CN215007184U - Two-stage sounding rocket model based on solid engine - Google Patents

Abstract

The utility model relates to a solid engine-based secondary sounding rocket model, which comprises a primary rocket model, a secondary rocket model, a stage section model and a fairing, wherein the primary rocket model comprises a primary rocket shell, a primary rocket engine and a first parachute bay; the second-stage rocket model is arranged above the first-stage rocket model and comprises a second-stage rocket shell, a second-stage rocket engine, a control cabin, an instrument cabin and a second parachute cabin; the stage section model comprises an inter-stage connecting mechanism and an impulse separating device, the inter-stage connecting mechanism is used for connecting the first parachute bay and the second rocket shell, and the impulse separating device can generate explosion to separate the first rocket model and the second rocket model; the fairing is located at the top end of the whole rocket model. The utility model discloses can guarantee rocket flight process's simulation effect, whole model reliability and stability are strong, possess the basic function of real rocket, and reduction degree and analog degree are high, have very strong guiding and practical function to the research and the design of rocket.

Description

Two-stage sounding rocket model based on solid engine

Technical Field

The utility model relates to a second grade sounding rocket model based on solid engine.

Background

The solid two-stage sounding rocket model is a rocket with reduced scale and belongs to a dynamic model. The rocket is pushed to fly by adopting a manually poured small-sized solid rocket engine, the motion states of ignition, rising and recovery of the rocket can be simulated, the launcher of the solid secondary sounding rocket model needs to be launched by a semi-open type launcher, the semi-open type launcher comprises a steel structure, a base and a T-shaped guide rail and a sliding block which are formed by an aluminum structure, the front end of the guide rail is pulled by a steel cable, and meanwhile, the steel cable is fixed by a steel ground nail so as to realize that the front end of the guide rail is vertically upward, ensure that the initial orientation direction of rocket launching is correct, and stably and not generate rocket body spinning.

At present, most rocket models are of empennage-free structures, but the flight speed of the empennage-free rocket model is low, and the empennage-free rocket model only can meet certain ornamental value, most existing rocket models cannot simulate and control flight postures, and the simulation effect of the whole rocket model is strong and satisfactory and far away from the technical indexes and practicability of an actual rocket.

SUMMERY OF THE UTILITY MODEL

The utility model provides a second grade sounding rocket model based on solid engine, its structural design is reasonable, can guarantee rocket flight process's simulation effect, and whole model reliability and stability are strong, possess the basic function of true rocket, and reduction degree and analog degree are high, have very strong guiding and practical function to the research and the design of rocket, have solved the problem that exists among the prior art.

The utility model discloses a solve the technical scheme that above-mentioned technical problem adopted and be: a two-stage space-finding rocket model based on a solid engine, comprising:

the first-stage rocket model comprises a first-stage rocket shell, a first-stage rocket engine and a first parachute bay, wherein a first-stage fixed tail wing is arranged on the outer wall of the first-stage rocket shell, the first-stage rocket engine is arranged inside the first-stage rocket shell, the first parachute bay is arranged at the top of the first-stage rocket shell, a parachute and a power part are arranged inside the first parachute bay, and the power part is used for opening the parachute;

the second-stage rocket model is arranged above the first-stage rocket model and comprises a second-stage rocket shell, a second-stage rocket engine, a control cabin, an instrument cabin and a second parachute cabin; the outer wall of the secondary rocket shell is provided with a secondary fixed tail wing, and a secondary rocket engine is arranged inside the secondary rocket shell; the control cabin is arranged at the top of the secondary rocket shell, a flow guide control surface is arranged on the outer wall of the control cabin, an electric control device and a transmission mechanism are arranged in the control cabin, the transmission mechanism is positioned below the electric control device, the transmission mechanism is connected with a pneumatic control surface, and the pneumatic control surface is positioned below the flow guide control surface; the instrument cabin is arranged at the top of the control cabin, the second umbrella cabin is arranged at the top of the instrument cabin, and the internal structure of the second umbrella cabin is the same as that of the first umbrella cabin;

a stage bay model comprising an inter-stage connection mechanism for connecting the first parachute bay and the secondary rocket hull and an impulse separation device capable of generating an explosion to disconnect the inter-stage connection mechanism and separate the primary rocket model and the secondary rocket model;

and the fairing is arranged at the top of the second parachute bay and is positioned at the top end of the rocket model.

