Sounding rocket capable of realizing inter-stage automatic separation based on aerodynamic resistance

Abstract

The invention belongs to the technical field of sounding rockets, and provides a sounding rocket capable of realizing inter-stage automatic separation based on aerodynamic resistance, the sounding rocket comprises a power stage and a load stage, the power stage and the load stage are in plug-in tenon-and-mortise connection, a butt joint tenon is located at the head end of the power stage, and a butt joint mortise is located at the tail end of the load stage. The axial acceleration of the power stage is smaller than that of the load stage due to different sectional areas between the power stage and the load stage at the end moment of the power flight section of the rocket under the action of aerodynamic resistance, so that automatic separation of the power stage and the load stage is realized, the energy loss of the rocket in the inertial flight section is effectively reduced, and the service life of the rocket is prolonged. An existing rocket interstage separation mode is simplified, and the complexity of a sounding rocket interstage separation system is effectively reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of sounding rockets, and particularly relates to a sounding rocket that realizes automatic separation between stages based on aerodynamic drag. Background Art

[0002] The near space generally refers to the region of 20 km to 120 km, covering the stratosphere, mesosphere, and lower thermosphere regions divided by temperature characteristics. There are complex atmospheric processes in this region, including photochemical processes, dynamic processes, ionization processes, phase change microphysical processes, etc., and there are also forced perturbations between the troposphere and the thermosphere. Therefore, near space exploration is of great significance to fields such as atmospheric science and atmospheric physics science.

[0003] The near space meteorological environment can be detected by technologies such as remote sensing and sounding rockets. Compared with remote sensing technology, although rocket detection has the disadvantages of not being reusable and unable to continuously observe for a long time, it is still an indispensable important means for near space atmospheric detection because it is the only method for in-situ detection in the near space. In-situ detection in the near space has been studied since the late 1940s. Currently, sounding rockets used for the near space mostly adopt single-stage rockets or two-stage powered rockets, but they have the following deficiencies: Single-stage rockets usually have a large diameter and large aerodynamic drag during the inertial flight segment; for two-stage powered rockets, the inter-stage separation control system is complex and will increase the ineffective mass. With the increasing urgency of the demand for near space atmospheric environment detection, it is necessary to propose a sounding rocket that realizes automatic separation between stages based on aerodynamic drag. Summary of the Invention

[0004] Aiming at the problems existing in the prior art, the sounding rocket of the present invention that realizes automatic separation between stages based on aerodynamic drag utilizes the aerodynamic force at the end of the operation of the power stage to form a resistance difference between the payload stage and the power stage with different cross-sectional areas, so that the structure of the docking tenon and mortise is separated, realizing the automatic separation between the payload stage and the power stage, reducing the energy loss of the rocket during inertial flight, simplifying the existing inter-stage separation method of the rocket, greatly reducing the complexity of the inter-stage separation system, and improving the stability of the rocket inter-stage separation.

[0005] The present invention provides a sounding rocket that realizes automatic separation between stages based on aerodynamic drag, which includes a power stage and a payload stage, and the head end of the power stage is connected to the tail end of the payload stage by a pluggable tenon and mortise;

[0006] The pluggable tenon and mortise includes a docking tenon and a docking mortise. The docking tenon is located at the head end of the power stage, and the docking mortise is located at the tail end of the payload stage;

[0007] At the end of the powered flight stage of the rocket, due to the different cross-sectional areas between the powered stage and the payload stage, under the action of aerodynamic drag, the axial acceleration of the powered stage is less than that of the payload stage, realizing the automatic separation of the powered stage and the payload stage. The specific inter-stage separation is as follows:

[0008] If the axial acceleration of the powered stage is less than that of the payload stage , then there is:

[0009] ;

[0010] In the formula, m 1 , m 2 are the masses of the powered stage and the payload stage at the end of the active section of the rocket, A 1 , A 2 are the aerodynamic drag cross-sectional areas of the powered stage and the payload stage of the rocket, C d1 , C d2 are the drag coefficients of the powered stage and the payload stage of the rocket, g is the acceleration due to gravity, θ is the rocket elevation angle, ρ is the atmospheric density, v is the rocket axial velocity, and f is the static friction force between the docking socket and the docking tenon.

[0011] Preferably, if , set the ratio of the aerodynamic drag cross-sectional areas of the powered stage and the payload stage of the rocket to satisfy the following conditions:

[0012] ;

[0013] In the formula, is the ratio of the inter-stage friction force to the aerodynamic cross-sectional drag force of the payload stage, denoted as β. The drag cross-section A 1 of the powered stage of the rocket is the area obtained by subtracting the cross-section blocked by the payload stage at the docking location from its outer diameter cross-section. The ratio of the blocked cross-section at the docking location to the cross-section of the payload stage is λ, , where is the blocked cross-section at the docking location.

[0014] Preferably, the outer diameter D 1 of the powered stage and the outer diameter D 2 of the payload stage have the following relationship:

[0015] ;

[0016] The following conditions are satisfied between the payload stage and the powered stage of the rocket:

[0017] .

