CN219167700U - Uncontrolled model rocket based on split type parachute opening recovery mechanism - Google Patents

Abstract

The utility model discloses a non-control model rocket based on a split type parachute opening recovery mechanism, which relates to the technical field of rocket models and comprises a rocket shell, wherein the rocket shell comprises a fairing mechanism, a rudder cabin, an electric control cabin and a power cabin, the fairing mechanism comprises an actuating nose cone and a fixed shaft nose cone, one side of the fairing mechanism is sleeved with the rudder cabin, the rudder cabin comprises a rudder cabin shell, a rudder cabin support frame is arranged in the rudder cabin shell, and the actuating nose cone is rotationally connected with the rudder cabin support frame through an actuating nose cone positioning pin, and the utility model has the beneficial effects that: the steering engine body controls the opening and the closing, the fairing mechanism consists of an actuating nose cone and a fixed shaft nose cone, the fairing mechanism is axially arranged at the top of the rocket, when the parachute is ready to be opened, the steering engine body drives the actuating nose cone to open and release the parachute, the nose cone adopts a curved surface reinforcement design, the parachute opening mode is stable and reliable, and the internal accommodating space is large.

Description

Uncontrolled model rocket based on split type parachute opening recovery mechanism

Technical Field

The utility model relates to the technical field of rocket models, in particular to a non-control model rocket based on a split parachute opening recovery mechanism.

Background

Recently, with successful launch of long-sign series carrier rockets and subsequent deployment of Chinese space stations, enthusiasm of the society for rocket technology is increasing. But the basic teaching tools are rare, professional science and education equipment is deficient, the basic teaching tools are mainly overview of the development process of Chinese spaceflight, the science popularization explanation of rocket systems and the manufacture of simple water rockets in the social level, the relevant overview and explanation are difficult to enable listeners to have real specific contact and experience, the water rocket model is lack of more modules compared with the real rocket systems, the teaching staff can deeply discover the thermodynamic and kinetic knowledge is limited, so that the current situation that the content of surface knowledge is low and the teaching staff is only used for entertainment science popularization is caused, and the learning requirement of high-level audience is difficult to meet. For universities with aerospace related professions, theoretical teaching is mainly used in teaching at present, experimental teaching is seriously lacking at ordinary times, particularly links of personally designing and manufacturing an aircraft model and performing visual flight tests are lacking, so that most universities lack knowledge of rocket systems, wide structures and mechanisms applied to the aircraft cannot be designed, visual understanding and knowledge of common processing and forming manufacturing methods are lacking, and scientific research work close to practical application is difficult to perform. According to the Chinese patent application number: CN113577789a discloses a modular assembled model rocket, which comprises a fairing, an upper cabin section, a cabin section support, an upper bottle mouth, a cylinder section, an upper adapter ring, a lower bottle mouth, a tail support, a tail and a bottle stopper, wherein the fairing is connected with the upper cabin section, and the cabin section support is arranged at the end part of the upper cabin section.

The utility model mainly focuses on a modularized model water rocket with high playability and convenient assembly, is mainly aimed at children receiving spaceflight science popularization education, has simpler appearance, lacks contrast to a real rocket system in structure, and can not meet the application and emission test of high-level teaching hierarchy because the driving energy is preloaded with high-pressure gas. In addition, the umbrella opening mode of the utility model is quite traditional and lacks a mechanism innovation design.

Disclosure of Invention

Aiming at the defects of the prior art, the utility model provides a non-control model rocket based on a split type parachute opening recovery mechanism, which solves the problems in the prior art.

In order to achieve the above purpose, the utility model is realized by the following technical scheme: the utility model provides a no accuse model rocket based on split type parachute opening recovery mechanism, includes the rocket casing, the rocket casing includes radome fairing mechanism, rudder cabin, automatically controlled cabin and power cabin, the radome fairing mechanism is including actuating nose cone and dead axle nose cone, rudder cabin has been cup jointed to one side of radome fairing mechanism, rudder cabin includes the rudder cabin casing, the inside of rudder cabin casing is provided with rudder cabin support frame, actuating nose cone rotates with rudder cabin support frame through actuating nose cone locating pin and is connected, the dead axle nose cone rotates through dead axle nose cone locating pin and is connected with rudder cabin support frame, one side of actuating nose cone is provided with the location drive piece, the inside of rudder cabin support frame is provided with the steering engine body, the output of steering engine body is connected with the rudder angle, the inside of rudder cabin support frame is provided with drive screw, drive screw runs through the location drive piece, the inner chamber of radome fairing mechanism can place the parachute.

Preferably, one side of rudder cabin has cup jointed automatically controlled cabin, automatically controlled cabin includes automatically controlled cabin casing, automatically controlled cabin upper bracket frame and automatically controlled cabin lower carriage frame are provided with respectively at the both ends of automatically controlled cabin casing, the inside of automatically controlled cabin casing is provided with control panel, battery and connection carbon pole respectively, the outside of automatically controlled cabin casing is provided with automatically controlled hatch board.

