CN214075044U

CN214075044U - Stagnant empty paper aircraft

Info

Publication number: CN214075044U
Application number: CN202023335624.9U
Authority: CN
Inventors: 李官翰
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-12-31
Filing date: 2020-12-31
Publication date: 2021-08-31
Anticipated expiration: 2030-12-31

Abstract

The application discloses a vacancy-retaining paper airplane, which comprises a fuselage and wings, wherein the fuselage and the wings are integrated and arranged in the middle, the nose part is provided with a seal head capable of locking a fuselage structure, and the wing structure is swept forward at the front edge and straight at the rear edge; the wingtip of the wing is provided with an upward vertical winglet; the rear edge of the wing is provided with an elevator; the average wing load of the wing is 0.0200-0.0205g/cm²(ii) a The aspect ratio of the wing is as follows: 1.55-1.75. The utility model discloses a lower aspect ratio, less wing load, less leading edge sweepback angle and no tail aerodynamic configuration have been compromise to the great flying height and the tailless aerodynamic device of upwards throwingThe aircraft has the advantages that the descent speed is low, the effect of long-time air-stagnation flight is achieved, compared with other long-time air-stagnation paper aircrafts, the aircraft has both indoor and outdoor flight performance, the requirement limit of the paper aircrafts on the site is eliminated, and the aircraft is more flexible and wide in application.

Description

Stagnant empty paper aircraft

Technical Field

The application relates to the technical field of paper airplanes, in particular to a stagnant paper airplane.

Background

The flying interest and appreciation of the paper plane are determined by the performance index of the dead time of the paper plane in flying. The longer the dead time of the paper plane in flying, the more stable the flight, the more interesting and ornamental, and the more commercial value.

The applicant found that the dead time for the vast majority of players in a pre-selection game in each country is about 3-6 seconds in a world paper plane tournament, while the dead time for the majority of players in a total playoff is about 6-12 seconds. According to the analysis, the reason is that most of the paper aircraft contestants launch the paper aircraft in an upward-throwing manner so as to obtain a higher flight height and thus improve flight time.

The player is in order to make the paper aircraft dead time more for a long time, often with the very big of folding of paper aircraft's wing area for paper aircraft's lift center and barycentric position mismatch, the lift center is too much behind than the barycentric position, this will make paper aircraft have more dive when gliding, glide unstable and make the descent speed too fast, too big wing area also can lead to turning into the glide phase in lower place when upwards throwing, also can reduce paper aircraft's dead time.

In addition, the domestic long-time air-lag paper plane is difficult to fly indoors and outdoors for a long time, the paper plane suitable for indoor flight does not have good wind resistance outdoors, and the paper plane suitable for outdoor flight has too high descending speed when flying indoors due to too far forward gravity center.

SUMMERY OF THE UTILITY MODEL

The main objective of this application is to provide a stagnant empty paper aircraft to solve present problem.

In order to achieve the above object, the present application provides the following techniques:

a kind of aircraft of empty paper of staying, including fuselage and wing, the said fuselage and wing are integrative and put in the middle, the said nose part has end sockets that can lock the fuselage structure, the said wing structure is sweepback for the leading edge, the trailing edge is straight; the wingtip of the wing is provided with an upward vertical winglet; the rear edge of the wing is provided with an elevator; the average wing load of the wing is 0.0200-0.0205g/cm²(ii) a The aspect ratio of the wing is as follows: 1.55-1.75.

Further, the width of the elevator is smaller than the width of the trailing edge of the wing.

Further, the rear edge of the elevator is bent upwards, and the upturning angle is 5-50 degrees.

Further, the dihedral angle of the airfoil is 0-30 °.

Further, the leading edge sweep angle of the airfoil is 35-45 °.

Further, the leading edge of the wing is formed by folding and thickening through an inner plug method.

Further, the average wing load of the wing is 0.0202g/cm²。

Further, the aspect ratio of the wing is: 1.65.

furthermore, the number of layers which are folded and thickened by the internal folding method is not less than four.

Further, the turning angle of the elevator is 45 degrees, the dihedral angle of the wing is 15 degrees, and the leading edge sweepback angle of the wing is 45 degrees.