Furthermore, the interstage connection mechanism is provided with a plurality of connection columns which are arranged at intervals along the circumferential outer walls of the first umbrella cabin and the second-stage rocket shell.

Further, the impulse separating device comprises an explosive piece and a separating piece, the explosive piece comprises a sealing tube and gunpowder, the sealing tube is sleeved outside the connecting column, and the gunpowder is filled between the sealing tube and the connecting column; the separating element comprises a supporting tube, a spring and steel balls, the corresponding shell walls of the first parachute bay and the second-stage rocket shell are provided with mutually corresponding limiting columns, the supporting tube is arranged between every two limiting columns, the supporting tube is further internally provided with two steel balls, the spring is arranged between the steel balls, and the spring abuts against the two steel balls on the limiting columns.

Furthermore, the power part is of an air cylinder structure and comprises an air cylinder barrel, a piston is arranged in the air cylinder barrel, and the parachute is arranged between the piston and the air cylinder barrel.

Further, be equipped with the parachute throwing singlechip in the first umbrella cabin, the parachute throwing singlechip links to each other with the parachute throwing detection piece, the separation state of stage section model can be detected to the parachute throwing detection piece, makes the parachute throwing singlechip control power spare action in order to open the parachute.

Furthermore, the connecting column is a nylon connecting column, and the sealing tube is an aluminum tube.

Furthermore, the parachute throwing detection part is an infrared detection module, a detection part matched with the infrared detection module is further arranged at the bottom of the second-stage rocket shell, after the second-stage rocket shell is separated from the second-stage rocket shell, the infrared detection module is separated from the detection part, and the parachute throwing single chip microcomputer receives a signal to start the power part.

Further, an ignition single chip microcomputer is arranged in the control cabin and connected with an electric control initiating explosive, and the electric control initiating explosive is connected with gunpowder of the explosive piece.

Furthermore, the transmission mechanism comprises a plurality of motors, each motor is connected with a driving bevel gear and a driven bevel gear, the driven bevel gears are connected with a rotating shaft, and the rotating shaft penetrates through the shell wall of the control cabin and then is connected with one of the pneumatic control surfaces so as to independently adjust the angle of each pneumatic control surface.

Furthermore, a control single chip microcomputer is arranged in the control cabin and connected with the motors through leads so as to respectively control the angle of the pneumatic control surface.

The utility model adopts the above structure beneficial effect be, whole model is based on solid engine is made, possess one-level rocket model and second grade rocket model, and the design has ingenious complete stage section model between the two-stage rocket model, can realize the controllable separation between connection and the two-stage rocket model in the flight process, and second grade rocket model still designs the adjustment that drive mechanism realized the pneumatic rudder face, realize the flight attitude control of second grade rocket model, and the two-stage rocket model all possesses the function of throwing the umbrella, effectively improve the simulation effect of whole rocket flight process, whole model reliability and stability are strong, possess the basic function of true rocket, reduction and analog are high, research and the design to the rocket have very strong guiding and practical function.

Drawings

Fig. 1 is a schematic view of the structure of the present invention.

Fig. 2 is a schematic sectional view of fig. 1 taken along the direction a-a.

Fig. 3 is a schematic view of the three-dimensional explosion structure of the present invention.

Fig. 4 is a schematic view of the enlarged sectional structure of the present invention.

Fig. 5 is an electrical schematic diagram of the umbrella-throwing single-chip microcomputer of the utility model.