Preferably, one side of the electric control cabin is sleeved with a power cabin, the power cabin comprises a power cabin shell, a plurality of tail wings are arranged on the outer side of the power cabin shell, the tail wings are printed by nylon, an engine front seal head and an engine rear seal head are respectively arranged in the power cabin shell, and an engine shell, a spray pipe throat liner, an engine spray pipe and a grain are respectively arranged in the power cabin shell.

Preferably, the material of the fairing mechanism is photosensitive resin or PLA material, the appearance is conical or elliptic, and the fairing mechanism is formed by adopting a photo-curing or fused deposition type printing technology.

The utility model provides a non-control model rocket based on a split type parachute opening recovery mechanism, which has the following beneficial effects:

the model rocket without control based on the split type parachute opening and recovering mechanism is controlled to open and close by a steering engine body, a fairing mechanism consists of an actuating nose cone and a fixed nose cone, the steering engine body is axially arranged at the top of the rocket, the steering engine body drives the actuating nose cone to open and release a parachute when the parachute is ready to open, the nose cone adopts a curved surface reinforcement design, the parachute opening mode is stable and reliable, the internal accommodating space is large, the scheme adopts a modularized design, and all parts in the model are approximately opposite to all systems of the standard rocket. The main components of the rocket are commercial spot, the design, manufacturing and assembly processes and the required expertise are similar to those of developing a large rocket, and the rocket can be used for carrying out a launch test on a campus site, so that the problems of rare practical aerospace science popularization and lack of aircraft teaching tools are effectively solved.

Drawings

FIG. 1 is a schematic diagram of the structure of the present utility model;

fig. 2 is a cross-sectional view of the present utility model.

In the figure: 1. actuating the nose cone; 2. fixing a shaft nose cone; 3. actuating the nose cone positioning nail; 4. positioning nails with fixed shaft heads and cones; 5. positioning a driving block; 6. rudder cabin bracket frame; 7. steering engine body; 8. rudder angle; 9. driving the screw; 10. rudder cabin shell; 11. an upper support frame of the electric control cabin; 12. an electric control cabin lower bracket frame; 13. connecting a carbon rod; 14. a control board; 15. a battery; 16. an electric control cabin shell; 17. an electric control hatch cover; 18. an engine front end socket; 19. an engine housing; 20. an engine rear end enclosure; 21. a nozzle throat insert; 22. an engine nozzle; 23. a grain; 24. a power cabin housing; 25. a tail wing; 26. a fairing mechanism; 27. a rudder trunk; 28. an electric control cabin; 29. a power cabin; 30. rocket hull.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments.

Referring to fig. 1 to 2, a control-free model rocket based on a split parachute opening recovery mechanism comprises a rocket shell 30, wherein the rocket shell 30 comprises a fairing mechanism 26, a rudder cabin 27, an electric control cabin 28 and a power cabin 29, the fairing mechanism 26 comprises an actuating nose cone 1 and a dead axle nose cone 2, one side of the fairing mechanism 26 is sleeved with the rudder cabin 27, the rudder cabin 27 comprises a rudder cabin shell 10, a rudder cabin support frame 6 is arranged in the rudder cabin shell 10, the actuating nose cone 1 is rotationally connected with the rudder cabin support frame 6 through an actuating nose cone locating pin 3, the dead axle nose cone 2 is rotationally connected with the rudder cabin support frame 6 through a dead axle nose cone locating pin 4, one side of the actuating nose cone 1 is provided with a locating driving block 5, the inside of the rudder cabin support frame 6 is provided with a steering engine body 7, an output end of the steering engine body 7 is connected with a rudder angle 8, the inside of the rudder cabin support frame 6 is provided with a driving screw 9, the driving screw 9 penetrates through the positioning driving block 5, the steering engine body 7 can receive a control signal from the control panel 14 to actuate, the driving screw 9 penetrates through the positioning driving block 5 and is screwed into a rudder angle 8 arranged on a rotating shaft of the steering engine body 7, the rotating shaft of the steering engine body 7 anticlockwise actuates to drive the positioning driving block 5 to move upwards, the driving nose cone 1 moves upwards and rotates outwards, then the driving nose cone 2 loses the restraint of the driving nose cone 1, only the rotation freedom degree of the left root part is left, the fairing mechanism 26 is divided into two petals, the parachute arranged in the interior is naturally opened under the action of windward, stable parachute recovery is realized, the inner cavity of the fairing mechanism 26 can be used for placing the parachute, the parachute consists of a parachute face and a parachute rope, the speed reduction and the instantaneous kinetic energy absorption of the parachute opening during rocket recovery are used, one side of the rudder cabin 27 is sleeved with the electric control cabin 28, the electric control cabin 28 comprises an electric control cabin shell 16, two ends of the electric control cabin shell 16 are respectively provided with an electric control cabin upper support frame 11 and an electric control cabin lower support frame 12, a control board 14, a battery 15 and a connecting carbon rod 13 are respectively arranged in the electric control cabin shell 16, an electric control hatch cover 17 is arranged on the outer side of the electric control cabin shell 16, when a burning program or battery 15 replacement is needed, the electric control hatch cover 17 can be detached, the electric control cabin shell 16 can be operated, three connecting carbon rods 13 are used for compensating rigidity loss caused by detachment of the electric control hatch cover 17, a power cabin 29 is sleeved on one side of the electric control cabin 28, the power cabin 29 comprises a power cabin shell 24, a plurality of tail fins 25 are arranged on the outer side of the power cabin shell 24, nylon printing is adopted by the plurality of tail fins 25, an engine front end enclosure 18 and an engine rear end enclosure 20 are respectively arranged in the power cabin shell 24, an engine shell 19, a spray pipe throat liner 21, an engine spray pipe 22 and a medicine column 23 are respectively arranged in the power cabin shell 24. Meanwhile, four stable tail fins 25 defined by a root chord, a tip chord, a height and a sweepback angle are adopted, so that the stable tail fin has good static stability, namely a stable flying trajectory, a high safety coefficient, is suitable for being launched in multiple fields, can meet various activity requirements, is made of photosensitive resin or PLA (polylactic acid) materials, is conical or elliptical in shape, is formed by adopting a photo-curing or fused deposition printing technology, and is designed by adopting a curved surface reinforcement design, so that the thickness of a wall surface is reduced while certain strength and rigidity are ensured, the weight of the nose cone is reduced, the assembled whole has industrial aesthetic texture, an umbrella opening mode is stable and reliable, and the internal accommodating space is large.

