CN113018881B - Aerospace science popularization model self-adaptive ejection device - Google Patents
Aerospace science popularization model self-adaptive ejection device Download PDFInfo
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- CN113018881B CN113018881B CN202110451088.9A CN202110451088A CN113018881B CN 113018881 B CN113018881 B CN 113018881B CN 202110451088 A CN202110451088 A CN 202110451088A CN 113018881 B CN113018881 B CN 113018881B
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/14—Starting or launching devices for toy aircraft; Arrangements on toy aircraft for starting or launching
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H33/00—Other toys
- A63H33/42—Toy models or toy scenery not otherwise covered
- A63H33/425—Toy space systems, e.g. satellites, space ships
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- Portable Nailing Machines And Staplers (AREA)
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Abstract
The invention discloses a self-adaptive ejection device of an aerospace popular model, which comprises a support base, an installation main frame, a guide support plate, a starting ejection assembly and a slope auxiliary guide piece, wherein the support base is riveted on the lower end face of the installation main frame through a rivet and is stably erected on the ground through the support base, and the guide support plate is installed on the upper end face of the installation main frame; the guide support plate can be arranged on the installation main frame in a relatively deflecting mode and is used as a jump track of the aerospace model; the starting ejection assembly is fixed on one side of the upper end face of the guide support plate and used for providing ejection starting power for the aerospace model so that the aerospace model can reach pre-flying speed to perform aerospace flight simulation before being separated from the guide support plate; and a slope auxiliary guide part is arranged on one side of the guide support plate, which is far away from the starting ejection assembly.
Description
Technical Field
The invention relates to the technical field of aerospace science popularization model equipment, in particular to a self-adaptive ejection device for an aerospace science popularization model.
Background
The development of aerospace is closely related to military application, and has great influence on various departments of national economy and many aspects of social life, so that the appearance of the world is changed; although aerospace plays a crucial role in economic development, scientific development and daily life, people generally know little about aerospace knowledge at present, more people need to know about aerospace knowledge, and aerospace related knowledge is popularized, various aerospace model props are used for science popularization simulation display at present, ejection power of most aerospace model props cannot achieve the effect of practical simulation tests, so that aerospace concepts cannot be clearly carried through in display teaching, initial positioning support on a model body is lost in general aerospace model flight tests, aviation stability in aerospace simulation tests is poor, and flight measurement data deviation is large, and therefore a self-adaptive ejection device for aerospace science popularization models is needed to be provided to solve the problems.
Disclosure of Invention
In order to achieve the purpose, the invention provides the following technical scheme: an aerospace popular model self-adaptive ejection device comprises a support base, an installation main frame, a guide support plate, a starting ejection assembly and a slope auxiliary guide piece, wherein the support base is riveted on the lower end face of the installation main frame through rivets and is stably erected on the ground through the support base, and the guide support plate is installed on the upper end face of the installation main frame;
the guide support plate can be arranged on the installation main frame in a relatively deflecting mode and is used as a jump track of the aerospace model;
the starting ejection assembly is fixed on one side of the upper end face of the guide support plate and used for providing ejection starting power for the aerospace model so that the aerospace model can reach pre-flying speed to perform aerospace flight simulation before being separated from the guide support plate;
and a slope auxiliary guide part is arranged on one side of the guide support plate, which is far away from the starting ejection assembly, the starting end surface of the slope auxiliary guide part is flush with the end surface of the guide support plate, and a take-off slope is provided for the aerospace model when the aerospace model is about to be separated from the guide support plate.
As a preferred technical scheme of the invention, the middle part of the lower end face of the mounting main frame is provided with a rotary screw rod which can relatively rotate through a fixing part, the rotary screw rod is provided with a connecting support part which can relatively slide through a thread meshing effect, the lower end face of the mounting main frame is provided with a driving motor, and the output end of the driving motor is connected and fixed with the rotary screw rod;
the installation main frame is provided with a rotary shaft seat, and the guide support plate can be hinged on the rotary shaft seat in a relative deflection way;
and a support column is hinged to the lower portion of one side, away from the rotary shaft seat, of the guide support plate, one end of the support column is connected with the connecting support piece, and the support column is driven by the connecting support piece to obliquely bear the guide support plate.