[0018] Preferably, ignoring the influence of minor factors such as air buoyancy and Coriolis force, according to Newton's second law, at the end of the powered flight stage of the rocket, the mechanical equilibrium equations of the powered stage and the payload stage are:

[0019] 。

[0020] Preferably, the docking tenon is made of a high-strength material and can withstand the load during powered flight.

[0021] Preferably, a mortise and tenon structure is adopted for the connection between the payload stage and the power stage, and the docking mortise is arranged at the tail of the payload stage.

[0022] Preferably, fins are provided at the tails of both the payload stage and the power stage to jointly maintain the stability during the powered flight section.

[0023] Compared with the prior art, the present invention has the following advantages:

[0024] The sounding rocket of the present invention realizes the automatic separation between stages based on aerodynamic drag. The automatic separation between the payload stage and the power stage is achieved through the drag difference formed by the aerodynamic force acting on the payload stage and the power stage with different cross-sectional areas when the power stage finishes working, reducing the energy loss during the inertial flight section of the rocket, simplifying the existing stage separation method of the rocket, greatly reducing the complexity of the stage separation system, improving the reliability of the rocket stage separation, and at the same time reducing the detection cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is the overall schematic diagram of the sounding rocket of the present invention that realizes the automatic separation between stages based on aerodynamic drag;

[0026] Figure 2 is the enlarged schematic diagram of the structure in the sounding rocket of the present invention that realizes the automatic separation between stages based on aerodynamic drag;

[0027] Figure 3 is the schematic diagram of the stage separation mechanism in the sounding rocket of the present invention that realizes the automatic separation between stages based on aerodynamic drag;

[0028] Figure 4 is the connection schematic diagram of the stage separation mechanism in the present invention;

[0029] Figure 5 is Figure 4 the enlarged schematic diagram at I in

[0030] Figure 6 is the structural schematic diagram of the docking mortise in the stage separation mechanism of the present invention;

[0031] Figure 7 is the structural schematic diagram of the docking tenon in the stage separation mechanism of the present invention.

[0032] Main reference numerals:

[0033] 1. Payload stage; 11. Payload fin; 12. Docking mortise; 2. Power stage; 21. Engine compartment section; 22. Power fin; 23. Docking tenon; 231. Limit pin. Detailed implementation mode

[0034] To elaborate on the technical content, structural features, achieved objectives and effects of the present invention, the following will be described in detail with reference to the accompanying drawings of the specification.

[0035] The sounding rocket of the present invention that realizes automatic stage separation based on aerodynamic drag, as Figure 1 shown, includes a power stage 2 and a payload stage 1. The front end of the power stage 2 and the rear end of the payload stage 1 are connected by a plug-in tenon-mortise connection. The payload stage 1 is provided with a payload fin 11 at the tail to ensure the stability of the payload stage 1 during inertial flight. The power stage 2 includes an engine compartment section 21 and a power fin 22, etc. The power fin 22 is arranged at the rear end of the engine compartment section 21 through a connecting member.

[0036] As Figures 2 to 7 shown, the plug-in tenon-mortise includes a docking mortise 12 and a docking tenon 23. The docking tenon 23 is located at the front end of the inter-stage section of the power stage 2. A limit pin 231 is provided on the docking tenon 23 to limit the relative rotation with the docking mortise 12 before separation. The docking mortise 12 is located at the rear end of the payload stage 1. The docking tenon 23 is made of a high-strength material and can withstand the load during powered flight. When the sounding rocket is under the action of aerodynamic drag at the end of the powered flight stage, the axial acceleration of the payload stage 1 is greater than that of the power stage 2, realizing the automatic separation of the power stage 2 and the payload stage 1. The specific inter-stage separation is as follows:

[0037] If the axial acceleration of the power stage 2 is less than the axial acceleration of the payload stage 1 , then there is:

[0038] ;

[0039] In the formula, m 1 , m 2 are the masses of the power stage and the payload stage at the end of the active section of the rocket, A 1 , A 2 are the aerodynamic drag cross-sectional areas of the power stage and the payload stage of the rocket, C d1 , C d2 are the drag coefficients of the power stage and the payload stage of the rocket, g is the acceleration due to gravity, θ is the rocket elevation angle, ρ is the atmospheric density, v is the axial velocity of the rocket, and f is the static friction force between the docking mortise 12 and the docking tenon 23.

[0040] If , set the ratio of the aerodynamic drag cross-sectional areas of the power stage 2 and the payload stage 1 of the rocket to satisfy the following conditions:

[0041] ;

[0042] In the formula, is the ratio of the inter-stage frictional force to the aerodynamic cross-sectional resistance of the load stage, denoted as β, and the resistance cross-section A of the power stage 1 is the area obtained by subtracting the cross-section blocked by the load stage at the docking location from the outer diameter cross-section. The ratio of the blocked cross-section at the docking location to the load stage cross-section is λ. , where is the blocked cross-section at the docking location.

[0043] The outer diameters of the power stage 2 and the load stage 1 are D 1 and D 2 , respectively, then it is:

[0044] .

[0045] The following conditions are satisfied between the rocket load stage 1 and the power stage 2:

[0046] .

