CN106902519B

CN106902519B - Ejection type gliding aircraft model

Info

Publication number: CN106902519B
Application number: CN201610925150.2A
Authority: CN
Inventors: 郭树冠
Original assignee: Tianjin Normal University
Current assignee: Tianjin Normal University
Priority date: 2016-10-30
Filing date: 2016-10-30
Publication date: 2023-03-28
Anticipated expiration: 2036-10-30
Also published as: CN106902519A

Abstract

The invention discloses an ejection type gliding aircraft model, which comprises: the wing comprises a body, and a wing and an empennage which are arranged on the body, wherein the wing comprises a wing middle section and 2 wing tips, the 2 wing tips are respectively fixedly arranged at two ends of the wing middle section, the upper dihedral angle of the wing tips is 15-25 degrees, a step platform is formed on the upper surface of the wing along the length direction of the wing, the step platform is positioned at the position where the chord length is 45-55%, and the step height of the step platform is 4% -6% of the chord length; the tail wing consists of a first tail wing and a vertical second tail wing, the first tail wing is installed on the machine body in a manner of rotating for 2-3 degrees by taking the machine body as a central shaft and taking a horizontal plane as a starting point, the lower end of the second tail wing is fixedly installed on the upper surface of the first tail wing, and the side surface of the second tail wing is fixedly installed on the machine body. The step platform of the invention enables the wings to form step wings, improves the lift-drag ratio of the wings and increases the stall attack angle of the wings.

Description

Ejection type glider model

Technical Field

The invention belongs to the technical field of scientific and technological movable aircrafts, and particularly relates to an ejection type gliding aircraft model.

Background

The catapult-type gliding aircraft model has a long history as a toy or a teaching aid for beginners of aviation knowledge. The hovering mode of the traditional catapult type gliding aircraft model is generally used for hovering the aircraft through adjusting a rudder or an aileron, the mode complicates the flight control of the aircraft, and the state is difficult to analyze during catapulting.

Disclosure of Invention

In view of the defects of the prior art, the invention aims to provide an ejection type gliding aircraft model, which controls the turning circle of the model through a tail wing.

The purpose of the invention is realized by the following technical scheme.

A catapult-assisted glider model, comprising: the wing comprises a body, and a wing and an empennage which are arranged on the body, wherein the wing comprises a wing middle section and 2 wing tips, the 2 wing tips are respectively fixedly arranged at two ends of the wing middle section, the dihedral angle of the wing tips is 15-25 degrees, a step platform is formed on the upper surface of the wing along the length direction of the wing, the step platform is positioned at the position where the chord length is 45-55%, and the step height of the step platform is 4% -6% of the chord length; the tail wing is composed of a first tail wing and a vertical second tail wing, the first tail wing is installed on the machine body in a manner of rotating for 2-3 degrees by taking the machine body as a central shaft and taking a horizontal plane as a starting point, the lower end of the second tail wing is fixedly installed on the upper surface of the first tail wing, and the side surface of the second tail wing is fixedly installed on the machine body.

In the technical scheme, the dihedral angle of the wing tip is 20 degrees.

In the technical scheme, the middle section of the wing is installed on the machine body through a mortise and tenon mechanism.

In the technical scheme, the wingtips are fixedly arranged at two ends of the middle section of the wing in a bonding mode.

In the above technical solution, the step is located at a position where the chord length is 50%.

In the technical scheme, a through hole for adjusting the gravity center of the ejection type glider model is formed in the front part of the body.

In the above technical solution, the second tail wing is located on the right side of the center line of the first tail wing.

In the above technical solution, the left end of the first tail wing is located below the right end of the first tail wing.

In the above technical solution, the first rear wing is installed on the body to rotate counterclockwise by 2 to 3 ° with the body as a central axis and a horizontal plane as a starting point.

Compared with the prior art, the invention has the beneficial effects that:

1. the step platform of the invention enables the wings to form step wings, improves the lift-drag ratio of the wings and increases the stall attack angle of the wings.

2. The step wing is simple to manufacture, time-saving and labor-saving, and the wing section is accurately processed and controlled.

3. The step wing can reduce the weight of the wing.

4. The lift force generated by the first tail wing deviates to the left, namely the tail part of the airplane deviates to the left, and the nose of the airplane deviates to the right, so that the airplane can hover to the right.