As a preferred technical scheme of the invention, the upper end surface of the mounting main frame is provided with a strip-shaped slide position, and the limit of the relative sliding of the rotary shaft seat is arranged in the strip-shaped slide position;
a connecting cross bar is transversely fixed on the middle side in the guide support plate, a bearing frame is arranged on the connecting cross bar in a relatively sliding manner, and the guide support plate is rotatably connected to the rotary shaft seat through the bearing frame;
the starting ejection assembly is fixed on the bearing frame and transversely slides along the guide support plate by the bearing frame so as to effectively regulate and control the horizontal distance between the starting ejection assembly and the slope auxiliary guide piece.
As a preferred technical scheme of the invention, the starting ejection assembly comprises a connecting column, a fixed frame body, a winding wheel, an auxiliary guide wheel, a built-in spring, a guide driving piece and a fixed rail frame, wherein the fixed rail frame is transversely fixed on the bearing frame, the guide driving piece is arranged in the fixed rail frame in a manner of relatively transversely sliding, and the guide driving piece is used for bearing and erecting an aerospace model;
a connecting column body is vertically arranged on the fixed rail frame, one side of the connecting column body is rotatably connected with a winding wheel through a fixed frame body, and a nylon rope is wound on the winding wheel;
a plurality of auxiliary guide wheels are vertically arranged on the other side of the connecting column body in a row, and a nylon rope is arranged between the auxiliary guide wheels in a penetrating manner and is connected with the guide driving piece;
a plurality of built-in springs are arranged in the fixed rail frame, and the built-in springs provide flight ejection power for the aerospace model through the elastic force.
As a preferred technical scheme of the invention, the guide driving part comprises a bearing disc, a driving main part, a traction buffering device, a locking part and an auxiliary ejection assembly, wherein the driving main part is arranged on the lower end surface of the bearing disc and is limited by the driving main part to slide in the fixed rail frame;
a traction buffer device is arranged on one side of the driving main part, which is far away from the built-in spring, and the traction buffer device performs traction buffering on the end part of the driving main part after the driving main part starts to eject under the action of elastic force;
therefore, the bearing disc is internally provided with a locking fastener for initially locking the driving wheel of the aerospace model;
and the auxiliary ejection assembly is arranged on the same side of the bearing disc, which is positioned on the built-in spring, and provides starting and disengaging power for the end part of the aerospace model, so that when the locking fastener stops locking the driving wheel, the auxiliary ejection assembly transversely pushes the aerospace model to drive away from the bearing disc.
As a preferred technical scheme of the present invention, the traction buffering device includes an upper guide wheel, a support rod member, an upper link rod, a damping spring and a front guide wheel, wherein the support rod member is obliquely fixed on one side of the driving main member, the support rod member is provided with the upper guide wheel which is in fit with and drives the upper inner wall of the fixed rail frame, the support rod member is provided with the upper link rod which can relatively deflect, and the upper link rod is rotatably provided with the front guide wheel;
and a damping spring is further connected between the driving main part and the upper connecting rod, and the damping spring is used for pressing the part of the front guide wheel to incline upwards under the action of elasticity.
As a preferable technical solution of the present invention, a stop body is further disposed on one side of the fixed rail frame, and an inner wall of a cross section of the stop body is of an arc structure.
As a preferred technical scheme of the invention, the locking fastener further comprises a poke rod, an inner transfer rod, a main clamping seat and an auxiliary clamping piece, wherein the main clamping seat is installed in the driving main piece, the auxiliary clamping piece is arranged on the main clamping seat in a relatively rotatable manner, and the auxiliary clamping piece is mutually matched with the main clamping seat under the action of the elastic force of a connecting spring to form a clamping state;
a poke rod is arranged in the driving main part and can deflect relatively, an inner transmission rod is hinged to one end of the poke rod and connected with the auxiliary clamping part, and the auxiliary clamping part and the main clamping seat are controlled to be opened and closed under the pushing of the poke rod;
one side of keeping away from built-in spring in the fixed track frame is equipped with spacing spout, the one end of poker rod can slide along spacing spout.