Fig. 6 is an electrical schematic diagram of the ignition single chip microcomputer of the present invention.

Fig. 7 is an electrical schematic diagram of the control single chip microcomputer of the present invention.

In the figure, the position of the upper end of the main shaft,

1. a first-stage rocket model; 101. a first stage rocket shell; 102. a first stage rocket engine; 103. a first umbrella cabin; 104. a first fixed tail; 105. a parachute; 106. a power member;

2. a second stage rocket model; 201. a secondary rocket shell; 202. a secondary rocket engine; 203. a control cabin; 204. an instrument pod; 205. a second umbrella cabin; 206. a secondary fixed tail; 207. a flow guide control surface; 208. an electronic control device; 209. a transmission mechanism; 210. an aerodynamic control surface; 211. a motor; 212. a drive bevel gear; 213. a driven bevel gear; 214. a rotating shaft;

3. a stage section model; 301. an interstage connection mechanism; 302. an impulse separating device; 303. connecting columns; 304. an explosive member; 305. a separating member; 306. a sealing tube; 307. gunpowder; 308. supporting a tube; 309. a spring; 310. steel balls; 311. a limiting column;

4. a cowling;

5. a parachute throwing single chip microcomputer; 501. an umbrella-throwing detection member;

6. an ignition single chip microcomputer; 601. electrically controlled initiating explosive;

7. and controlling the singlechip.

Detailed Description

In order to clearly illustrate the technical features of the present invention, the present invention is explained in detail by the following embodiments in combination with the accompanying drawings.

In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application, however, the present application may be practiced in other ways than those described herein, and therefore the scope of the present application is not limited by the specific embodiments disclosed below.

In addition, in the description of the present application, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", and the like, indicate orientations and positional relationships based on those shown in the drawings, are only for convenience of description and simplicity of description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present application.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.

In this application, unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, removable connections, or integral parts; the connection can be mechanical connection, electrical connection or communication; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

As shown in fig. 1-7, a two-stage exploration rocket model based on a solid engine comprises:

the first-stage rocket model 1 comprises a first-stage rocket shell 101, a first-stage rocket engine 102 and a first parachute bay 103, wherein a first-stage fixed tail fin 104 is arranged on the outer wall of the first-stage rocket shell 101, the first-stage rocket engine 102 is arranged inside the first-stage rocket shell 101, the first parachute bay 103 is arranged at the top of the first-stage rocket shell 101, a parachute 105 and a power part 106 are arranged inside the first parachute bay 103, and the power part 106 is used for opening the parachute 105;

the second-stage rocket model 2 is arranged above the first-stage rocket model 1 and comprises a second-stage rocket shell 201, a second-stage rocket engine 202, a control cabin 203, an instrument cabin 204 and a second parachute cabin 205; the outer wall of the second-stage rocket shell 201 is provided with a second-stage fixed tail wing 206, and a second-stage rocket engine 202 is arranged inside the second-stage rocket shell 201; the control cabin 203 is arranged at the top of the secondary rocket shell 201, the outer wall of the control cabin 203 is provided with a flow guide control surface 207, the control cabin 203 is internally provided with an electric control device 208 and a transmission mechanism 209, the transmission mechanism 209 is positioned below the electric control device 208, the transmission mechanism 209 is connected with a pneumatic control surface 210, and the pneumatic control surface 210 is positioned below the flow guide control surface 207; the instrument cabin 204 is arranged at the top of the control cabin 203, the second umbrella cabin 205 is arranged at the top of the instrument cabin 204, and the internal structure of the second umbrella cabin 205 is the same as that of the first umbrella cabin 103;

the inter-stage section model 3 comprises an inter-stage connecting mechanism 301 and an impulse separating device 302, the inter-stage connecting mechanism 301 is used for connecting the first umbrella cabin 103 and the second rocket shell 201, and the impulse separating device 302 can generate explosion to disconnect the inter-stage connecting mechanism 301 and separate the first rocket model 1 and the second rocket model 2;

and the fairing 4 is arranged at the top of the second parachute bay 205 and is positioned at the top end of the rocket model.

