A box type launch rocket one, two subgrade separation dynamics equivalent verification method

Abstract

The application provides a box type launching rocket one-two substage separation dynamics equivalent verification method, which comprises the following steps: rocket interstage vertical two-body separation free motion is equivalent to horizontal single-body separation motion, horizontal separation single-body equivalent mass calculation, three lateral load equivalents are one horizontal load, separation dynamics equivalent verification method, and test result interpretation. The application, by acceleration equivalence, equivalent two-body vertical separation dynamics of the box type launching rocket one-two substage to single-body dynamics with one end fixed and one end moving; equivalent forces and moments at the separation surface of all loads of the rocket to lateral forces at the moving end; equivalent vertical two-body separation free motion of the interstage to horizontal single-body separation motion based on the air floating platform; equivalent forces and moments at the separation surface of all loads of the rocket to lateral forces at the moving end by measuring the displacement of the separation body and solving the speed of the separation body; and the separation capacity is analyzed based on the interpretation principle.

Description

Technical Field

[0001] This invention relates to the technical field of verification methods for rocket separation dynamics, and particularly to an equivalent verification method for the separation dynamics of the first and second stages of a box-launched rocket. Background Technology

[0002] The box-type launch vehicle separation system consists of three separation subsystems: the first and second stage separation system, the fairing separation system, and the second and third stage separation system. The first and second stage separation mechanism enables the mechanical connection between the first and second stages of the rocket, ensuring reliable connection during launch and reliable separation during dynamic processes. Successful separation of the first and second stages of the box-type rocket is a crucial step for a successful launch; failure to separate will lead to mission failure. To mitigate development risks, dynamic verification tests of the first and second stage separation are necessary.

[0003] Due to limitations in ground environment and test site, existing separation tests mainly consist of static tests of a single separation spring and suspension tests with small overall loads. These separation tests differ significantly from actual free-state separation and cannot accurately obtain the dynamic characteristics of separation. Summary of the Invention

[0004] The purpose of this invention is to provide a dynamic equivalent verification method for the separation of the first and second stages of a box-type launch rocket, accurately obtain the dynamic characteristics of the separation of the first and second stages of the box-type launch rocket, verify the reliability of the separation, and provide guidance for the design of separation mechanism parameters.

[0005] The technical solution of this invention is: to provide a method for verifying the dynamic equivalence of the separation of the first and second stages of a box-type launch rocket, comprising the following steps:

[0006] S1. The vertical two-body separation free motion between rocket stages is equivalent to the horizontal single-body separation motion.

[0007] S2, Calculation of equivalent mass of separated monomers;

[0008] S3. Equivalent the three lateral loads to one horizontal load;

[0009] S4. Equivalent verification of separation kinetics;

[0010] S5. Interpretation of test results.

[0011] Furthermore, in step S1, when the rocket is vertically separated, the free separation motion of the first stage and the second stage is equivalent to a horizontal separation state, the first stage structural tube is fixed, and the separation unit moves horizontally.

[0012] Furthermore, in step S2, the calculation of the equivalent mass of the separated monomers specifically involves:

[0013] equivalent quality Where m1 is the mass of the first stage of the rocket and m2 is the mass of the second stage of the rocket.

[0014] Furthermore, in step S3:

[0015] The aerodynamic force F borne by the first stage of the rocket y1_aero Control force F y1_ctrl And the aerodynamic force F borne by the second stage of the rocket y2_aero First, it can be equivalent to the lateral forces at the separation surfaces of the first and second stages of the rocket.

[0016] and torque

[0017]

[0018] Where d1 is F y2_aero The distance to the second-stage mass center, d2 is F flm Distance to the center of mass of the second stage, I zz_2 For the inertia of the two substages about the Z-axis, I zz_1 Let d3 be the moment of inertia of the first stage about the Z-axis, and F be the moment of inertia of y1_aero The distance to the first-order centroid, d4 ​​is F y1_ctrl The distance to the first-order centroid, d5 is F flm The distance to the center of mass of the first stage.

[0019] Furthermore, in step S3, the equivalent shear force F at the separation interface is... flm and equivalent moment T flm Through shear force F flm This is achieved by offsetting the separation interface by a distance d.

[0020] Furthermore, in step S4, the first-stage rocket structure tube is fixed to the ground by a fixing device, and the separation unit structure tube is suspended on a marble platform by air pressure. The displacement of the separation unit is measured by a high-speed camera, and the shear force F is transferred to the mass block via a steel wire rope pulley. flm It is applied to the separated monomer structure cylinder.

[0021] Furthermore, the mass of the separated monomer structure cylinder The moment of inertia about the Z-axis is I zz_2 .