As a preferred technical scheme of the invention, the auxiliary ejection assembly comprises an external pump element, a sealing guide element, a transmission shaft plug and a conveying branch pipe, wherein the sealing guide element is transversely arranged on the bearing disc, and the transmission shaft plug is arranged in the sealing guide element in a relatively sliding manner;
and a delivery branch pipe is connected below one side of the sealing guide piece, and one end of the delivery branch pipe is communicated with an external pump piece.
Compared with the prior art, the invention provides an aerospace science popularization model self-adaptive ejection device, which has the following beneficial effects:
according to the invention, the guidance support plate simulates an catapult-assisted take-off channel of aviation flight, and the launch-assisted take-off component provides launch-assisted power for the model by placing the aerospace model in the launch-assisted take-off component, so that the aerospace model can realize aviation stable simulated flight along the guidance support plate and through a slope auxiliary guide part; the lower end face of the guide support plate is hinged with a support column, and the support column is driven by the connecting support piece through a thread meshing effect to support the inclined plane of the guide support plate, so that the slope of the inclined plane of the channel is regulated and controlled; a rotary shaft seat is also arranged on the lower end face of the guide support plate in a sliding manner, and the starting ejection assembly is erected above the guide support plate through the rotary shaft seat so as to adjust the pre-flying distance of the aerospace model; the starting ejection assembly also comprises a traction buffer device used for buffering the end part of the driving main part after ejection and take-off; the lock catch piece is used for carrying out preliminary positioning locking connection on the guide wheel of the aerospace model so as to keep the stability of the guide wheel of the aerospace model in the initial ejection starting state and the pre-flying state, and the auxiliary ejection assembly is used for ejecting the lock catch piece on the way of pre-flying the aerospace model and is used as auxiliary ejection power.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of a support column according to the present invention;
FIG. 3 is a schematic structural view of the receiving frame of the present invention;
fig. 4 is a schematic structural diagram of the starting ejection assembly in the invention;
FIG. 5 is a schematic view of the configuration of the guide drive of the present invention;
FIG. 6 is an enlarged view of the point A in FIG. 5;
fig. 7 is a schematic structural view of the locking member and the auxiliary ejection assembly of the present invention;
in the figure: the device comprises a main mounting frame 1, a 101 supporting base, a 102 rotating shaft seat, a 103 rotating screw rod, a 104 driving motor, a 105 connecting support, a 106 supporting column, a 2 guiding support plate, a 201 connecting cross bar, a 202 bearing frame, a 3 starting ejection assembly, a 301 fixing rail frame, a 302 connecting column, a 303 fixing frame body, a 304 winding wheel, a 305 auxiliary guide wheel, a 306 built-in spring, a 4-slope auxiliary guide piece, a 5 guiding driving piece, a 501 driving main piece, a 502 bearing disc, a 6 traction buffering device, a 601 supporting rod piece, a 602 upper guide wheel, a 603 upper connecting rod, a 604 front guide wheel, a 605 damping spring, a 7 locking piece, a 701 main clamping seat, a 702 auxiliary clamping piece, a 703 poking rod, a 704 inner transmission rod, an 8 auxiliary ejection assembly, a 801 sealing guide piece, an 802 plug, a 803 transmission branch pipe and a 9 stopping body.