Compared with the prior art, this application can bring following technological effect:

1. the utility model adopts lower aspect ratio, smaller wing load, smaller leading edge sweepback angle and tailless pneumatic layout, takes account of larger flying height and smaller descending speed of the unpowered glider thrown upwards, realizes the effect of long-time air-lag flight, and compared with other long-time air-lag paper airplanes, the aircraft simultaneously takes account of indoor and outdoor flight performance, eliminates the requirement limit of the paper airplane flying to the field, and has more flexible and wide application;

2. the utility model discloses be fit for the long-time stagnant empty paper aircraft of flying of indoor outdoor, the paper aircraft is formed by whole paper is folding in order, need not to tailor, supplementary measures such as paste.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, serve to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:

fig. 1 is a schematic diagram of the three-dimensional structure of the present invention;

fig. 2 is a schematic front view of the present invention;

fig. 3 is a rear view structure diagram of the present invention;

fig. 4 is a schematic side view of the present invention;

fig. 5 is a schematic top view of the present invention;

fig. 6 is a schematic view of the upturn angle of the elevator of the present invention;

in the figure: 1. the aircraft comprises a seal head, 2, wings, 3, vertical winglets, 4, elevators, 5 and an aircraft body.

Detailed Description

In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.

In this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.

Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.

In addition, the term "plurality" shall mean two as well as more than two.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

Example 1

A kind of aircraft of empty paper of staying, including fuselage 5 and wing 2, the said fuselage 5 and wing 2 are integrative and put in the middle, the said nose part has end sockets 1 that can lock the fuselage structure, the said wing 2 structure is that the leading edge sweepbacks, the trailing edge is straight; the wingtip of the wing 2 is provided with an upward vertical winglet 3; the rear edge of the wing 2 is provided with an elevator 4; the average wing load of the wing is 0.0200-0.0205g/cm²(ii) a The aspect ratio of the wing 2 is: 1.55-1.75.

As shown in the attached figures 1-5,

the utility model discloses paper aircraft is formed by whole paper is folding in proper order, need not to tailor, supplementary measures such as paste. The fuselage 5 and the wing 2 are integrated and arranged in the middle, and the wing 2 is a trapezoidal wing with a sweepback front edge and a straight back edge. The wingtip is provided with an upward vertical winglet (3), the rear edge of the wing (2) is provided with an elevator (4) which is bent upward, and the nose part is provided with a seal head (1) which can lock the structure of the fuselage.

The adoption of lower aspect ratio, smaller wing load, smaller leading edge sweepback angle and tailless aerodynamic layout gives consideration to larger flying height and smaller descending speed of the upward throwing of the unpowered glider, and realizes the effect of long-time air-lag flight. Compared with other long-time air-lag paper airplanes, the airplane has both indoor and outdoor flight performance, eliminates the requirement limit of the paper airplane on the field, and is more flexible and wide in application.

In order to obtain the ideal gliding ability and throwing height, the resistance of the paper plane should be controlled within a reasonable range:

the average wing load of the wing is 0.0200-0.0205g/cm²(ii) a The aspect ratio of the wing 2 is: 1.55-1.75.

Further, in order to obtain better flight capability of both indoor and outdoor air stagnation, the width of the elevator 4 is smaller than that of the trailing edge of the wing 2.

Further, as shown in fig. 6, the rear edge of the elevator 4 is bent upward, and the flip-up angle c is 5 to 50 °.

In order to obtain better doubling indoor and outdoor empty flight ability that stagnates, the utility model discloses a through many times's experiment, finally found and to have so that lift center and the best book method of gravity center position collocation.

The front edge of the paper plane is thickened by folding, the center of gravity moves forwards, and if the paper plane descends at an excessively high speed and is easy to fall during flying, the paper plane is trimmed by the elevator with the bent and upward rear edge, and the bent and upward rear edge is at an angle of 5-50 degrees.

Further, the dihedral angle of the wing 2 is 0-30 °.

As shown in fig. 2, the present embodiment employs a dihedral angle a of 30 °.

Further, the leading edge sweep angle of the airfoil 2 is 35-45 °.

As shown in fig. 5, the present machine uses this small leading-edge sweep angle b of 39 °, so that the paper plane achieves a slow descent speed while achieving a large throw height.