The whole model is made based on the solid engine in the scheme, the system is provided with a first-stage rocket model 1 and a second-stage rocket model 2, a skillful and complete stage section model 3 is designed between the two-stage rocket models, connection in the flight process and controllable separation between the two-stage rocket models can be realized, a transmission mechanism 209 is further designed for the second-stage rocket model 2 to realize adjustment of a pneumatic control surface 210, flight attitude control of the second-stage rocket model 2 is realized, the two-stage rocket models are respectively provided with a first umbrella cabin 103 and a second umbrella cabin 205, the system is provided with the parachute throwing function respectively, the simulation effect of the whole rocket flight process is effectively improved, the whole model is high in reliability and stability, the basic function of a real rocket is realized, the reduction degree and the simulation degree are high, and the research and design of the rocket have strong instructive and practical functions.

In a preferred embodiment, the interstage connection 301 is provided as a plurality of connecting struts 303, the connecting struts 303 being spaced apart along the circumferential outer wall of the first parachute bay 103 and the secondary rocket case 201. In the scheme, the connection of the first-stage rocket model 1 and the second-stage rocket model 2 is realized through the connecting column 303.

In a preferred embodiment, the impulse separating device 302 comprises an explosive member 304 and a separating member 305, the explosive member 304 comprises a sealing tube 306 and gunpowder 307, the sealing tube 306 is sleeved outside the connecting column 303, and the gunpowder 307 is filled between the sealing tube 306 and the connecting column 303; the separating element 305 comprises a supporting tube 309, a spring 309 and steel balls 310, the corresponding shell walls of the first umbrella cabin 103 and the second-stage rocket shell 201 are provided with corresponding limiting columns 311, the supporting tube 308 is arranged between every two limiting columns 311, two steel balls 310 are further arranged in the supporting tube 308, the spring 309 is arranged between the steel balls 310, and the two steel balls 310 are abutted to the limiting columns 311 by the spring 309. In the scheme, after the gunpowder 307 is detonated, the sealing tube 306 and the connecting column 303 are exploded to disconnect the interstage connection mechanism 301, the first-stage rocket model 1 and the second-stage rocket model 2 are separated, in addition, elastic potential energy accumulated by the spring 309 in the separating piece 305 is released by means of the machine, the spring 309 pushes the two steel balls 310 to bounce to two sides and respectively push the limiting columns 311 on the two sides, so that the first umbrella cabin 103 and the second-stage rocket shell 201 are further pushed away by the separating piece, and the interstage separation action is completed.

In the preferred embodiment, the power element 106 is provided as a cylinder structure comprising a cylinder barrel with a piston disposed therein and a parachute 105 disposed between the piston and the cylinder barrel. In the scheme, after the first-stage rocket model 1 and the second-stage rocket model 2 complete interstage separation, the parachute 105 in the first parachute bay 103 can be pushed out and opened through the air cylinder structure of the power part 106, and the first-stage rocket model 1 is recycled. In addition, the internal structure of the second parachute bay 205 adopts the same structure in this scheme, and the parachute inside is pushed out through the cylinder structure.

In a preferred embodiment, the first umbrella cabin 103 is internally provided with the parachute-throwing single-chip microcomputer 5, the parachute-throwing single-chip microcomputer 5 is connected with the parachute-throwing detecting piece 501, and the parachute-throwing detecting piece 501 can detect the separation state of the stage section model 3, so that the parachute-throwing single-chip microcomputer 5 controls the power piece 106 to act to open the parachute 105. Specifically, the parachute opening is automatically controlled by designing the parachute throwing single-chip microcomputer 5 and the parachute throwing detection piece 501.