Detailed Description
Referring to fig. 1, the present invention provides a technical solution: an aerospace science popularization model self-adaptive ejection device comprises a supporting base 101, an installation main frame 1, a guide support plate 2, a starting ejection assembly 3 and a slope auxiliary guide member 4, wherein the supporting base 101 is riveted on the lower end face of the installation main frame 1 through rivets, the supporting base 101 is stably erected on the ground, and the guide support plate 2 is installed on the upper end face of the installation main frame 1;
the guide support plate 2 is arranged on the installation main frame 1 in a relatively deflecting manner and is used as a jump track of the aerospace model;
the starting ejection assembly 3 is fixed on one side of the upper end face of the guide support plate 2, and the starting ejection assembly 3 is used for providing ejection starting power for the aerospace model so that the aerospace model can reach the pre-flying speed before being separated from the guide support plate 2 to carry out aerospace flight simulation;
a slope auxiliary guide part 4 is arranged on one side, far away from the starting ejection component 3, of the guide support plate 2, the starting end face of the slope auxiliary guide part 4 is flush with the end face of the guide support plate 2, and a take-off slope is provided for the aerospace model when the aerospace model is about to break away from the guide support plate 2.
Referring to fig. 2, in this embodiment, a rotating screw 103 is relatively rotatably disposed in the middle of the lower end surface of the mounting main frame 1 through a fixing member, a connecting support member 105 is relatively slidably disposed on the rotating screw 103 through a thread engagement, a driving motor 104 is mounted on the lower end surface of the mounting main frame 1, and an output end of the driving motor 104 is connected and fixed to the rotating screw 103;
the installation main frame 1 is provided with a rotary shaft seat 102, and the guide support plate 2 is hinged on the rotary shaft seat 102 in a manner of relative deflection; the adjustable rotating angle range of the guide support plate is between-10 degrees and 45 degrees, so that the aviation test under most conditions can be effectively simulated;
and a support column 106 is hinged to the lower portion of one side of the guide support plate 2, which is far away from the rotating shaft seat, one end of the support column 106 is connected with the connecting support piece 105, and the connecting support piece 105 drives the support column 106 to obliquely carry the guide support plate 2.
Referring to fig. 3, in this embodiment, a strip-shaped sliding position is arranged on the upper end surface of the installation main frame 1, and the rotation shaft seat 102 is limited in the strip-shaped sliding position in a relatively sliding manner;
a connecting cross bar 201 is transversely fixed on the middle side inside the guide support plate 2, a bearing frame 202 is arranged on the connecting cross bar 201 in a relatively sliding manner, and the guide support plate 2 is rotatably connected to the rotary shaft seat 102 through the bearing frame 202;
the starting ejection component 3 is fixed on the bearing frame 202, and the bearing frame 202 slides transversely along the guide support plate 2, so that the horizontal distance between the starting ejection component 3 and the slope auxiliary guide 4 can be effectively regulated and controlled.
Referring to fig. 4, in this embodiment, the starting ejection assembly 3 includes a connecting cylinder 302, a fixed frame 303, a winding wheel 304, an auxiliary guide wheel 305, an internal spring 306, a guiding driving element 5, and a fixed rail frame 301, where the fixed rail frame 301 is transversely fixed on the receiving frame 202, the guiding driving element 5 is arranged inside the fixed rail frame 301 in a manner of being relatively slidable transversely, and the guiding driving element 5 is used for carrying and erecting an aerospace model;
a connecting column 302 is vertically arranged on the fixed rail frame 301, one side of the connecting column 302 is rotatably connected with a winding wheel 304 through a fixed frame body 303, and a nylon rope is wound on the winding wheel 304; it should be noted that the nylon rope is used as a traction end of the launch starting power, and a high-strength hard-to-break smooth rope is adopted to prevent a broken joint or fatigue wear in the launch preparation process;
a plurality of auxiliary guide wheels 305 are vertically arranged on the other side of the connecting column 302, and a nylon rope is arranged between the auxiliary guide wheels 305 and connected with the guide driving piece 5;
a plurality of built-in springs 306 are arranged in the fixed rail frame 301, and the built-in springs 306 provide flight ejection power for the aerospace model through the elastic force.
