Adjustable control surface limiting mechanism

Abstract

The utility model provides an adjustable control surface limiting mechanism which comprises an adjusting screw sleeve, one end of the adjusting screw sleeve is connected with a base through a nut A, the other end of the adjusting screw sleeve is connected with a control surface support column through a nut B, and the adjusting screw sleeve, the base and the control surface support column are located in the same vertical direction. A simple mechanical structure is adopted, safety and reliability are high, and a control surface is not damaged; positive and negative thread design and lightweight design are adopted, the structure is simple, operation is convenient, cost is low, and anti-loosening measures are taken; the rotation limiting performance of the folding rudders is good, the folding rudders with different lengths and angle directions can be limited, and when the aircraft is ejected out of the cylinder, the limiting mechanism stably stays in the storage and transportation cylinder. The functions of limiting rotation of the aircraft folding rudder in the storage and transportation cylinder, stable and reliable separation of the limiting mechanism and the aircraft and no damage to the folding rudder in the process that the aircraft leaves the cylinder are achieved, and the safety and reliability of launching and flying of the aircraft are effectively improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of mechanical design and manufacturing, and relates to an adjustable rudder surface limiting mechanism. Background Art

[0002] The folding rudder plays an important role in the flight process of the aircraft. It is mainly used to generate additional aerodynamic force, form control force and control torque on the aircraft, and thus control the aircraft to fly according to the predetermined orbit. Since the aircraft is affected by various factors during the flight, the flight trajectory will change to a certain extent, so the deflection of the rudder wing must be used to adjust and correct the flight trajectory of the missile. Therefore, it is very important to ensure that the structure of the folding rudder is intact. The aircraft is usually stored in a storage and transportation tube and ejected out of the tube when needed. When the aircraft is assembled into the storage and transportation tube, the folding rudder needs to be folded into the tube. During transportation, the rudder wing is prone to deflect at a certain angle along the circumference in the tube. After the rudder wing is deflected, it is easy to interfere with the brake mechanism in the tube during the process of leaving the tube, affecting the deployment of the rudder wing, causing damage to the rudder wing structure, and thus causing serious accidents such as flight failure. Therefore, limiting the rotation of the folding rudder in the storage and transportation tube is the first step to ensure the successful flight of the aircraft. Usually an aircraft has four folding rudders distributed at different angles. How to limit the rotation of the aircraft's folding rudder in the storage and transportation tube without damaging the rudder surface and to adapt to different lengths and directions and to have a stable, reliable, economical and adjustable limit mechanism for the folding rudders at different angles in the storage and transportation tube is a problem that needs to be solved urgently.

[0003] The Chinese patent with publication number CN217533170U discloses a guide limit mechanism and railing for pipe fittings, including a body and a guide piece arranged at the lower end of the body, the guide piece has several pieces, the guide piece is provided with a groove with an opening inclined upward, a spring is provided on the upper inner wall of the groove, a limit block is provided at the lower part of the spring, one end of the limit block is connected to the guide piece through a connecting piece, and the other end is a free end; however, the limit mechanism acts on longitudinal expansion and contraction, and cannot meet the rotation limit problem of the folding rudder inside the cylinder. The present application can limit the folding rudders of different lengths and angles, realize the limited rotation of the folding rudder of the aircraft in the storage and transportation cylinder, and the limit mechanism and the aircraft are stably and reliably separated during the process of the aircraft leaving the cylinder, without damaging the function of the folding rudder. Utility Model Content

[0004] In order to solve the above technical problems, the utility model provides an adjustable rudder surface limiting mechanism.

[0005] The utility model is realized through the following technical solutions.

[0006] The utility model provides an adjustable rudder surface limiting mechanism, comprising an adjusting screw sleeve, one end of the adjusting screw sleeve is connected to a base through a nut A, and the other end of the adjusting screw sleeve is connected to a rudder surface bracket column through a nut B, and the adjusting screw sleeve, the base and the rudder surface bracket column are located in the same vertical direction.

[0007] Preferably, one end of the rudder surface support column is arranged as a V-shaped surface.

[0008] Preferably, one end of the rudder support column is connected to a cowhide pad.

[0009] Preferably, the nut A is a left-handed nut.

[0010] Preferably, the nut B is a right-handed nut.

[0011] Preferably, the interior of the adjusting screw sleeve is a forward and reverse thread structure.

[0012] The beneficial effects of the utility model are: it adopts a simple mechanized structure, has high safety and reliability, and does not damage the rudder surface; it adopts a positive and negative thread design and a lightweight design, has a simple structure, is easy to operate, is low in cost, and has anti-loosening measures; it has good performance in limiting the rotation of the folding rudder, and can limit the folding rudders of different lengths and angles. When the aircraft is ejected out of the tube, the limit mechanism stays stably in the storage and transportation tube. It realizes the function of limiting the rotation of the folding rudder of the aircraft in the storage and transportation tube and the stable and reliable separation of the limit mechanism and the aircraft during the process of the aircraft being ejected from the tube, without damaging the folding rudder, and effectively improves the safety and reliability of the aircraft launch and flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a structural schematic diagram of the utility model;

[0014] Figure 2 It is a structural schematic diagram of the utility model;

[0015] In the figure: 1-base, 2-nut A, 3-screw sleeve, 4-nut B, 5-rudder support column, 6-cowhide pad. DETAILED DESCRIPTION

[0016] The technical solution of the utility model is further described below, but the scope of protection required is not limited to the description.