In the preferred embodiment, the connecting column 303 is provided as a nylon connecting column and the sealing tube 306 is provided as an aluminum tube. The spliced pole 303 adopts the nylon material preparation, can guarantee firstly that the spliced pole is to the joint strength and the stability of one-level rocket model 1 and second grade rocket model 2, secondly can alleviate spliced pole 303 self weight, subtracts heavy to whole rocket model, practices thrift power, thirdly makes things convenient for the impact force disconnection by gunpowder 307 explosion. Further, the sealing tube 306 is an aluminum tube, which can maintain light weight while ensuring sufficient sealing and pressure effects.

In a preferred embodiment, the parachute throwing detection part 501 is an infrared detection module, the bottom of the secondary rocket shell 201 is further provided with a detection part matched with the infrared detection module, after the secondary rocket shell 3 is separated, the infrared detection module is separated from the detection part, and the parachute throwing single-chip microcomputer 5 receives a signal to start the power part 106. In this scheme, whether utilize infrared detection module to realize separating the detection to one-level rocket model 1 and second grade rocket model 2 to can transmit the separation signal to parachute throwing singlechip 5, and then realize the control to power part 106, open parachute 105 automatically.

In the preferred embodiment, an ignition single chip microcomputer 6 is arranged in the control cabin 203, the ignition single chip microcomputer 6 is connected with an electric control initiating explosive 601, and the electric control initiating explosive 601 is connected with gunpowder 307 of the explosive element 304.

In a preferred embodiment, the transmission mechanism 209 includes a plurality of motors 211, each motor 211 is connected with a driving bevel gear 212 and a driven bevel gear 213, the driven bevel gear 213 is connected with a rotating shaft 214, and the rotating shaft 214 passes through the wall of the control cabin 203 and then is connected with one of the aerodynamic control surfaces 210, so as to adjust the angle of each aerodynamic control surface 210 individually.

In the preferred embodiment, a control single chip microcomputer 7 is arranged in the control cabin 203, and the control single chip microcomputer 7 is connected with a plurality of motors 211 through leads so as to respectively control the angle of the pneumatic control surface 210. When in use, the transmission mechanism 209 controls the differential gear to operate the pneumatic control surface 210 by controlling the singlechip 7 and the motor 211 so as to achieve the effect of stable flight; the pitch angle, the yaw angle and the rolling angle of the model rocket are measured in real time by using the gyroscope, data are sent to the control single chip microcomputer 7 in real time through a serial port for attitude calculation, the control single chip microcomputer 7 performs attitude calculation, four paths of two identical PWM waves are output through an amplitude limiting method, the four motors 211 are controlled in real time, the motors 211 realize power direction conversion through a 90-degree bevel gear transmission set, and accurate control over the pneumatic control surface 210 is realized.

The above-mentioned specific embodiments can not be regarded as the restriction to the scope of protection of the utility model, to technical personnel in this technical field, it is right the utility model discloses any replacement improvement or transform that embodiment made all fall within the scope of protection of the utility model.

The parts of the present invention not described in detail are the known techniques of those skilled in the art.

Claims (10)

1. A two-stage sounding rocket model based on a solid engine is characterized by comprising:

the first-stage rocket model comprises a first-stage rocket shell, a first-stage rocket engine and a first parachute bay, wherein a first-stage fixed tail wing is arranged on the outer wall of the first-stage rocket shell, the first-stage rocket engine is arranged inside the first-stage rocket shell, the first parachute bay is arranged at the top of the first-stage rocket shell, a parachute and a power part are arranged inside the first parachute bay, and the power part is used for opening the parachute;