Referring to fig. 5, in this embodiment, the guide driving member 5 includes a receiving disc 502, a driving main member 501, a traction buffer device 6, a locking member 7, and an auxiliary ejection assembly 8, wherein the driving main member 501 is mounted on a lower end surface of the receiving disc 502, and is limited by the driving main member 501 to slide in the fixed rail frame 301;
a traction buffer device 6 is installed on one side, away from the built-in spring 306, of the driving main part 501, and the traction buffer device 6 performs traction buffering on the end part of the driving main part 501 after the driving main part starts to eject under the action of elastic force;
therefore, the bearing disc 502 is internally provided with a locking fastener 7 for initially locking a driving wheel of the aerospace model;
the carrying disc 502 is provided with an auxiliary ejection assembly 8 on the same side of the built-in spring 306, and the auxiliary ejection assembly 8 provides starting and disengaging power for the end of the aerospace model, so that when the locking fastener 7 stops locking the driving wheel, the auxiliary ejection assembly 8 transversely pushes the aerospace model to drive away from the carrying disc 502.
Referring to fig. 6, in this embodiment, the traction buffering device 6 includes an upper guide wheel 602, a support rod 601, an upper link 603, a damping spring 605 and a front guide wheel 604, wherein the support rod 601 is obliquely fixed on one side of the driving main part 501, the upper guide wheel 602 is arranged on the support rod 601 and is attached to and driven by an inner wall of the upper side of the fixed rail frame 301, the upper link 603 is arranged on the support rod 601 in a relatively deflectable manner, and the front guide wheel 604 is arranged on the upper link 603 in a rotatable manner;
and a damping spring 605 is further connected between the driving main part 501 and the upper link 603, and the damping spring 605 partially pushes the front guide wheel 604 upwards and slantways through the action of elasticity.
In this embodiment, one side of the fixed rail frame 301 is further provided with a stopping body member 9, the inner wall of the cross section of the stopping body member 9 is of an arc structure, specifically, after the aerospace model is successfully ejected, the front guide wheel and the upper guide wheel are abutted against the inner wall of the upper end of the fixed rail frame, after the stopping body member is contacted, the front guide wheel deflects around the support rod member through the upper link rod and is abutted against the inner wall of the stopping body member, and after the tail end of the stopping body member is contacted, the ejecting buffer is performed by the ejecting action of the damping spring, so that the ejecting equipment is protected, and the service life of the equipment is prolonged.
Referring to fig. 7, in this embodiment, the locking element 7 further includes a toggle rod 703, an inner transmission rod 704, a main holder 701 and an auxiliary clip 702, wherein the main holder 701 is installed in the driving main element 501, the auxiliary clip 702 is relatively rotatably installed on the main holder 701, and the auxiliary clip 702 is mutually matched with the main holder 701 under an elastic action of a connecting spring to be in a clamping state;
a poke rod 703 is arranged in the driving main part 501 in a relatively deflectable manner, one end of the poke rod 703 is hinged with an inner transmission rod 704, the inner transmission rod 704 is connected with the auxiliary clamp piece 702, and the auxiliary clamp piece 702 and the main clamp seat 701 are controlled to be opened and closed under the pushing of the poke rod 703;
one side of the fixed rail frame 301, which is far away from the built-in spring 306, is provided with a limiting sliding groove, one end of the poke rod 703 can slide along the limiting sliding groove, it should be noted that, in a launch starting preparation state, the poke rod is in a downward inclined state and does not contact with the limiting sliding groove to slide, when the aerospace model enters a starting state and moves to the middle of the fixed rail frame, the poke rod is deflected and adjusted under the clamping effect of the limiting sliding groove, so that the opening and closing effect of the auxiliary clamping piece and the main clamping seat is realized through the inner transfer rod, and the guide wheel of the aerospace model is driven.
In this embodiment, the auxiliary ejection assembly 8 includes an external pump member, a seal guide 801, a transmission shaft plug 802 and a delivery branch pipe 803, the seal guide 801 is transversely installed on the tray 502, and the transmission shaft plug 802 is relatively slidably arranged in the seal guide 801;
and, a delivery branch pipe 803 is connected to one side of the lower part of the sealing guide 801, and one end of the delivery branch pipe 803 is communicated with an external pumping device (not shown in the way).