[0017] like Figure 1-2 As shown,

[0018] An adjustable rudder surface limiting mechanism includes an adjusting screw sleeve 3, the threaded end of the adjusting screw sleeve 3 is connected to a base 1 through a nut A2, and the base 1 is fixed to a tray in a storage and transportation tube by a screw connection method, so that when an aircraft is ejected out of the tube, the limiting mechanism does not affect the unfolding of the folding rudder along with the aircraft out of the tube; the threaded end of the adjusting screw sleeve 3 is connected to a rudder surface support column 5 through a nut B4, and the adjusting screw sleeve 3, the base 1 and the rudder surface support column 5 are located in the same vertical direction. This limiting mechanism can efficiently, safely and reliably limit the function of the folding rudder of different directions and angles of the aircraft to rotate in the storage and transportation tube.

[0019] The nut A2 is a left-handed nut.

[0020] The nut B4 is a right-handed nut. The left-handed nut A2 and the right-handed nut B4 lock the adjusting screw sleeve 3 up and down to prevent the adjusting screw sleeve 3 from loosening during transportation, and further prevent the length of the rudder support column 5 from shrinking.

[0021] The locking port of the rudder support column 5 is set as a V-shaped surface. During operation, the rudder support column 5 is rotated to a suitable angle to ensure that the folding rudder is in the middle of the V-shaped mouth to meet the position requirements of the folding rudders at different directions and angles. The adjusting screw sleeve 3 is rotated to extend or contract the entire limit mechanism. The rudder support column 5 is extended to a suitable position of the rudder wing by adjusting the rudder support column 5 to ensure that the rudder wing contacts the upper cowhide pad. The adjusting screw sleeve 3 is fixed by rotating the left-hand nut 2 and the right-hand nut 4 to achieve locking and preventing the limit mechanism from loosening. The limit mechanism is stably and reliably separated from the aircraft during the aircraft exiting the tube, and the folding rudder of the aircraft is not damaged.

[0022] The V-shaped surface of the rudder support column 5 is bonded with a cowhide pad 6 by adhesive. The cowhide pad 6 has the function of preventing the rudder surface from being scratched when the rudder support column 5 locks the folding rudder, and can ensure that the limiting mechanism does not damage the surface of the folding rudder.

[0023] The adjusting screw sleeve 3 has a positive and negative thread structure inside. By adjusting the adjusting screw sleeve 3, the length of the entire limit mechanism can be extended or contracted, thereby locking the rudder support column 5 and the aircraft folding rudder; ensuring that the limit mechanism can reliably and effectively limit the rotation of the folding rudder. Ultimately, the purpose of adapting to different directions and angles, not scratching the rudder surface, reliably limiting the rotation of the folding rudder, and smoothly separating the limit mechanism from the folding rudder when the aircraft is ejected from the tube is achieved, meeting the requirements of economy, processability, practicality and operability, and providing guarantee for the safe, reliable and error-free launch of the aircraft.

[0024] In summary, the rudder limiting mechanism can meet the function of the rudder wings of different directions and angles rotating in the storage and transportation tube. It has been verified through a 2000-kilometer transportation test that the deflection angle of the folding rudder is no more than 0.1° after the limit mechanism is clamped and limited after the aircraft enters the tube and after a 2000-kilometer transportation test. The stability and reliability of the rudder limiting mechanism is fully verified through flight tests. When the aircraft is ejected from the tube, the limit mechanism does not interfere with the folding rudder, and it is effectively separated from the folding rudder and stays in the storage and transportation tube. The rudder limiting mechanism provided can stably, reliably, simply and adjustably limit the rotation of the aircraft folding rudder of different directions and angles in the tube without damaging the rudder surface. When the aircraft is ejected from the tube, the limit mechanism can be reliably separated from the folding rudder without affecting the deployment of the folding rudder. It meets the requirements of economy, processability, practicality and operability, and ensures the safe, reliable and error-free launch of the aircraft.

Claims

1. An adjustable rudder surface limiting mechanism, characterized in that: The invention comprises an adjusting screw sleeve (3), one end of which is connected to a base (1) via a nut A (2), and the other end of which is connected to a rudder support column (5) via a nut B (4); the adjusting screw sleeve (3), the base (1) and the rudder support column (5) are located in the same vertical direction.

2. An adjustable rudder surface limiting mechanism as claimed in claim 1, characterized in that: One end of the rudder support column (5) is arranged as a V-shaped surface.

3. The adjustable rudder surface limiting mechanism according to claim 1, characterized in that: One end of the rudder support column (5) is connected to a cowhide pad (6).

4. The adjustable rudder surface limiting mechanism according to claim 1, characterized in that: The nut A (2) is a left-handed nut.

5. The adjustable rudder surface limiting mechanism according to claim 1, characterized in that: The nut B (4) is a right-handed nut.

6. The adjustable rudder surface limiting mechanism according to claim 1, characterized in that: The interior of the adjusting screw sleeve (3) is a positive and negative thread structure.

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