[0047] Neglecting the influence of minor factors such as air buoyancy and Coriolis force, according to Newton's second law, at the end of the powered flight section of the rocket, the mechanical equilibrium equations of the power stage 2 and the load stage 1 are:

[0048] .

[0049] The following further describes the sounding rocket of the present invention for achieving inter-stage automatic separation based on aerodynamic resistance in combination with embodiments:

[0050] The separation method of the sounding rocket for achieving inter-stage automatic separation based on aerodynamic resistance includes the following steps:

[0051] S1. The diameter of the load stage 1 is affected by the size of the built-in device. Usually, it is first determined in the design, and then the power stage is designed with the power stage diameter being 3 times the diameter of the load stage 1. Then, a check is carried out. If the separation conditions cannot be met, the mass of the load stage 1 is adjusted to meet the separation requirements.

[0052] S2. The load stage 1 and the power stage 2 achieve automatic separation under the action of the resistance difference formed by the difference in the rocket body cross-section.

[0053] S3. The load stage 1 continues to fly upward under the action of inertia to near the ballistic vertex, and the timing device is activated to throw out the detection load.

[0054] S4. The detection load detects from top to bottom and transmits the detection data in real time. The data is received and saved by the ground receiving device.

[0055] The sounding rocket of the present invention realizes automatic staging separation based on aerodynamic drag. When the power stage 2 finishes working, the drag difference formed by the aerodynamic force acting on the payload stage 1 and the power stage 2 with different cross-sectional areas causes the docking tenon and mortise structure to separate, thereby realizing the automatic separation of the payload stage 1 and the power stage 2, reducing the energy loss of the rocket during the inertial flight section, greatly reducing the complexity of the staging separation system, improving the stability of the rocket staging separation, and thus reducing the rocket cost.

[0056] The embodiments described above are only descriptions of the preferred embodiments of the present invention and do not limit the scope of the present invention. Without departing from the design spirit of the present invention, various deformations and improvements made by those of ordinary skill in the art to the technical solutions of the present invention shall fall within the protection scope determined by the claims of the present invention.

Claims

1. A sounding rocket that realizes automatic stage separation based on aerodynamic drag, characterized in that: It includes a power stage and a load stage, and the front end of the power stage and the rear end of the load stage are connected by plug-in mortise and tenon joints; The plug-in mortise and tenon joints include a butt joint and a butt joint. The butt joint is located at the head end of the power stage, and the butt joint is located at the tail end of the load stage. At the end of the powered flight phase, due to the different cross-sectional areas between the power stage and the payload stage, under the action of aerodynamic drag, the axial acceleration of the power stage is less than that of the payload stage, thus achieving automatic separation of the power stage and the payload stage. The specific separation between the stages is as follows: If the axial acceleration of the power stage is less than the axial acceleration of the load stage , then: ； Where m1 and m2 are the masses of the power stage and the payload stage at the end of the active phase of the rocket, A1 and A2 are the aerodynamic drag cross-sectional areas of the power stage and the payload stage of the rocket, and C d1 , C d2 is the drag coefficient of the rocket power level and payload level, g is the acceleration of gravity, θ is the rocket elevation angle, ρ is the atmospheric density, v is the axial velocity of the rocket, and f is the static friction between the mortise and tenon.

2. The sounding rocket for realizing automatic stage separation based on aerodynamic drag according to claim 1, characterized in that: like , the ratio of the cross-sectional area of ​​the rocket power stage and the load stage aerodynamic drag is set to meet the following conditions: ； In the formula, is the ratio of the interstage friction force to the aerodynamic cross-sectional resistance of the load stage, assuming it is β. The drag cross-sectional area A1 of the rocket power stage is the area after deducting the cross-sectional area blocked by the load stage at the docking point from its outer diameter cross-sectional area. The ratio of the blocked cross-sectional area at the docking point to the cross-sectional area of ​​the load stage is λ. ,in Block the cross section for the joint.

3. The sounding rocket for realizing automatic stage separation based on aerodynamic drag according to claim 2, characterized in that: The power stage outer diameter D1 and the load stage outer diameter D2 have the following relationship: ； The rocket payload stage and power stage meet the following conditions: 。 4. The sounding rocket for realizing automatic stage separation based on aerodynamic drag according to claim 1, characterized in that: Ignoring the influence of air buoyancy and Coriolis force, according to Newton's second law, at the end of the rocket power flight phase, the mechanical equilibrium equation between the power stage and the load stage is: 。 5. The sounding rocket for realizing automatic stage separation based on aerodynamic drag according to claim 1, characterized in that: The joints are made of high-strength material and can withstand the loads during powered flight.

6. The sounding rocket for realizing automatic stage separation based on aerodynamic drag according to claim 1, characterized in that: The connection between the load stage and the power stage adopts a mortise and tenon structure, in which the butt joint is located at the tail of the load stage.

7. The sounding rocket for realizing automatic stage separation based on aerodynamic drag according to claim 1, characterized in that: Both the payload stage and the power stage are equipped with tail fins at the tail to maintain the stability of the powered flight section.

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