the second-stage rocket model is arranged above the first-stage rocket model and comprises a second-stage rocket shell, a second-stage rocket engine, a control cabin, an instrument cabin and a second parachute cabin; the outer wall of the secondary rocket shell is provided with a secondary fixed tail wing, and a secondary rocket engine is arranged inside the secondary rocket shell; the control cabin is arranged at the top of the secondary rocket shell, a flow guide control surface is arranged on the outer wall of the control cabin, an electric control device and a transmission mechanism are arranged in the control cabin, the transmission mechanism is positioned below the electric control device, the transmission mechanism is connected with a pneumatic control surface, and the pneumatic control surface is positioned below the flow guide control surface; the instrument cabin is arranged at the top of the control cabin, the second umbrella cabin is arranged at the top of the instrument cabin, and the internal structure of the second umbrella cabin is the same as that of the first umbrella cabin;

a stage bay model comprising an inter-stage connection mechanism for connecting the first parachute bay and the secondary rocket hull and an impulse separation device capable of generating an explosion to disconnect the inter-stage connection mechanism and separate the primary rocket model and the secondary rocket model;

and the fairing is arranged at the top of the second parachute bay and is positioned at the top end of the rocket model.

2. A solid engine-based two-stage sounding rocket model according to claim 1, wherein the inter-stage connection mechanism is provided as a plurality of connection columns spaced along the circumferential outer wall of the first parachute bay and the second stage rocket case.

3. A solid engine-based two-stage sounding rocket model according to claim 2, wherein said impulse separating means comprises an explosive member and a separating member, said explosive member comprises a sealed tube and gunpowder, said sealed tube is sleeved outside said connecting column, and said gunpowder is filled between said sealed tube and said connecting column; the separating element comprises a supporting tube, a spring and steel balls, the corresponding shell walls of the first parachute bay and the second-stage rocket shell are provided with mutually corresponding limiting columns, the supporting tube is arranged between every two limiting columns, the supporting tube is further internally provided with two steel balls, the spring is arranged between the steel balls, and the spring abuts against the two steel balls on the limiting columns.

4. The solid engine-based two-stage sounding rocket model according to claim 1, wherein the power member is a cylinder structure comprising a cylinder barrel, a piston is arranged in the cylinder barrel, and the parachute is arranged between the piston and the cylinder barrel.

5. The solid engine-based two-stage sounding rocket model according to claim 1 or 4, wherein a parachute throwing single-chip microcomputer is arranged in the first parachute cabin, the parachute throwing single-chip microcomputer is connected with a parachute throwing detection piece, the parachute throwing detection piece can detect the separation state of the stage section model, and the parachute throwing single-chip microcomputer controls the power piece to act so as to open the parachute.

6. A solid engine-based two-stage sounding rocket model according to claim 3, wherein said connecting columns are nylon connecting columns and said sealed tubes are aluminum tubes.

7. A two-stage sounding rocket model based on a solid engine according to claim 5, characterized in that the parachute-throwing detection piece is an infrared detection module, the bottom of the two-stage rocket shell is further provided with a detection part matched with the infrared detection module, after the two-stage rocket shell is separated, the infrared detection module is separated from the detection part, and the parachute-throwing singlechip receives a signal to start the power piece.

8. A two-stage sounding rocket model based on solid engine according to claim 3, wherein an ignition single chip microcomputer is arranged in the control cabin, the ignition single chip microcomputer is connected with an electrically controlled initiating explosive, and the electrically controlled initiating explosive is connected with gunpowder of the explosive member.

9. The solid engine-based two-stage sounding rocket model according to claim 1, wherein the transmission mechanism comprises a plurality of motors, each motor is connected with a driving bevel gear and a driven bevel gear, the driven bevel gear is connected with a rotating shaft, and the rotating shaft passes through the wall of the control cabin and is connected with one of the pneumatic control surfaces, so as to adjust the angle of each pneumatic control surface independently.

10. The solid engine-based two-stage sounding rocket model according to claim 9, wherein a control single chip microcomputer is disposed in the control cabin, and the control single chip microcomputer is connected to the plurality of motors through wires to control the angles of the pneumatic control surfaces respectively.

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