[0022] Furthermore, the wire rope is fixed to the single-unit structural cylinder, and the wire rope passes over a fixed pulley. The other end of the wire rope is fixed to a mass block, and the mass of the mass block is m3 = F. flm / 9.86;

[0023] Distance between the fixed point of the wire rope and the separation interface of the separate unit structure cylinder .

[0024] Furthermore, the distance l between the fixed pulley and the connection point between the wire rope and the separation unit structure cylinder is ≥10m, ensuring that the component of the wire rope tension in the separation direction can be ignored during the separation process.

[0025] Furthermore, in step S5, the displacement of the separated unit is calculated using Euler difference to obtain the separation velocity. The separation distance being greater than the compression stroke of the first and second stage springs of the rocket and the separation velocity being greater than 1 m / s are used as the criteria for determining whether the separation is successful.

[0026] The beneficial effects of the box-type launch rocket first and second stage separation dynamics equivalent verification method provided by this invention are:

[0027] The method of this invention can effectively test the dynamic characteristics of the separation of the first and second stages of a box-launched rocket, verify the reliability of the separation, and has a rigorous and reasonable principle, a clear equivalent method, and a convenient and feasible operation method. It is also economical and easy to implement. It can be widely applied to separation tests between different stages of rockets. Attached Figure Description

[0028] The invention will be further described below with reference to the accompanying drawings:

[0029] Figure 1 This is a schematic diagram of a box-type launch rocket first and second stage separation dynamics verification method according to the present invention;

[0030] Figure 2 This invention provides an equivalent principle for verifying the separation dynamics of the first and second stages of the box-type launch rocket.

[0031] Figure 3 This is a schematic diagram illustrating the interpretation of the separation distance test results of the present invention;

[0032] Figure 4 This is a schematic diagram illustrating the interpretation of the separation speed test results of the present invention. Detailed Implementation

[0033] The following detailed description, in conjunction with the accompanying drawings and specific embodiments, further illustrates the proposed method for verifying the dynamic equivalence of the separation of the first and second stages of a box-type launch rocket. The advantages and features of the present invention will become clearer from the following description and claims. It should be noted that the accompanying drawings are in a very simplified form and use non-precise ratios, and are only used to facilitate and clarify the illustration of the embodiments of the present invention.

[0034] The core idea of ​​this invention is that the method can effectively test the dynamic characteristics of the separation of the first and second stages of a box-launched rocket, verify the reliability of the separation, and has a rigorous and reasonable principle, a clear equivalent method, and a convenient and feasible operation method. Furthermore, it is economical and easy to implement. It can be widely applied to separation tests between different stages of rockets.

[0035] Example 1

[0036] The following description, in conjunction with the accompanying drawings, provides a more detailed explanation of the method for verifying the separation dynamics of the first and second stages of a box-type launch rocket provided in this application. Specific implementation methods may include (e.g.) Figures 1-4 As shown):

[0037] I. The vertical two-body separation free motion between rocket stages is equivalent to the horizontal single-body separation motion.

[0038] When the rocket separates vertically, the free separation motion of the first and second stages is equivalent to a horizontal separation state. The first stage structural tube is fixed, and the separation unit moves horizontally, such as... Figure 2 As shown on the right.

[0039] II. Calculation of Equivalent Mass of Separated Monomers

[0040] According to the principle of equal acceleration, the equivalent mass of the moving end... m1 is the mass of the first stage of the rocket, and m2 is the mass of the second stage of the rocket.

[0041] III. Three lateral loads are equivalent to one horizontal load.

[0042] The free motion state of the first and second stages of the box-launched rocket after vertical separation is as follows: Figure 2 (Left) As shown, the rocket's first stage is subjected to aerodynamic force F. y1_aero Control force F y1_ctrl The aerodynamic force F borne by the second stage of the rocket y2_aero This is equivalent to the horizontal separation motion of individual units, such as... Figure 2 (Right), placed horizontally, one end fixed, the other end movable; the three lateral loads on the first and second stages of the rocket are equivalent to one horizontal load F. flm ;

[0043] The aerodynamic force F borne by the first stage of the rocket y1_aero Control force F y1_ctrl And the aerodynamic force F borne by the second stage of the rocket y2_aero First, it can be equivalent to the lateral forces at the separation surfaces of the first and second stages of the rocket.

[0044] and torque

[0045]

[0046] d1 is F y2_aero The distance to the second-stage mass center, d2 is the distance from the separation interface to the second-stage mass center, I zz_2 For the inertia of the two substages about the Z-axis, I zz_1 Let d3 be the moment of inertia of the first stage about the Z-axis, and F be the moment of inertia of y1_aero The distance to the first-order centroid, d4 ​​is F y1_ctrlThe distance to the first-stage centroid, d5 is the distance from the separation interface to the first-stage centroid.