If a higher flying quality is desired and the descent speed of the paper plane is reduced to obtain an ideal gliding capability and throwing height, the resistance of the paper plane should be controlled within a reasonable range. Too little drag can cause the aircraft to fly too quickly and the descent to be fast, and too much drag can cause the aircraft to climb to a lower altitude when thrown upward. The utility model discloses a folding method that uses can hide folding paper in inside for the appearance of paper aircraft is more smooth. At the same time, the paper plane adopts the smaller front edge sweepback angle of 39 degrees, so that the paper plane obtains a larger throwing height and a slower descending speed at the same time.

Further, the leading edge of the wing 2 is formed by folding and thickening through an inner plug method.

The utility model discloses an use special folding method to hide folding paper inside for the appearance of paper aircraft is more smooth.

Further, the average wing load of the wing is 0.0202g/cm²。

Further, the aspect ratio of the wing 2 is: 1.65.

in order to give consideration to higher upward throwing flying height and less gliding descent speed when better, the utility model discloses an adopted less wing load during the design, average wing load is 0.0202g/cm²Moderate wing load is the key of unpowered gliding, and too big wing load will lead to getting into gliding state prematurely when throwing upwards and dive more when gliding, and wing load undersize can make the flight speed too fast when gliding, and the decline speed increases. The wing load of the machine is 0.0202g/cm²And the wing load lower limit in a reasonable range is closer than that of the conventional air-trapped paper aircraft.

If the paper plane is shifted to the gliding height when being thrown upwards so that the paper plane begins to glide from a higher place, the aspect ratio of the paper plane is properly reduced on the premise of ensuring the wing load, and the formula of the aspect ratio is as follows: aspect ratio being the square of the wing span/wing area, i.e.

The aspect ratio of the machine is as follows: 1.65, guarantee wing load can make the influence of gliding quality less, reduce the aspect ratio and can make the fuselage of paper aircraft shorter, thereby it is higher to exert oneself easily when throwing so that throw the height.

In order to overcome the distortion caused by impulsive force applied to the wings of the paper plane during throwing and obtain better lateral wind resistance during outdoor flight, the number of layers of paper is increased at the joint of the wings and the plane body during folding so as to increase the strength of the wings, and the aim is effectively fulfilled.

Further, the turning angle of the elevator 4 is 45 °, the dihedral angle of the wing 2 is 15 °, and the leading edge sweepback angle of the wing 2 is 45 °.

The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A kind of empty paper plane of staying, including fuselage (5) and wing (2), the said fuselage (5) and wing (2) are integrative and put into the middle, the aircraft nose part has head (1) that can lock the fuselage structure, characterized by that, the said wing (2) structure is that the leading edge sweepbacks, the trailing edge is straight; the wingtip of the wing (2) is provided with an upward vertical winglet (3); the rear edge of the wing (2) is provided with an elevator (4); the average wing load of the wing is 0.0200-0.0205g/cm²(ii) a The aspect ratio of the wing (2) is as follows: 1.55-1.75.

2. A flying lead aircraft according to claim 1, wherein the width of the elevator (4) is less than the width of the trailing edge of the wing (2).

3. A airborne paper aircraft according to claim 1 or 2, characterized in that the trailing edge of the elevator (4) is curved upwards and the upturn angle is 5-50 °.

4. A space-saving paper aircraft according to claim 3, wherein the dihedral of the wing (2) is between 0 ° and 30 °.

5. A slot-free paper aircraft as claimed in claim 1 or 4, characterized in that the leading-edge sweep of the wing (2) is 35-45 °.

6. An aircraft according to claim 5, characterized in that the leading edge of the wing (2) is formed by folding and thickening by tucking in.

7. An aircraft according to claim 1 or claim 6, wherein the wing has an average wing load of 0.0202g/cm²。

8. An aircraft according to claim 1 or 6, characterized in that the wing (2) has an aspect ratio of: 1.65.

9. the airborne dead space paper aircraft of claim 6, wherein the number of folds thickened by tucking in is not less than four.

10. A flying machine according to claim 5, wherein the rudder (4) has a tip angle of 45 °, the wing (2) has a dihedral angle of 15 °, and the wing (2) has a leading-edge sweep angle of 45 °.