5. The empennage of the invention avoids the situation that the second empennage deflects to the right to make the airplane hover, and avoids the situation that the attitude is disordered and difficult to adjust when the airplane takes off by catapulting.

Drawings

FIG. 1 is a two-section type folded wing for a conventional dihedral angle of an airplane;

FIG. 2 is an airfoil of the present invention;

FIG. 3 is a cross-sectional view of an ejection glider model according to the present invention;

FIG. 4 is an enlarged view of a portion of FIG. 3;

FIG. 5 is a schematic view of a rotating vortex behind a step platform;

FIG. 6 is a wing of a conventional catapult glider;

FIG. 7 is a schematic perspective view of a catapult-type glider model according to the present invention;

FIG. 8 is a rear view of the catapult-type glider model of the present invention;

FIG. 9 is a cross-sectional view of the tail of the catapult-type gliding aircraft model of the present invention;

fig. 10 shows a conventional catapult glider takeoff pattern.

Wherein, 1 is a wing, 1-1 is a wing tip, 1-2 is a wing middle section, 2 is a fuselage, 3 is an empennage, 3-1 is a second empennage, 3-2 is a first empennage, and 4 is a stair platform.

Detailed Description

The technical scheme of the invention is further explained by combining the attached drawings.

As shown in fig. 1 to 10, the present invention includes: a fuselage 2, and wings 1 (wings horizontally installed) and a tail 3 mounted on the fuselage, a through hole (not shown) for adjusting the center of gravity of the catapult-type glider model and a hook (not shown) for catapulting are formed in the front of the fuselage.

The traditional aircraft dihedral adopts a two-section type folding wing, as shown in figure 1, the wing has the advantages of difficult improvement of assembly precision, easy askew installation and great assembly difficulty. In the invention, the wings are installed in a three-section mode, and consist of a wing middle section 1-2 and 2 wing tips 1-1, as shown in figure 2, the wing middle section is installed on the fuselage through a mortise and tenon mechanism, so that the connection between the wings and the fuselage becomes very simple and accurate, and the manual connection speed only needs 20 seconds; the 2 wingtips are fixedly arranged at two ends of the middle section of the wing respectively in a bonding mode, the dihedral angle of the wingtips is 20 degrees, and the dihedral angle of the wingtips is installed by adopting an angle fixing device, so that the dihedral angle error of the two wingtips is smaller than 2-3 degrees, and the consistency is strong.

As shown in fig. 3, a step 4 is formed on the upper surface of the wing along the length direction of the wing (step platforms are formed on the upper surfaces of the wing tip and the middle section of the wing tip), the step is located at a position where the chord length is about 50%, and the step height of the step is 4% -6% of the chord length. The step platform makes the wing form a 'step wing', the step wing mainly uses the rotating vortex behind the step platform of the wing chord to change the laminar flow of the wing profile surface into turbulent flow, the rotating vortex like the ball in the bearing makes the airflow flowing through the wing surface not reduce in flow speed and not easily separate from the wing surface, thus, the lift force is almost generated from the leading edge to the trailing edge of the wing to reduce the resistance, as shown in fig. 5. The lift force is increased, the resistance is reduced, the lift-drag ratio of the wing is improved, and the stall attack angle of the wing is increased. In addition, the step wing has the effect of the traditional wing type, the wing of the traditional catapult glider generally adopts the plano-convex wing type, as shown in fig. 6, the polishing needs to be carefully carried out, the time is wasted, the precision is difficult to master, the wing type of the wing needs to be manufactured in advance, a grinding tool or a unified production line is needed, and the energy is very high. The test performance of the wing-shaped airplane is superior to that of a traditional wing-shaped catapult glider.

The tail wing consists of a first tail wing 3-2 and a vertical second tail wing 3-1, the first tail wing is fixedly arranged on the fuselage in a manner of anticlockwise rotating for 2-3 degrees by taking the fuselage as a central axis and taking a horizontal plane as a starting point (taking a certain point behind the ejection type gliding aircraft model as an observation point), namely, the left end of the first tail wing is positioned below (obliquely) the right end of the first tail wing. The second tail is located to the right of the centerline of the first tail. The lower end of the second tail wing is fixedly mounted on the upper surface of the first tail wing, and the left side surface of the second tail wing is fixedly mounted on the machine body. In the present invention, as shown in fig. 7 to 9, the first tail wing is fixedly mounted on the fuselage by rotating counterclockwise by 2 to 3 degrees with the fuselage as a central axis and a horizontal plane as a starting point, and has the advantages that: the first tail wing and the first tail wing generate lift force to deflect left, so that the tail part of the airplane deflects left, the nose of the airplane deflects right, and the airplane can hover rightwards; and secondly, the situation that the airplane is enabled to hover by deflecting the second tail wing to the right is avoided, and the situation that the airplane is disordered and difficult to adjust during catapult takeoff is avoided.

