CN209865303U

CN209865303U - Automatic parachute jumping aircraft

Info

Publication number: CN209865303U
Application number: CN201920349890.5U
Authority: CN
Inventors: 申宝银
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-03-19
Filing date: 2019-03-19
Publication date: 2019-12-31
Anticipated expiration: 2029-03-19

Abstract

The embodiment of the utility model discloses automatic parachute jumping aircraft belongs to aircraft technical field, and its technical scheme main points are automatic parachute jumping aircraft, including aircraft body, parachute and balancing weight, the balancing weight is fixed to be set up on the umbrella rope of parachute, parachute and balancing weight set up in on the aircraft body, when the aircraft body is in flight state, parachute and balancing weight can break away from aircraft body and parachute, have reached the purpose that the parachute can be put in automatically to the aircraft at the flight in-process, can increase the interest when the aircraft uses.

Description

Automatic parachute jumping aircraft

Technical Field

The embodiment of the utility model provides an automatic parachuting aircraft relates to aircraft technical field, concretely relates to.

Background

The toy aircraft is common toy, can attract more children to use, play, and current toy aircraft only possesses flight ability, and the form is too single during play, and the reality is not enough, can't attract more crowds to purchase the use.

Disclosure of Invention

Therefore, the embodiment of the utility model provides an automatic parachuting aircraft to solve the single problem of aircraft form of playing among the prior art.

In order to achieve the above object, the embodiment of the present invention provides the following technical solutions:

the utility model provides an automatic parachute jumping aircraft, includes aircraft body, parachute and balancing weight, the balancing weight is fixed to be set up on the parachute rope of parachute, parachute and balancing weight set up in on the aircraft body, when the aircraft body is in flight state, parachute and balancing weight can break away from aircraft body and parachute.

Further, aircraft body downside is equipped with and deposits slide and interim fixed storehouse temporarily, it includes horizontal slide and slope slide to deposit the slide temporarily, horizontal slide is located inside the aircraft body, the slope slide is close to aircraft body top one end and is close to aircraft body head one end intercommunication with horizontal slide, the slope slide is close to aircraft top one end to being close to aircraft bottom one end and inclines to aircraft body head or afterbody gradually, slope slide lower extreme opening, the balancing weight sets up horizontal slide is close to aircraft body afterbody one end, interim fixed storehouse is close to aircraft bottom one side opening, and interim fixed storehouse is close to aircraft bottom one side open position and is provided with a plurality of fixed archs, the parachute stacks in interim fixed storehouse and is located fixed protruding upside.

Furthermore, an ejection device and a starting device are arranged on the aircraft body, the ejection device can push the counterweight block to be separated from the aircraft body, and the starting device can trigger the ejection device to be started.

Furthermore, the ejection device is arranged on one side, close to the tail portion of the aircraft body, of the horizontal slideway, the ejection device comprises an electromagnet, a firing pin and a return spring, an avoidance channel is arranged in the middle of the electromagnet, the firing pin is connected to the avoidance channel in a sliding mode, an iron plate is arranged at one end, close to the tail portion of the aircraft body, of the firing pin, the return spring is sleeved on the firing pin, and two ends of the return spring are respectively abutted to the electromagnet and the iron.

Further, the starting device comprises a power supply and a timing switch, and the power supply is connected with the ejection device through the timing switch.

Further, the timing switch is a mechanical timing switch or an electronic timing switch.

Further, the aircraft body is a hand throwing aircraft or a power aircraft.

The embodiment of the utility model provides a have following advantage:

the parachute and the balancing weight of the aircraft body are separated from the aircraft body in the flying state, real parachute jumping or air-drop scenes are simulated, the playing form of the aircraft is increased, the aircraft is more interesting, and more crowds can be attracted to use.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.

The structure, ratio, size and the like shown in the present specification are only used for matching with the content disclosed in the specification, so as to be known and read by people familiar with the technology, and are not used for limiting the limit conditions which can be implemented by the present invention, so that the present invention has no technical essential significance, and any structure modification, ratio relationship change or size adjustment should still fall within the scope which can be covered by the technical content disclosed by the present invention without affecting the efficacy and the achievable purpose of the present invention.

