies to the maximum dynamic pressure point, the separation action of the columnar surface and the rocket outer body is controlled through the pneumatic resultant force difference generating device and the connecting unlocking device, so that the influence of the structure of the rocket outer body on the transport capacity is reduced to the minimum.)

1. A stage section pneumatic shape-preserving solid rocket is characterized by comprising a plurality of solid power devices, wherein the adjacent solid power devices are connected through a stage section, the shapes of the solid power devices and the stage section are rocket outer bodies, a shape-preserving device is arranged on the surface of each rocket outer body, the shape-preserving device comprises a pneumatic power difference generating device (1), a connecting and unlocking device (2) and at least two columnar surfaces (3), the columnar surfaces (3) are connected to the rocket outer bodies through the connecting and unlocking devices (2), and the pneumatic power difference generating device (1) is arranged on the columnar surfaces (3);

at least two columnar surfaces (3) are connected to form a hollow columnar structure, the hollow columnar structure is installed on the rocket outer body, and the hollow columnar structure is used for keeping the appearance of two adjacent stages of the rocket outer body consistent;

the aerodynamic resultant force difference generating device (1) comprises a first control surface (11) and a second control surface (12), wherein the first control surface (11) is arranged at the end part, close to the head part of the rocket outer body, of the columnar surface (3), and the second control surface (12) is arranged at the end part, close to the tail part of the rocket outer body, of the columnar surface (3);

the first control surface (11), the second control surface (12) and the cylindrical surface (3) form an included angle therebetween, and the first control surface (11) and the second control surface (12) are different in the included angle to generate a difference in aerodynamic force, so that the cylindrical surface (3) is separated from the rocket outer body under the unlocking action of the connecting and unlocking device (2).

2. The pneumatic conformal solid rocket according to claim 1, wherein the first control surface (11) and the second control surface (12) each comprise a control surface (4) and a servo action component (5), one end of the control surface (4) is connected with the columnar surface (3) through a hinge shaft (6), the middle position of the back side surface of the control surface (4) is connected with the columnar surface (3) through the servo action component (5), the servo action component (5) is used for driving the control surface (4) to rotate by taking the hinge shaft (6) as a rotation axis, so that the control surface (4) and the surface of the columnar surface (3) form the included angle, and the included angle faces to the incoming flow direction of the rocket outer body in flight.

3. A stage section aerodynamic conformal solid rocket according to claim 2, wherein the control surface (4) of the first control surface (11) forms an included angle a with the surface of the cylindrical surface (3) under the driving of a servo action assembly (5);

the control surface (4) of the second control surface (12) forms an included angle B with the surface of the cylindrical surface (3) under the driving of a servo action assembly (5);

the included angle A enables the control surface (4) of the first control surface (11) to bear the maximum normal force vertical to the rocket outer body direction when the rocket outer body reaches the set flight condition;

the included angle B is smaller than the included angle A.

4. A stage-interval pneumatic conformal solid rocket according to claim 3, wherein the servo action assembly (5) comprises a servo motor (51), a controller, a power supply, and a support rod (52) fixedly connected to an output end of the servo motor, an end of the support rod (52) far away from the servo motor (51) is connected with a back side surface in the control surface (4);

the control surface (4) is attached to the surface of the columnar surface (3) when the controller does not generate a control signal of the servo motor (51) in an initial state; the power supply is used for supplying power to the servo motor and the controller.

5. A staged pneumatic conformal solid rocket according to claim 1, wherein said connection unlocking means (2) comprises a connection block (21) fixedly connected to said cylindrical surface (3), said connection block (21) being connected to the rocket outer body by means of explosive bolts (22).