The conventional take-off mode of the catapult glider generally adopts the following modes: 1. the mode of the plane body inclined and horizontally catapulted and spirally ascended, the mode of the weight pulling rudder 2, and the mode of the movable elastic elevator 3 (the mode is the mode of the small flying dragon catapult model plane) as shown in figure 10. The disadvantage of spiral rising is that the height is not easy to increase; the disadvantage of the heavy hammer rudder pulling is that a certain weight is required, and the heavy hammer rudder pulling is not suitable for small catapult planes; the movable elastic elevator has the defects that the elasticity is not easy to control, multiple times of careful debugging are needed, and the difficulty is very high. The ejection mode of the ejection type glider model of the invention is as follows: the catapult type gliding aircraft model is held by the left hand and is taken by the right hand (the left hand is obliquely above the right hand), and the model takes off in a catapult mode of a large angle (75-85 degrees) with the ground. The ejection type gliding aircraft model is almost vertically upward when taking off, and simultaneously rolls anticlockwise, and changes into horizontal gliding when reaching the highest point. The catapult-type gliding aircraft model can take off in a straight line and vertically climb, almost all the energy of rubber bands can be used for improving the height of the aircraft, and the climbing height exceeds 30 meters. The increase in altitude also increases the chances that the aircraft will encounter an up-draft, increasing the time the aircraft will remain empty.

The invention has been described in an illustrative manner, and it is to be understood that any simple variations, modifications or other equivalent changes which can be made by one skilled in the art without departing from the spirit of the invention fall within the scope of the invention.

Claims

1. A catapult-assisted glider model, comprising: the airplane comprises an airplane body (2) and wings (1) and an empennage (3) which are installed on the airplane body (2), and is characterized in that the wings (1) comprise wing middle sections (1-2) and 2 wing tips (1-1), the 2 wing tips (1-1) are fixedly installed at two ends of the wing middle sections (1-2) respectively, the dihedral angles of the wing tips (1-1) are 15-25 degrees, a step platform (4) is formed on the upper surface of the wings (1) along the length direction of the wings (1), the step platform (4) is located at the position where the chord length is 45-55%, and the step height of the step platform (4) is 4% -6% of the chord length; the tail wing (3) consists of a first tail wing (3-2) and a vertical second tail wing (3-1), the first tail wing (3-2) is installed on the machine body (2) in a manner of rotating for 2-3 degrees by taking the machine body (2) as a central shaft and taking a horizontal plane as a starting point, the lower end of the second tail wing (3-1) is fixedly installed on the upper surface of the first tail wing (3-2), and the side surface of the second tail wing (3-1) is fixedly installed on the machine body (2);

the second tail wing (3-1) is located to the right of the centerline of the first tail wing (3-2);

the left end of the first tail wing (3-2) is positioned below the right end of the first tail wing (3-2);

the first empennage (3-2) is installed on the machine body (2) in a manner of rotating counterclockwise by 2-3 degrees by taking the machine body (2) as a central axis and taking a horizontal plane as a starting point.

2. The catapult-assisted glider model according to claim 1, characterized in that the tip (1-1) dihedral is 20 degrees.

3. The catapult-assisted glider model according to claim 1, wherein the mid-wing sections (1-2) are mounted to the fuselage (2) by mortise and tenon joint.

4. The catapult-assisted glider model according to claim 1, characterized in that the wingtips (1-1) are fixed to the two ends of the wing center piece (1-2) by means of adhesive bonding.

5. The catapult-type gliding aircraft model as claimed in claim 1, characterized in that the step (4) is located at a position where the chord length is 50%.

6. The catapult-type glider model according to claim 1, wherein a through hole for adjusting the center of gravity of the catapult-type glider model is formed at the front of the body (2).