Specifically, in the launching and launching simulation of the aerospace science popularization model, the starting length of a model channel is controlled through the sliding action of a rotating shaft seat, the local adjustment of the slope surface of the channel is realized through a support column, the aerospace model is erected on a starting and launching assembly, a lock catch part is used for positioning and locking a guide wheel of the aerospace model, and a winding wheel is used for rotating and winding a nylon rope, so that a guide driving part can be used for jacking the end part of a built-in spring and achieving a launching preparation state; the guide driving piece slides along the guide support plate through a connecting joint between the loose/broken nylon rope and the guide driving piece, and the traction buffer device performs end buffering on the driving main piece after catapult takeoff in the sliding process; the locking fastener stops positioning and locking connection of the guide wheel of the aerospace model, the aerospace model is ejected out of the locking fastener in the pre-flying process by the auxiliary ejection assembly, and the aerospace model is separated from the fixed rail frame and takes off along the slope auxiliary guide piece.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can substitute or change the technical solution of the present invention and the inventive concept within the technical scope of the present invention, and the technical solution and the inventive concept thereof should be covered by the scope of the present invention.
Claims (7)
1. The utility model provides an aerospace science popularization model self-adaptation jettison device, its includes support base (101), installation body frame (1), direction extension board (2), starting jettison subassembly (3) and domatic supplementary guide (4), wherein, the lower terminal surface of installation body frame (1) has support base (101) through rivet riveting, and by support base (101) firm the setting up subaerial, its characterized in that: the upper end surface of the installation main frame (1) is provided with a guide support plate (2);
the guide support plate (2) is arranged on the installation main frame (1) in a relatively-deflected manner and is used as a jump track of the aerospace model;
the starting ejection assembly (3) is fixed on one side of the upper end face of the guide support plate (2), and the starting ejection assembly (3) is used for providing ejection starting power for the aerospace model so that the aerospace model can reach the pre-flying speed before being separated from the guide support plate (2) to carry out aerospace flight simulation;
a slope auxiliary guide part (4) is arranged on one side, far away from the starting ejection assembly (3), of the guide support plate (2), the starting end face of the slope auxiliary guide part (4) is flush with the end face of the guide support plate (2), and a take-off slope is provided for the aeronautical model when the aeronautical model is about to be separated from the guide support plate (2);
the middle part of the lower end face of the mounting main frame (1) is provided with a rotary screw (103) which can relatively rotate through a fixing part, the rotary screw (103) is provided with a connecting support part (105) which can relatively slide through a thread meshing effect, the lower end face of the mounting main frame (1) is provided with a driving motor (104), and the output end of the driving motor (104) is connected and fixed with the rotary screw (103);
a rotary shaft seat (102) is arranged on the mounting main frame (1), and the guide support plate (2) can be hinged on the rotary shaft seat (102) in a relatively deflecting manner;
a support column (106) is hinged to the lower portion of one side, away from the rotating shaft seat, of the guide support plate (2), one end of the support column (106) is connected with the connecting support piece (105), and the connecting support piece (105) drives the support column (106) to obliquely bear the guide support plate (2);
a strip-shaped sliding position is arranged on the upper end surface of the mounting main frame (1), and the rotary shaft seat (102) is limited in the strip-shaped sliding position in a relatively sliding manner;
a connecting cross bar (201) is transversely fixed on the middle side in the guide support plate (2), a bearing frame (202) is arranged on the connecting cross bar (201) in a relatively sliding manner, and the guide support plate (2) is rotatably connected to the rotary shaft seat (102) through the bearing frame (202);
the starting ejection assembly (3) is fixed on the bearing frame (202), and the bearing frame (202) slides transversely along the guide support plate (2), so that the horizontal distance between the starting ejection assembly (3) and the slope auxiliary guide piece (4) can be effectively regulated and controlled.