6. A method for separating a pneumatic conformal solid rocket in a stage section is characterized by comprising the following steps:

step 100, rocket appearance shape keeping: a hollow columnar structure formed by connecting a plurality of columnar surfaces is sleeved on the rocket outer body, and the connection between the columnar surfaces and the rocket outer body is realized through a connecting unlocking device, so that the appearances of two adjacent stages of the rocket outer body are kept consistent, and the shape preservation of the appearance of the rocket outer body is completed;

step 200, constructing a pneumatic resultant force difference generation mechanism at the end part of the columnar surface: the end part of the columnar surface close to the head of the rocket outer body and the end part surface of the columnar surface close to the tail of the rocket outer body are provided with control surfaces and servo action components for controlling included angles between the control surfaces and the columnar surface, the included angles between the control surfaces and the columnar surface face the incoming flow direction of the rocket outer body, the included angles between the two control surfaces and the columnar surface are controlled to be different through the servo action components, and the two end parts of the columnar surface generate poor aerodynamic force under the action of airflow in the flying process of the rocket outer body;

step 300, setting the separation condition and state of the columnar surface and the rocket outer body: when the rocket outer body takes off and the rocket outer body reaches the flight condition of transonic speed or maximum dynamic pressure point, the two servo action assemblies receive the trigger control signal to work, so that the included angle between the control surface close to the head of the rocket outer body and the columnar surface is larger than the included angle between the control surface close to the tail of the rocket outer body and the columnar surface, and a separation state is provided for the separation between the columnar surface and the rocket outer body;

step 400, separating the columnar surface from the rocket outer body: the connecting unlocking device receives the detonation control signal to explode the explosive bolt, and the columnar surface is disconnected with the rocket outer shape body under the action of the separation state.

7. The method of claim 6, wherein in step 300, the aerodynamic resultant force difference generating device is subjected to an axial force along the rocket outer body and a normal force perpendicular to the rocket outer body direction under a flight condition that the rocket outer body reaches a transonic speed or a maximum dynamic pressure point, and the aerodynamic resultant force difference generating device makes one end of the columnar surface near the top of the rocket outer body subjected to the normal force perpendicular to the rocket outer body direction larger than the normal force perpendicular to the rocket outer body direction at the other end of the columnar surface.

8. The method for separating a staged pneumatic conformal solid rocket as recited in claim 7, wherein the unlocking device is connected to receive the detonation control signal to explode the explosive bolt after the servo-actuated component receives the triggering control signal, and the time interval between the triggering control signal and the detonation control signal is not more than 0.5 seconds.

9. The method for separating the pneumatically conformal solid rocket in the stage section according to claim 7, wherein the calculation formula of the included angle between the control surface and the cylindrical surface close to the rocket outer body head is as follows: define an included angle of，

，

，

，

Wherein the content of the first and second substances,the upper surface pressure of the control surface is shown,the lower surface pressure of the control surface is shown,the pressure difference between the upper surface and the lower surface of the control surface is shown, F represents the resultant pneumatic force under the condition of incoming flow, S represents the stressed area of the control surface,the maximum normal force of the control surface perpendicular to the rocket outer body direction is shown.

10. The method for separating a pneumatically conformal solid rocket according to claim 9, wherein the method for determining the angle between the control surface near the rocket outer body head and the cylindrical surface, under the condition of the incoming flow, the maximum normal force applied to the control surface comprises:

step 301, determining incoming flow states of the rocket outer body and the columnar surface when separation is needed, and obtaining incoming flow Mach number, pressure, temperature, incoming flow density and incoming flow speed of the rocket outer body;

step 302, calculating the pressure of the lower surface of the control surface, which is in contact with the incoming flow in the incoming flow state:

，

wherein the content of the first and second substances,is the total pressure of the mixture,、、respectively the pressure, density and speed of the incoming flow, the incoming flow flows to the lower surface of the control surface to be stopped,namely the pressure intensity of the lower surface of the control surface;

step 303, calculating the maximum reverse force of the control surface in the direction vertical to the rocket outer body according to an included angle calculation formula between the control surface and the columnar surface;

step 304, the included angles between the different control surfaces and the cylindrical surface are given, and the step 301 and the step 303 are repeated to determine the optimal included angle between the control surface and the cylindrical surface.

Technical Field

The invention relates to the technical field of material stacking separation, in particular to a stage-section pneumatic shape-preserving solid rocket and a separation method.

Background

The solid rocket is formed by connecting solid power of each stage in a stage section. At present, the selection of the sub-stage power system of the large and medium-sized solid carrier rocket is developed towards shelving and combination, so that the diameter of the lower-stage engine and the fairing is larger than that of the upper-stage engine, and the rocket is in a 'cavity' shape.