Fig. 1 is a schematic view of an overall structure of an automatic parachuting aircraft provided in embodiment 1 of the present invention;

fig. 2 is a cross-sectional view showing the structure of the ejector in embodiment 2 of the present invention;

fig. 3 is a schematic view of a connection structure between an ejection device and a starting device according to embodiment 2 of the present invention;

in the figure:

1. an aircraft body; 11. a temporary storage chute; 111. a horizontal slideway; 112. inclining the slideway; 12. temporarily fixing the bin; 121. a fixed protrusion; 2. a parachute; 3. a balancing weight; 4. an ejection device; 41. an electromagnet; 411. avoiding the channel; 42. a striker; 421. an iron plate; 43. a return spring; 5. starting the device; 51. a power source; 52. and (5) timing switching.

Detailed Description

The present invention is described in terms of specific embodiments, and other advantages and benefits of the present invention will become apparent to those skilled in the art from the following disclosure. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Example one

The utility model provides an automatic parachute jumping aircraft, as shown in fig. 1, the dotted line shows inside lines in the picture, automatic parachute jumping aircraft includes aircraft body 1, parachute 2 and balancing weight 3, balancing weight 3 is fixed to be set up on parachute 2's parachute line, and be located 2 parachute lines of parachute and keep away from umbrella face one end, parachute 2 and balancing weight 3 set up on aircraft body 1, when aircraft body 1 is in flight state, parachute 2 and balancing weight 3 can break away from aircraft body 1 and descend, thereby simulation parachute jumping or air-drop scene, increase interest.

The aircraft body 1 can be a hand-throwing aircraft or a power aircraft, wherein the power aircraft comprises an ejection aircraft, an electric remote control aircraft, a mechanical power aircraft and the like.

The aircraft body 1 downside is equipped with and deposits slide 11 and interim fixed storehouse 12 temporarily, deposit slide 11 temporarily and include horizontal slide 111 and slope slide 112, wherein, horizontal slide 111 is located aircraft body 1 insidely, horizontal slide 111 length direction is on a parallel with the length direction of aircraft body 1 fuselage, slope slide 112 is located horizontal slide 111 and is close to 1 bottom one side of aircraft body, slope slide 112 is close to 1 top one end of aircraft body and is close to aircraft body 1 head one end intercommunication with horizontal slide 111, slope slide 112 is close to aircraft top one end to being close to aircraft bottom one end and inclines to aircraft body 1 head or afterbody gradually, slope slide 112 lower extreme opening, balancing weight 3 sets up horizontal slide 111 is close to 1 afterbody one end of aircraft body.

Temporary fixation storehouse 12 is for being close to aircraft bottom one side open-ended rectangular groove, and the 12 open positions in temporary fixation storehouse are provided with a plurality of fixed archs 121, and this fixed archs 121 sets up along the even interval in 12 open-ended edges in temporary fixation storehouse, and parachute 2 stacks in temporary fixation storehouse 12 and is located fixed archs 121 upside, and parachute 2 fixes in temporary fixation storehouse 12 when not putting in temporarily.

Aircraft body 1 uses hand-thrown aircraft as an example, the head of aircraft body 1 is raised when the aircraft is in the raised condition, balancing weight 3 is deposited in horizontal slideway 111, and parachute 2 fixes in interim fixed storehouse 12, when aircraft body 1 reachs the highest position and begins to descend, aircraft body 1 head sinks, balancing weight 3 slides to slope slide 112 along horizontal slideway 111 under the action of gravity, and slide to aircraft body 1 outside along slope slide 112, make parachute 2 break away from interim fixed storehouse 12 under the pulling force effect of balancing weight 3, accomplish the process of puting in parachute 2.

Example two

With reference to fig. 2 and fig. 3, a difference between this embodiment and the first embodiment is that an ejection device 4 and a starting device 5 are disposed on an aircraft body 1, the ejection device 4 can push a counterweight 3 to separate from the aircraft body 1, the starting device 5 can trigger the ejection device 4 to start, and a parachute 2 can be actively launched under the action of the ejection device 4 and the starting device 5, so that the counterweight 3 cannot separate from the aircraft body 1 under the condition of a large friction force.

The ejection device 4 is arranged on one side, close to the tail portion of the aircraft body 1, of the horizontal slideway 111, the ejection device 4 comprises an electromagnet 41, a firing pin 42 and a return spring 43, an avoidance channel 411 is arranged in the middle of the electromagnet 41, the central line direction of the avoidance channel 411 is parallel to the length direction of the horizontal slideway 111, the firing pin 42 is of a long-strip-shaped rod-shaped structure, the firing pin 42 is connected to the avoidance channel 411 in a sliding mode, an iron plate 421 is arranged at one end, close to the tail portion of the aircraft body 1, of the firing pin 42, the return spring 43 is sleeved with a support spring, the return spring.