[0047] Then the equivalent shear force F at the separation interface flm and equivalent moment T flm Through shear force F flm This is achieved by offsetting the separation interface by a distance d.

[0048] IV. Equivalent Verification Method for Separation Kinetics

[0049] Separation kinetics equivalent verification method such as Figure 1 As shown, the first stage structure 4 of the rocket is fixed to the ground by a fixing device; the separation unit structure 3 is suspended on the marble platform 2 by air pressure; the displacement of the separation unit is measured by a high-speed camera 6; and the shear force F is transferred to the mass block 1 via a steel wire rope pulley 5. flm It is applied to the separated monomer structure cylinder.

[0050] Mass of the separated single-unit structural cylinder The moment of inertia about the Z-axis is I zz_2 .

[0051] A wire rope is fixed to the single-unit structural cylinder. The wire rope passes over a fixed pulley, and the other end is fixed to a mass block. The mass block has a mass m3 = F. flm / 9.86.

[0052] Distance between the fixed point of the wire rope and the separation interface of the separate unit structure cylinder .

[0053] The distance l between the fixed pulley and the fixed point between the wire rope and the separation unit structure cylinder is ≥10m, ensuring that the component of the wire rope tension in the separation direction (X direction) can be ignored during the separation process;

[0054] V. Interpretation of Test Results

[0055] The separation velocity is calculated by using Euler finite difference to determine the displacement of the separated unit. The separation distance is greater than the compression stroke of the first and second stage springs of the rocket (e.g., Figure 3 As shown), and the separation speed is greater than 1 m / s (e.g. Figure 4 As shown in the figure, this serves as the criterion for determining whether the separation was successful.

[0056] The contents not described in detail in this specification are prior art known to those skilled in the art. It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within the present invention.

Claims

1. A method for verifying the dynamic equivalence of the separation of the first and second stages of a box-launched rocket, characterized in that, Includes the following steps: S1. The vertical two-body separation free motion between rocket stages is equivalent to the horizontal single-body separation motion. S2, Calculation of equivalent mass of separated monomers; S3. Equivalent the three lateral loads to one horizontal load; S4. Equivalent verification of separation kinetics; S5. Interpretation of test results; In step S1, when the rocket is vertically separated, the free separation motion of the first stage and the second stage is equivalent to the horizontal separation state. The first stage structural tube is fixed, and the separation unit moves horizontally. In step S2, the calculation of the equivalent mass of the separated monomers is specifically as follows: equivalent quality ,in For the mass of the first stage of the rocket, The mass of the second stage of the rocket; In step S3: The aerodynamic forces borne by the first stage of the rocket Control And the aerodynamic forces borne by the second stage of the rocket First, it can be equivalent to the lateral forces at the separation surfaces of the first and second stages of the rocket. and torque ， in for Distance to the center of mass of the second stage for Distance to the center of mass of the second stage The moment of inertia of the second stage about the Z-axis, The moment of inertia of the first stage about the Z-axis, for Distance to the first-stage center of mass for Distance to the first-stage center of mass for The distance to the center of mass of the first-stage sub-sub ... In step S3, the lateral forces acting on the separation surfaces of the first and second stages of the rocket are... and torque Through shear force Distance from separation interface To achieve, ; In step S4, the first-stage rocket structure tube is fixed to the ground by a fixing device. The separation unit structure tube is suspended on a marble platform by air pressure. The displacement of the separation unit is measured by a high-speed camera. The lateral force of the separation surface between the first and second stages of the rocket is distributed by a steel cable pulley and mass block. Apply to the separated monomer structure cylinder; The wire rope is fixed to the single-unit structural cylinder, and the wire rope passes over a fixed pulley. The other end of the wire rope is fixed to a mass block, and the mass block has a mass of [missing information]. ; Distance between the fixed point of the wire rope and the separation interface of the separate unit structure cylinder .

2. The method for verifying the dynamics of separation between the first and second stages of a box-type launch rocket as described in claim 1, characterized in that, The mass of the separated single-unit structural cylinder The moment of inertia about the Z-axis is .

3. The method for verifying the dynamic equivalence of the separation of the first and second stages of a box-type launch rocket as described in claim 1, characterized in that, Distance between the fixed pulley and the fixed point of the wire rope and the separate unit structure cylinder This ensures that the component of the wire rope tension in the separation direction can be ignored during the separation process.

4. The method for verifying the separation dynamics of the first and second stages of a box-type launch rocket as described in claim 1, characterized in that, In step S5, the displacement of the separated unit is calculated using Euler difference to obtain the separation velocity. The separation distance is greater than the compression stroke of the first and second stage springs of the rocket, and the separation velocity is greater than 1 m / s, which are used as the criteria for judging whether the separation is successful.

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