The rocket has a concave cavity in the appearance, a transonic section and a very strong pulsating pressure from the inverted cone section of the fairing, and the external noise intensity reaches 160-170 dB through wind tunnel test measurement. This increases the load on the surface of the arrow body; the low-frequency pulsating pressure can often excite the strong vibration of the rocket shell to cause the structure buffeting response; in addition, the wall pulsating pressure is transmitted into the rocket body in a noise mode, and the reliability of the satellite and rocket-borne equipment is directly influenced. The unsteady aerodynamic force on the surface of the arrow body caused by the cavity with large transonic speed can be handled only by the reinforcing structure, and the vibration suppression measures are taken for the equipment in the arrow. Compared with a rocket without the cavity, the rocket with the shape of the cavity has larger aerodynamic resistance; when the 'concave cavity' section is positioned in front of the arrow body mass center, the pneumatic pressure center is closer to the front, and larger attitude control force is needed near the maximum dynamic pressure point.

When the rocket body is in transonic speed, the external load borne by the rocket body is larger, the 'cavity' section is positioned near the upper stage of the rocket, and the weight reinforced by the structure causes the rocket to lose larger transport capacity. When the pulsating pressure has a low-frequency peak value and is close to the frequency of the rocket body structure, the rocket body is likely to shake, so that the rocket is disassembled and is difficult to solve through structural reinforcement. In addition, the full-speed area of the rocket with the shape of the cavity has larger aerodynamic resistance, which is unfavorable for the transport capacity of the rocket. The pressure center is closer to the front, so that a power system provides a larger spray pipe swing angle, and the requirement on a servo system is higher; on the other hand, a larger nozzle pivot angle reduces the effective thrust.

Disclosure of Invention

The invention aims to provide a stage section pneumatic conformal solid rocket and a separation method, and aims to solve the technical problems that a 'cavity' shape rocket in the prior art has strong transonic pulsating pressure and increases the pneumatic resistance of the rocket outer body.

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

a stage section pneumatic shape-preserving solid rocket comprises a plurality of solid power devices, wherein adjacent solid power devices are connected through a stage section, the shapes of the solid power devices and the stage section are rocket outer bodies, a shape-preserving device is arranged on the surface of each rocket outer body and comprises a pneumatic resultant force difference generating device, a connecting unlocking device and at least two columnar surfaces, the columnar surfaces are connected to the rocket outer bodies through the connecting unlocking devices, and the pneumatic resultant force difference generating devices are arranged on the columnar surfaces;

the at least two columnar surfaces are connected to form a hollow columnar structure, the hollow columnar structure is installed on the rocket outer body, and the hollow columnar structure is used for keeping the appearance of two adjacent stages of the rocket outer body consistent;

the aerodynamic resultant force difference generating device comprises a first control surface and a second control surface, the first control surface is arranged at the end part of the columnar surface close to the head part of the rocket outer body, and the second control surface is arranged at the end part of the columnar surface close to the tail part of the rocket outer body;

the first control surface, the second control surface and the columnar surface form an included angle, and the first control surface and the second control surface generate aerodynamic resultant force difference when the included angles are different, so that the columnar surface is separated from the rocket outer body under the unlocking action of the connecting unlocking device.

As a preferable scheme of the present invention, each of the first control surface and the second control surface includes a control surface and a servo action component, one end of the control surface is connected to the columnar surface through a hinge shaft, a middle position of a back side surface of the control surface is connected to the columnar surface through the servo action component, and the servo action component is configured to drive the control surface to rotate by using the hinge shaft as a rotation axis, so that the control surface and a surface of the columnar surface form the included angle, and the included angle faces an incoming flow direction when the rocket outer body flies.

As a preferable aspect of the present invention, an included angle a is formed between the control surface of the first control surface and the surface of the cylindrical surface under the driving of the servo actuating assembly;

the control surface of the second control surface forms an included angle B with the surface of the cylindrical surface under the driving of the servo action assembly;

the included angle A enables the control surface of the first control surface to bear the maximum normal force vertical to the rocket outer body direction when the rocket outer body reaches the set flight condition;

the included angle B is smaller than the included angle A.