The starting device 5 comprises a power supply 51 and a timing switch 52, the power supply 51 is connected with the ejection device 4 through the timing switch 52, when the timing switch 52 is in a closed state, the power supply 51 is connected with a passage of the electromagnet 41, the attraction iron plate 421 moves towards the electromagnet 41 under the action of the electromagnet 41, the striker 42 impacts the counterweight 3 to enable the counterweight 3 to be separated from the aircraft body 1, and the process of putting the parachute 2 is completed.

The timing switch 52 can be a mechanical timing switch 52 or an electronic timing switch 52, and a user presets ejection time to determine the putting time of the parachute 2, so that the parachute 2 is automatically put after the automatic parachuting aircraft takes off.

It should be noted that the friction force between the counterweight 3 and the horizontal slideway 111 can be increased under the condition that the ejection device 4 and the starting device 5 are arranged on the aircraft body 1, so that the counterweight 3 can not automatically launch the parachute 2 under the action of gravity, and the friction force can also not be increased, so that the automatic parachuting aircraft can also realize the function of automatically launching the parachute 2 under the condition that the ejection device 4 and the starting device 5 are not started.

Although the invention has been described in detail with respect to the general description and the specific embodiments, it will be apparent to those skilled in the art that modifications and improvements can be made based on the invention. Therefore, such modifications and improvements are intended to be within the scope of the invention as claimed.

Claims

1. The utility model provides an automatic parachute jumping aircraft, its characterized in that, includes aircraft body (1), parachute (2) and balancing weight (3), balancing weight (3) are fixed to be set up on the parachute rope of parachute (2), parachute (2) and balancing weight (3) set up in on aircraft body (1), when aircraft body (1) is in flight state, parachute (2) and balancing weight (3) can break away from aircraft body (1) and descend.

2. The parachuting aircraft of claim 1, wherein a temporary storage chute (11) and a temporary fixing bin (12) are arranged at the lower side of the aircraft body (1), the temporary storage chute (11) comprises a horizontal chute (111) and an inclined chute (112), the horizontal chute (111) is positioned inside the aircraft body (1), the inclined chute (112) is communicated with the horizontal chute (111) near the head of the aircraft body (1) near one end of the top of the aircraft body (1), the inclined chute (112) is gradually inclined towards the head or the tail of the aircraft body (1) from one end near the top of the aircraft to one end near the bottom of the aircraft, the lower end of the inclined chute (112) is open, the counterweight (3) is arranged at one end near the tail of the aircraft body (1) near the horizontal chute (111), the temporary fixing bin (12) is open at one side near the bottom of the aircraft, temporary fixed storehouse (12) are close to aircraft bottom one side open position and are provided with a plurality of fixed archs (121), parachute (2) stack in temporary fixed storehouse (12) and are located fixed arch (121) upside.

3. The parachuting aircraft of claim 2, wherein the aircraft body (1) is provided with an ejection device (4) and an actuating device (5), the ejection device (4) can push the counterweight (3) to be separated from the aircraft body (1), and the actuating device (5) can trigger the ejection device (4) to be actuated.

4. The automatic parachuting aircraft of claim 3, wherein the ejection device (4) is arranged on one side, close to the tail of the aircraft body (1), of the horizontal slideway (111), the ejection device (4) comprises an electromagnet (41), a striker (42) and a return spring (43), an avoidance channel (411) is arranged in the middle of the electromagnet (41), the striker (42) is connected to the avoidance channel (411) in a sliding mode, an iron plate (421) is arranged at one end, close to the tail of the aircraft body (1), of the striker (42), and the return spring (43) is sleeved on the striker (42) and two ends of the return spring are respectively abutted to the electromagnet (41) and the iron plate (421).

5. Automatic parachuting aircraft according to claim 3, characterized in that said activation means (5) comprise a power source (51) and a timing switch (52), said power source (51) being connected to said ejection means (4) through the timing switch (52).

6. Auto-parachuting aircraft according to claim 5, characterized in that the timing switch (52) is a mechanical timing switch (52) or an electronic timing switch (52).

7. The parachuting aircraft of claim 1, wherein the aircraft body (1) is a hand-thrown aircraft or a powered aircraft.