A single-power source wing surface variable sweep and locking mechanism

Abstract

A single-power source wing surface variable sweep and locking mechanism includes a power output rod, a rocker arm, a rotating shaft, a locking member, a wing surface and a wing spar, wherein the power output rod is hinged to the rocker arm, the rocker arm is mounted on the rotating shaft, the wing spar is fixedly connected to the fuselage, the wing surface's rotary joint is placed in the wing spar's clamping ear, and the rotating shaft passes through the wing surface and is fixedly connected to the wing spar; the locking member passes through the rotating shaft, rocker arm, and wing spar and is inserted into the wing surface, the locking member cannot rotate around the rotating shaft, and a spring is connected between the locking member and the fuselage; the wing surface is provided with an initial locking hole, a locking hole and a groove; the locking member is provided with a zigzag groove for placing the rocker arm in the initial position. The present invention relies on a single power source to achieve the variable sweep function of the wing surface and the unlocking and locking of the wing surface at a specific angle, and integrates the variable sweep function of the wing surface, the unlocking and locking mechanism into one, effectively reducing the pressure of the wing surface variable sweep system on the energy power system, structural weight and internal space of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft structures, and in particular to a single-power-source wing surface sweep-variable and locking mechanism. Background Art

[0002] The sweep angle of the wing significantly affects the aerodynamic characteristics of an aircraft. Variable wing sweep technology not only provides technical support for achieving better aerodynamic performance during flight, but also expands the aircraft's mission envelope. After the wing's sweep angle is changed, the variable-sweep mechanism must promptly lock the wing. Currently, most variable-sweep aircraft primarily rely on continuously supplying energy to the variable-sweep power source to maintain the sweep angle, or employ a separate power source to achieve wing lock and unlock functions. The continuous power supply method places a significant burden on the energy and power systems of small UAVs, while the use of a separate power source results in a waste of volume, weight, and cost. Therefore, a mechanism is needed that can achieve both wing sweep angle change and wing lock and unlock simultaneously, relying solely on a single power source and without the need for continuous power supply. Summary of the Invention

[0003] The technical problem solved by the present invention is to provide a single-power source wing surface variable sweep and locking mechanism to solve the problems in the above-mentioned background technology.

[0004] The technical problem solved by the present invention is achieved by adopting the following technical solutions:

[0005] A single-power source wing surface sweep and locking mechanism includes a power output rod, a rocker arm, a rotating shaft, a locking member, a wing surface and a wing spar, wherein the power output rod and the rocker arm are connected by a hinge, and the power output rod can rotate around the hinge and the rocker arm; the rocker arm is sleeved on the rotating shaft, the wing spar is fixedly connected to the fuselage, the rotary joint of the wing surface is placed in the clamping ear of the wing spar, and the rotating shaft passes through the wing surface and is fixedly connected to the wing spar; the locking member passes through the rotating shaft, the rocker arm, and the wing spar and is inserted into the wing surface, and the locking member It cannot rotate around the rotating shaft, and a spring is connected between the locking piece and the fuselage. Under the action of the spring force, the locking piece is pressed against the rotating shaft. The wing surface is provided with an initial locking hole for inserting the locking piece to form an initial lock on the wing surface, a locking hole for changing different sweep angles and a groove for pushing the wing surface to rotate through a rocker arm. The rocker arm drives the wing surface to rotate around the rotating shaft to achieve changes in the sweep angle behind the wing surface at multiple angles. The locking piece is provided with a serrated groove for placing the rocker arm in the initial position.

[0006] In the present invention, two stop rings are installed on the rotating shaft, and the stop rings installed on the rotating shaft are used to limit the displacement of the rocker arm in the axial direction of the rotating shaft.

[0007] In the present invention, the groove is provided on the rotary joint and is used to push the airfoil to rotate through the rocker arm, and the groove is a U-shaped groove.

[0008] In the present invention, the wing surface and the wing beam are respectively provided with a shaft hole for the shaft to pass through.

[0009] In the present invention, the rocker arm includes a push rod and a push rod. The push rod is located at the initial position of the serrated groove of the locking member, and the push rod is located in the center of the U-shaped groove of the airfoil rotary joint.

[0010] In the present invention, a U-shaped groove is provided on the wing spar.

[0011] In the present invention, the locking member includes a locking pin, which passes through the U-shaped groove of the spar and is inserted into the initial locking hole on the wing surface.

[0012] In the present invention, the zigzag groove includes a horizontal section and a tooth groove.

[0013] When the cam is in operation, the push rod is pressed against the rotating shaft again under the action of the spring, and the locking pin moves with the locking member and is inserted into the locking hole under the corresponding sweep angle of the wing surface, and the wing surface is locked; repeat the above operation, and the wing surface continues to change the sweep angle in the same direction. When the wing surface changes the sweep angle in the opposite direction, the output direction of the power source needs to be reversed.

[0014] Beneficial effects: The present invention relies on a single power source to realize the variable sweep function of the wing surface and the unlocking and locking of the wing surface at a specific angle, and integrates the variable sweep function of the wing surface, the unlocking and locking mechanism into one, effectively reducing the pressure of the variable sweep system of the wing surface on the energy power system, structural weight and internal space of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is an isometric view of a preferred embodiment of the present invention.

[0016] Figure 2 It is a front view of a preferred embodiment of the present invention.