As a preferred scheme of the invention, the servo action assembly comprises a servo motor, a controller, a power supply and a support rod fixedly connected to the output end of the servo motor, wherein the end part of the support rod far away from the servo motor is connected with the middle back side surface of the control surface;

the control surface is attached to the surface of the columnar surface when the controller does not generate the initial state of a control signal of the servo motor; the power supply is used for supplying power to the servo motor and the controller.

As a preferable scheme of the present invention, the connection unlocking means includes a connection block fixedly connected to the columnar surface, and the connection block is connected to the rocket outer body by an explosive bolt.

The invention provides a stage section pneumatic conformal solid rocket separation method, which comprises the following steps:

step 100, rocket appearance shape keeping: a hollow columnar structure formed by connecting a plurality of columnar surfaces is sleeved on the rocket outer body, and the connection between the columnar surfaces and the rocket outer body is realized through a connecting unlocking device, so that the appearances of two adjacent stages of the rocket outer body are kept consistent, and the shape preservation of the appearance of the rocket outer body is completed;

step 200, constructing a pneumatic resultant force difference generation mechanism at the end part of the columnar surface: the end part of the columnar surface close to the head of the rocket outer body and the end part surface of the columnar surface close to the tail of the rocket outer body are provided with control surfaces and servo action components for controlling included angles between the control surfaces and the columnar surface, the included angles between the control surfaces and the columnar surface face the incoming flow direction of the rocket outer body, the included angles between the two control surfaces and the columnar surface are controlled to be different through the servo action components, and the two end parts of the columnar surface generate poor aerodynamic force under the action of airflow in the flying process of the rocket outer body;

step 300, setting the separation condition and state of the columnar surface and the rocket outer body: when the rocket outer body takes off and the rocket outer body reaches the flight condition of transonic speed or maximum dynamic pressure point, the two servo action assemblies receive the trigger control signal to work, so that the included angle between the control surface close to the head of the rocket outer body and the columnar surface is larger than the included angle between the control surface close to the tail of the rocket outer body and the columnar surface, and a separation state is provided for the separation between the columnar surface and the rocket outer body;

step 400, separating the columnar surface from the rocket outer body: the connecting unlocking device receives the detonation control signal to explode the explosive bolt, and the columnar surface is disconnected with the rocket outer shape body under the action of the separation state.

As a preferred embodiment of the present invention, in step 300, when the rocket outer body is subjected to an inflow action under a flight condition where the transonic speed or the maximum dynamic pressure point is reached, the pneumatic resultant force difference generating device receives an axial acting force along the rocket outer body and a normal force perpendicular to the rocket outer body direction, and the pneumatic resultant force difference generating device makes one end of the columnar surface near the top of the rocket outer body receive a normal force perpendicular to the rocket outer body direction larger than a normal force perpendicular to the rocket outer body direction at the other end of the columnar surface.

As a preferable scheme of the invention, after the servo action assembly receives the trigger control signal to work, the connecting unlocking device receives the detonation control signal to explode the explosive bolt, and the time interval between the trigger control signal and the detonation control signal is not more than 0.5 second.

As a preferred scheme of the invention, the calculation formula of the included angle between the control surface close to the rocket outer body head and the cylindrical surface is as follows: defining an included angle of，

，

，

，

Wherein the content of the first and second substances,the upper surface pressure of the control surface is shown,the lower surface pressure of the control surface is shown,the pressure difference between the upper surface and the lower surface of the control surface is shown, F represents the resultant pneumatic force under the condition of incoming flow, S represents the stressed area of the control surface,the maximum normal force of the control surface perpendicular to the rocket outer body direction is shown.