2. The aerospace science popularization model adaptive ejection device according to claim 1, wherein: the starting ejection assembly (3) comprises a connecting column (302), a fixed frame body (303), a winding wheel (304), an auxiliary guide wheel (305), a built-in spring (306), a guide driving piece (5) and a fixed rail frame (301), wherein the fixed rail frame (301) is transversely fixed on the bearing frame (202), the guide driving piece (5) is arranged in the fixed rail frame (301) in a manner of relatively transversely sliding, and the guide driving piece (5) is used for bearing and erecting a space model;
a connecting column (302) is vertically arranged on the fixed rail frame (301), one side of the connecting column (302) is rotatably connected with a winding wheel (304) through a fixed frame body (303), and a nylon rope is wound on the winding wheel (304);
a plurality of auxiliary guide wheels (305) are vertically arranged on the other side of the connecting column body (302), and a nylon rope is arranged among the auxiliary guide wheels (305) in a penetrating manner and is connected with the guide driving piece (5);
a plurality of built-in springs (306) are arranged in the fixed rail frame (301), and the built-in springs (306) provide flight ejection power for the aerospace model through the elastic force.
3. The aerospace science-popularization model adaptive ejection device according to claim 2, wherein: the guide driving part (5) comprises a bearing disc (502), a driving main part (501), a traction buffering device (6), a locking part (7) and an auxiliary ejection assembly (8), wherein the driving main part (501) is installed on the lower end face of the bearing disc (502), and is limited by the driving main part (501) to slide in the fixed rail frame (301);
a traction buffer device (6) is installed on one side, away from the built-in spring (306), of the driving main part (501), and the traction buffer device (6) performs traction buffering on the end part of the driving main part (501) after starting and ejecting under the action of elastic force;
therefore, a locking fastener (7) is arranged in the bearing disc (502) and is used for initially locking the driving wheel of the aerospace model; an auxiliary ejection assembly (8) is arranged on the same side, located on the built-in spring (306), of the bearing disc (502), the auxiliary ejection assembly (8) provides starting and disengaging power for the end portion of the aerospace model, and therefore when the locking fastener (7) stops locking the driving wheel, the auxiliary ejection assembly (8) pushes the aerospace model to move away from the bearing disc (502) in the transverse direction.
4. The aerospace science-popularization model adaptive ejection device according to claim 3, wherein: the traction buffer device (6) comprises an upper guide wheel (602), a support rod piece (601), an upper link rod (603), a damping spring (605) and a front guide wheel (604), wherein the support rod piece (601) is obliquely fixed on one side of the driving main piece (501), the upper guide wheel (602) is arranged on the support rod piece (601) and is attached to and driven by the inner wall of the upper side of the fixed rail frame (301), the upper link rod (603) is arranged on the support rod piece (601) in a relatively-deflecting manner, and the front guide wheel (604) is rotatably arranged on the upper link rod (603);
and a damping spring (605) is further connected between the driving main part (501) and the upper link rod (603), and the damping spring (605) partially pushes the front guide wheel (604) upwards and slantwise through the action of elasticity.
5. The aerospace science-popularization model adaptive ejection device according to claim 2, wherein: one side of the fixed rail frame (301) is further provided with a stopping body piece (9), and the inner wall of the cross section of the stopping body piece (9) is of an arc-shaped structure.
6. The aerospace science-popularization model adaptive ejection device according to claim 3, wherein: the lock catch piece (7) further comprises a poke rod (703), an inner transmission rod (704), a main clamping seat (701) and an auxiliary clamping piece (702), wherein the main clamping seat (701) is installed in the driving main piece (501), the auxiliary clamping piece (702) is arranged on the main clamping seat (701) in a relatively rotating mode, and the auxiliary clamping piece (702) is matched with the main clamping seat (701) to be in a clamping state under the action of the elastic force of a connecting spring in a general state;
a poke rod (703) is arranged in the driving main part (501) and can deflect relatively, an inner transmission rod (704) is hinged to one end of the poke rod (703), the inner transmission rod (704) is connected with the auxiliary clamping piece (702), and the auxiliary clamping piece (702) and the main clamping seat (701) are controlled to be opened and closed under the pushing of the poke rod (703);
one side of the fixed rail frame (301) far away from the built-in spring (306) is provided with a limiting sliding groove, and one end of the poke rod (703) can slide along the limiting sliding groove.