In summary, when the split type parachute-opening recovery mechanism-based uncontrolled model rocket is used, the steering engine body 7 can receive a control signal from the control panel 14 to actuate, the driving screw 9 penetrates through the positioning driving block 5 and is screwed into the rudder angle 8 arranged on the rotating shaft of the steering engine body 7, the rotating shaft of the steering engine body 7 is actuated anticlockwise to drive the positioning driving block 5 to move upwards and rotate outwards, the movable nose cone 1 is driven to move upwards and rotate outwards, then the fixed nose cone 2 loses the constraint of the movable nose cone 1, only the rotational freedom degree of the root is left, the fairing mechanism 26 is divided into two petals, and the parachute arranged inside is naturally opened under the action of windward, so that stable landing recovery is realized.

The foregoing is only a preferred embodiment of the present utility model, but the scope of the present utility model is not limited thereto, and any person skilled in the art, who is within the scope of the present utility model, should make equivalent substitutions or modifications according to the technical scheme of the present utility model and the inventive concept thereof, and should be covered by the scope of the present utility model.

Claims (4)

1. The utility model provides a no accuse model rocket based on split parachute opening recovery mechanism, includes rocket case (30), its characterized in that: rocket case (30) includes radome fairing mechanism (26), rudder cabin (27), automatically controlled cabin (28) and power cabin (29), radome fairing mechanism (26) are including actuating nose cone (1) and dead axle nose cone (2), rudder cabin (27) have been cup jointed to one side of radome fairing mechanism (26), rudder cabin (27) include rudder cabin case (10), the inside of rudder cabin case (10) is provided with rudder cabin support frame (6), actuating nose cone (1) through actuating nose cone locating pin (3) and rudder cabin support frame (6) rotation connection, dead axle nose cone (2) through dead axle nose cone locating pin (4) and rudder cabin support frame (6) rotation connection, one side of actuating nose cone (1) is provided with location drive piece (5), the inside of rudder cabin support frame (6) is provided with steering wheel body (7), the output of steering wheel body (7) is connected with rudder angle (8), the inside of rudder cabin support frame (6) is provided with rudder cabin support frame (9), but driving screw (26) are placed in inner chamber (9), but driving screw (26) are placed.

2. The uncontrolled model rocket based on a split parachute-opening recovery mechanism of claim 1, wherein: one side of rudder cabin (27) has cup jointed automatically controlled cabin (28), automatically controlled cabin (28) are including automatically controlled cabin casing (16), automatically controlled cabin upper bracket frame (11) and automatically controlled cabin lower carriage frame (12) are provided with respectively at the both ends of automatically controlled cabin casing (16), the inside of automatically controlled cabin casing (16) is provided with control panel (14), battery (15) and connection carbon pole (13) respectively, the outside of automatically controlled cabin casing (16) is provided with automatically controlled hatch board (17).

3. The uncontrolled model rocket based on a split parachute-opening recovery mechanism of claim 1, wherein: one side of automatically controlled cabin (28) has cup jointed power cabin (29), power cabin (29) include power cabin casing (24), the outside of power cabin casing (24) is provided with a plurality of fin (25), and is a plurality of fin (25) adopt nylon to print, the inside of power cabin casing (24) is provided with engine front end enclosure (18) and engine rear end enclosure (20) respectively, engine casing (19), spray pipe throat liner (21), engine spray pipe (22) and grain (23) are installed respectively to the inside of power cabin casing (24).

4. The uncontrolled model rocket based on a split parachute-opening recovery mechanism of claim 1, wherein: the fairing mechanism (26) is made of photosensitive resin or PLA material, and is conical or elliptical in shape and is formed by adopting a photo-curing or fused deposition printing technology.

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