As a preferred scheme of the invention, the method for determining the maximum normal force applied to the control surface under the condition that the included angle between the control surface close to the rocket outer body head and the cylindrical surface is subjected to the action of incoming flow comprises the following steps:

step 301, determining incoming flow states of the rocket outer body and the columnar surface when separation is needed, and obtaining incoming flow Mach number, pressure, temperature, incoming flow density and incoming flow speed of the rocket outer body;

step 302, calculating the pressure of the lower surface of the control surface, which is in contact with the incoming flow in the incoming flow state:

，

wherein the content of the first and second substances,is the total pressure of the mixture,、、respectively the pressure, density and speed of the incoming flow, the incoming flow flows to the lower surface of the control surface to be stopped,namely the pressure intensity of the lower surface of the control surface;

step 303, calculating the maximum reverse force of the control surface in the direction vertical to the rocket outer body according to an included angle calculation formula between the control surface and the columnar surface;

step 304, the included angles between the different control surfaces and the cylindrical surface are given, and the step 301 and the step 303 are repeated to determine the optimal included angle between the control surface and the cylindrical surface.

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

aiming at the phenomenon that transonic pulsating pressure of a rocket with a cavity shape is strong, the shape-preserving outer cover is added outside the cavity to form the shape of the equal-diameter rocket, so that adverse effects of transonic region pulsating pressure on a rocket body are avoided, and requirements on aerodynamic resistance and a swing angle of an engine jet pipe are reduced.

The shape-preserving device realizes the separation from the rocket through pneumatically controlling the control surface after the rocket flies to the maximum dynamic pressure point, and reduces the influence on the transport capacity to the minimum.

The shape-preserving device has the characteristics of simple separation and low bearing weight cost, and can realize the optimization of rocket load and external noise environment.

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 view of an installation structure of a hollow cylindrical structure and rocket outer body provided in an embodiment of the present invention;

FIG. 2 is a schematic structural diagram of a plurality of columnar surfaces connected into a hollow columnar structure according to an embodiment of the present invention;

fig. 3 is a schematic structural diagram of a longitudinal section of a control surface according to an embodiment of the present invention.

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

1-a pneumatic power difference generating device; 2-connecting the unlocking device; 3-a cylindrical surface; 4-control surface; 5-a servo action assembly; 6-articulated shaft; 11-a first control surface; 12-a second control surface; 21-connecting blocks; 22-explosive bolts; 51-a servo motor; 52-support bar.

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, fig. 2 and fig. 3, the invention provides a stage section pneumatic conformal solid rocket, which comprises a plurality of solid power devices, wherein adjacent solid power devices are connected through a stage section, the solid power devices and the stage section are in the shape of a rocket outer body, a conformal device is arranged on the surface of the rocket outer body, and the conformal device comprises a cylindrical surface, a pneumatic resultant force difference generating device and a connection unlocking device. The hollow columnar structure formed by connecting the plurality of columnar surfaces aims at a rocket outer body with a 'cavity' structure, and the 'cavity' specifically refers to the structure of the rocket outer body formed by the fact that the diameter of one interstage structure of the rocket is smaller than the diameter of other interstage structures connected with the interstage structure of the rocket.

The hollow columnar structure is arranged on the rocket outer body and used for keeping the appearance of two adjacent interstage structures of the rocket outer body consistent, namely, the hollow columnar structure is arranged on the interstage structure at the 'cavity', so that the interstage structure forming the 'cavity' is consistent with other interstage structures in appearance.

As shown in fig. 1, specifically, the hollow columnar structure is formed by connecting at least two columnar surfaces, the end portions of the columnar surfaces are connected with the rocket outer body through a connecting and unlocking device, and the pneumatic resultant force difference generating device is arranged on the columnar surfaces.

The connecting and unlocking device 2 is used for realizing the connection and the separation between the columnar surface 3 and the rocket outer body;

the aerodynamic resultant force difference generating device 1 comprises a first control surface 11 and a second control surface 12, wherein the first control surface 11 is arranged at the end part of the columnar surface 3 close to the head part of the rocket outer body, and the second control surface 12 is arranged at the end part of the columnar surface 3 close to the tail part of the rocket outer body;

when the rocket outer body reaches a set flight condition, the first control surface 11 and the second control surface are used for enabling the end part of the columnar surface 3 close to the head part of the rocket outer body and the end part close to the tail part of the rocket outer body to generate a pneumatic power difference, and the connecting and unlocking device 2 separates the connection between the columnar surface 3 and the rocket outer body under the condition that the pneumatic power difference exists between the end part of the columnar surface 3 close to the head part of the rocket outer body and the end part close to the tail part of the rocket outer body.