7. The aerospace science-popularization model adaptive ejection device according to claim 3, wherein: the auxiliary ejection assembly (8) comprises an external pump piece, a sealing guide piece (801), a transmission shaft plug (802) and a transmission branch pipe (803), wherein the sealing guide piece (801) is transversely arranged on the bearing disc (502), and the transmission shaft plug (802) is arranged in the sealing guide piece (801) in a relatively sliding manner;
and a delivery branch pipe (803) is connected below one side of the sealing guide piece (801), and one end of the delivery branch pipe (803) is communicated with an external pump piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110451088.9A CN113018881B (en) | 2021-04-25 | 2021-04-25 | Aerospace science popularization model self-adaptive ejection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110451088.9A CN113018881B (en) | 2021-04-25 | 2021-04-25 | Aerospace science popularization model self-adaptive ejection device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113018881A CN113018881A (en) | 2021-06-25 |
| CN113018881B true CN113018881B (en) | 2022-04-29 |
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| CN202110451088.9A Active CN113018881B (en) | 2021-04-25 | 2021-04-25 | Aerospace science popularization model self-adaptive ejection device |
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| GB517331A (en) * | 1938-07-22 | 1940-01-26 | Nicholas Sandor | Improvements connected with the catapulting of aircraft |
| GB1490164A (en) * | 1976-03-17 | 1977-10-26 | Airfix Prod Ltd | Toy |
| GB2293146B (en) * | 1994-09-15 | 1998-04-15 | Airscrew Howden Ltd | Launching projectiles |
| CN101920787A (en) * | 2009-06-10 | 2010-12-22 | 马世强 | Aircraft fuselage orientation adjustment steering wheel stand |
| CN102107737B (en) * | 2010-09-19 | 2013-03-27 | 济南环太机电技术有限公司 | Front-pull rear-push aircraft carrier ejector and ejection method |
| CN102951297B (en) * | 2011-08-19 | 2015-04-22 | 丁陶生 | Device for realizing high-speed take-off of shipboard aircraft by spring combination mechanical ejection |
| CN203094464U (en) * | 2013-01-24 | 2013-07-31 | 周景谊 | High-frequency gradually-accelerated sliding-jumping catapult |
| US10118713B2 (en) * | 2013-08-27 | 2018-11-06 | Engineered Arresting Systems Corporation | Electric unmanned aerial vehicle launcher |
| KR101343246B1 (en) * | 2013-09-24 | 2013-12-18 | (주)한국유에이브이 | Launchign apparatus for samll unmanned aerial vehicle |
| CN104608937B (en) * | 2015-02-03 | 2017-03-01 | 河南省汇隆精密设备制造股份有限公司 | A kind of multi-model unmanned plane hydraulic energy-accumulating catapult-launching gear |
| US9994335B1 (en) * | 2015-06-04 | 2018-06-12 | The United States Of America, As Represented By The Secretary Of The Navy | Rapid unmanned aerial vehicle launcher (UAV) system |
| CN106314814B (en) * | 2016-09-28 | 2018-12-18 | 天津大学 | A kind of field the scientific research portable launching apparatus of fixed-wing unmanned plane and application method |
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| CN211513405U (en) * | 2019-12-27 | 2020-09-18 | 王竑博 | Aircraft carrier model with carrier-based aircraft ejection function |
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| CN113274742A (en) * | 2021-06-18 | 2021-08-20 | 南京工业职业技术大学 | Flywheel energy storage ejection toy plane propelled by coaxial counter-propellers |
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