The pneumatic power difference generating device is used for enabling the end parts on the two sides of the columnar surface to generate pneumatic power difference after the rocket outer body reaches a set flight condition, and the connecting unlocking device is matched to receive a triggering control instruction to break the connection between the columnar surface and the rocket outer body, so that the columnar surface is far away from the rocket outer body.

The specific implementation process of the invention is that before the rocket takes off, a hollow columnar structure is arranged outside the rocket outer body with a shape of a cavity, so that the rocket has a good external noise environment in a transonic speed section, after the rocket outer body flies over the transonic speed (the Mach number is more than 1.2) or the maximum dynamic pressure point, the front pneumatic resultant force difference generating device and the rear pneumatic resultant force difference generating device (close to the top point of the rocket is the front pneumatic resultant force difference generating device) simultaneously control the action at a specified time (pre-installed in a control system), and at the moment, the incoming flow generated in the flight of the rocket outer body enables the pneumatic resultant force difference generating device to be acted by forces along two directions of the axial direction and the outward direction.

The connecting unlocking device is used for bolt blasting, and the hollow columnar structure is far away from the arrow body and flies out under the outward pneumatic acting force of the two control surfaces.

Specifically, the first control surface and the second control surface are used for generating a normal force perpendicular to the rocket outer body direction under the action of an incoming flow generated by the first control surface and the second control surface when the rocket outer body flies after reaching a set flying condition, so that the normal force of the first control surface is larger than the aerodynamic force difference generated by two side ends of a columnar surface formed by the normal force of the second control surface.

The first control surface 11 and the second control surface 12 both comprise a control surface 4 and a servo action assembly 5;

one end of the control surface 4 passes through the hinged shaft 6 and the columnar surface 3, and the servo action assembly 5 is used for driving the control surface 4 to rotate by taking the hinged shaft 6 as a rotating shaft, so that an included angle is formed between the control surface 4 and the surface of the columnar surface 3 and faces to the incoming flow direction of the rocket outer body during flying;

an included angle A formed by the control surface 4 of the first control surface 11 and the surface of the columnar surface 3 enables the control surface 4 of the first control surface 11 to bear the maximum normal force vertical to the rocket outer body direction when the rocket outer body reaches a set flight condition;

the included angle B formed by the control surface 4 of the second control surface 12 and the surface of the cylindrical surface 3 is smaller than the included angle A, and the purpose is that from the perspective of the rocket, the aerodynamic action force formed by the first control surface and the second control surface under the incoming flow condition is poor, so that the separation process of the cylindrical surface and the rocket outer body forms the separating effect of breaking off.

The calculation formula of the included angle A in the invention is as follows: define an included angle A ofThe determining method specifically comprises the following steps:

firstly, determining the incoming flow state, namely the working condition at the separation moment, and knowing the mach number, the pressure, the temperature, the density and the speed of the incoming flow.

Secondly, calculating the pressure intensity of the lower surface of the control surface:

，

in the formulaIs the total pressure of the mixture,、、respectively, the incoming flow pressure, density and velocity. The incoming flow is stopped at the lower surface of the control surface,namely the pressure intensity of the lower surface of the control surface.

Thirdly, calculating the pressure intensity of the upper surface of the control surface:

the separation state is supersonic speed working condition flying over transonic speed, so that the flow generates expansion shock wave on the upper surface of the control surface, and the opening angle of the control surface isAccording to the prandtl-meier theory, the control surface upper surface pressure is calculated as follows.

1) Known incoming flowAccording toTo obtain；

2) Using a known opening angleAnd 1) is calculated toAccording toTo obtain；

3) Obtained according to 2)According toTo obtain；

The entropy value after the expansion wave front is not changed, so that the wave front is wave rearIs not changed, i.e.According to the following:

to obtain，I.e. the upper surface pressure of the control surface.

A fourth step, further according to:

，

，

，

wherein the content of the first and second substances,the upper surface pressure of the control surface is shown,the lower surface pressure of the control surface is shown,the pressure difference between the upper surface and the lower surface of the control surface is shown, F represents the resultant pneumatic force under the condition of incoming flow, S represents the stressed area of the control surface,the maximum normal force of the control surface perpendicular to the rocket outer body direction is represented, and the maximum normal force of the control surface perpendicular to the rocket outer body direction is calculated;

the total pressure of the incoming flow in front of the control surface is obtained;the pressure of the incoming flow in front of the control surface, namely static pressure;the Mach number of the incoming flow of the control surface is;the total pressure of the flow on the upper surface of the control surface is obtained after the expansion wave;the Mach number of the flow on the upper surface of the control surface is obtained after the expansion wave;the specific heat ratio of the gas is,n is the number of microscopic degrees of freedom of movement of the gas molecules, and for a standard gas,。

and fifthly, determining the optimal angle.

And (4) giving different control surface opening angles theta, repeating the first step to the fourth step, and finding the control surface opening angle when the maximum normal force perpendicular to the arrow body direction is found, namely the control surface opening optimal angle.

At this time, an included angle is formed between the control surface and the columnar surface, the incoming flow environment of the control surface is supersonic incoming flow, the airflow flow of the lower surface of the control surface (namely the surface of the control surface opposite to the columnar surface) is completely stagnant, the pressure on the control surface is the total pressure of the incoming flow, the top edge of the upper surface of the control surface generates expansion shock waves, and the pressure generated by the expansion shock waves on the control surface along the axial direction of the rocket outer body is smaller than the total pressure of the incoming flow.

Thus, under the action of the incoming flow, the control surface is subjected to a resultant aerodynamic force perpendicular to the surface of the control surface, which is decomposed into an axial force along the rocket outer body and a normal force perpendicular to the rocket outer body, which is related to the opening angle of the control surface.

The difference of aerodynamic force generated at the two ends of the columnar surface mainly lies in the difference of opening angles of the control surfaces arranged in a mirror image mode at the two ends of the columnar surface under the action of incoming flow.

In the invention, the control of the included angle between the control surface and the columnar surface is realized through a servo action assembly, the servo action assembly comprises a servo motor, a controller, a power supply and a support rod fixedly connected to the output end of the servo motor, and the end part of the support rod far away from the servo motor is connected with the middle back side surface of the control surface.

And when the controller does not generate the control signal of the servo motor in the initial state, the control surface is attached to the surface of the columnar surface.

The power supply is used for supplying power to the servo motor and the controller.

The connecting and unlocking device comprises a connecting block fixedly connected to the end part of the cylindrical surface, and the connecting block is connected with the rocket outer body through an explosive bolt.

After the rocket outer body enters the supersonic speed section, namely the Mach number is larger than 1.2, the selected time (preferably just exceeding the maximum dynamic pressure point) is selected, the explosion bolt explosion starting time connected with the unlocking device after the first control surface is opened is not too long, the opening state provides large aerodynamic resistance, and the time interval is not more than 0.5 second.

The first control surface and the second control surface at two ends of the circular surface are not limited to be a pair and can comprise a plurality of control surfaces;

the number of the first control surface can be larger than that of the second control surface. The general principle is to ensure that the normal force in the direction perpendicular to the arrow body on the front part of the columnar surface is larger than that on the rear end of the columnar surface.

Generally, the plurality of columnar surfaces are combined to form the whole of a hollow columnar structure, and the first control surfaces on the two ends of the hollow columnar structure are uniformly distributed in the circumferential direction of the hollow columnar structure.

The columnar surface is not used as a bearing part of the rocket outer body, only bears the pressure difference between the inner surface and the outer surface caused by the flying attack angle of the rocket outer body, and takes a certain medium-large solid rocket as an example, the maximum pressure on the position of the columnar surface is 15 kpa.

The arrow in the flying process of the rocket outer body can be bent, the columnar surface is rigidly connected with the outer wall of the rocket outer body through the explosion bolt, the hollow columnar structure whole body can be stretched and extruded to deform by the rocket, and therefore the columnar surface is made of a composite material with a good stretching and extruding effect.

Considering the stretching and pressing, and the pressure bearing, the aim of saving weight is that the columnar surface should not exceed 2 mm.

At least two columnar mask bodies can be in a two-petal type with 180-degree circumferential direction, and also can be in a three-petal type with 120-degree circumferential direction or in a four-petal type with 90-degree circumferential direction.

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.