[0017] Figure 3 It is a left view of a preferred embodiment of the present invention.

[0018] Figure 4 It is a top view of a preferred embodiment of the present invention.

[0019] Figure 5 for Figure 4 Cross-sectional view at AA in the middle.

[0020] Figure 6 for Figure 4 Cross-sectional view at the middle BB.

[0021] Figure 7 Schematic diagram of the wing surface sweep change process in a preferred embodiment of the present invention (the wing beam is hidden). Implementation Method

[0022] In order to make the technical means, creative features, objectives and effects achieved by the present invention easier to understand, the present invention is further described below with reference to specific illustrations.

[0023] See also Figures 1 to 7 A single-power source wing surface variable sweep and locking mechanism comprises a power output rod 1, a rocker arm 2, a rotating shaft 3, a locking member 4, an wing surface 5 and a wing spar 6, wherein the power output rod 1 is connected to the rocker arm 2 by a hinge, and the power output rod 1 can rotate around the hinge and the rocker arm 2; the rocker arm 2 is sleeved on the rotating shaft 3, and two stop rings are installed on the rotating shaft 3. The stop ring installed on the rotating shaft 3 limits the axial displacement of the rocker arm 2 in the rotating shaft 3, and the power output rod 1 drives the rocker arm 2 to rotate around the rotating shaft 3; the wing spar 6 is fixedly connected to the fuselage, the wing surface 5 is placed in the clamping ear of the wing spar 6, and the rotating shaft 3 passes through the wing surface 5 and is fixed to the wing spar 6 Connection; the locking piece 4 passes through the rotating shaft 3, the rocker arm 2, and the wing beam 6 and is inserted into the wing surface 5. The locking piece 4 cannot rotate around the rotating shaft 3, and a spring is connected between the locking piece 4 and the fuselage. Under the action of the spring force, the locking piece 4 is pressed against the rotating shaft 3; the wing surface 5 is provided with an initial locking hole for inserting the locking piece 4 to form an initial locking of the wing surface 5, a locking hole for changing different sweep angles and a groove for pushing the wing surface 5 to rotate through the rocker arm 2. The rocker arm 2 drives the wing surface 5 to rotate around the rotating shaft 3 to achieve changes in the sweep angle behind the wing surface at multiple angles; the locking piece 4 is provided with a serrated groove for placing the rocker arm 2 in the initial position.

[0024] In this embodiment, a rotary joint is provided on the airfoil 5 , and the rotary joint is placed in the clamping ear of the spar 6 .

[0025] In this embodiment, the groove is provided on the rotary joint, and is used to push the airfoil 5 to rotate through the rocker arm 2, and the groove is a U-shaped groove.

[0026] In this embodiment, the wing surface 5 and the wing beam 6 are respectively provided with a shaft hole for the shaft 3 to pass through.

[0027] In this embodiment, the rocker arm 2 includes a push rod 2-1 and a push rod 2-2. The push rod 2-1 is located at the initial position of the serrated groove of the locking member 4, and the push rod 2-2 is located in the center of the U-shaped groove of the wing surface 5 rotary joint.

[0028] In this embodiment, a U-shaped groove is provided on the spar 6 .

[0029] In this embodiment, the locking member 4 includes a locking pin 4 - 1 , which passes through the U-shaped groove of the spar 6 and is inserted into the initial locking hole on the wing surface 5 .

[0030] In this embodiment, the sawtooth groove includes a horizontal section and a tooth groove.

[0031] When the cam 2 is in the upright position, the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam 2 is in the upright position, and the cam

[0032] Here's how it works:

[0033] A single power source pushes the power output rod 1 to move forward, and the power output rod 1 drives the rocker arm 2 to rotate around the rotating shaft 3. The push rod 2-1 moves along the serrated groove on the locking piece 4 to the horizontal section to push the locking piece 4 upward, and the locking pin 4-1 disengages from the initial locking hole, and the wing surface 5 is unlocked; at this time, the push rod 2-2 is tightly attached to the end of the U-shaped groove of the wing surface 5. Under the action of the power source, the push rod 2-2 pushes the wing surface 5 to rotate. When the wing surface 5 reaches the specified sweep angle, the power source acts in the opposite direction. The power output rod 1 and the rocker arm 2 move in the opposite direction under the action of the power source, and the push rod 2-1 moves from the horizontal section of the serrated groove in the locking piece 4 to the tooth groove , the push rod 2-2 moves in the opposite direction along the U-shaped groove of the wing surface 5 to the center position of the U-shaped groove, and the locking member 4 is re-pressed with the rotating shaft 3 under the action of the spring force, and the locking pin 4-1 moves with the locking member 4 and is inserted into the locking hole under the corresponding sweep angle of the wing surface 5, and the wing surface 5 is locked; repeat the above operation, the wing surface 5 continues to change the sweep angle in the same direction. When the wing surface 5 changes the sweep angle in the opposite direction, the output direction of the power source needs to be reversed; in the process of changing the sweep angle of the wing surface 5, only a single power source is involved. At the same time, the integration of the locking mechanism and the motion mechanism also effectively reduces the use of the internal space of the fuselage by the entire mechanism.

Claims

1. A single-power source airfoil variable sweep and locking mechanism, comprising a power output lever, a rocker arm, a rotating shaft, a locking member, an airfoil and a wing spar, characterized in that: The power output rod is hinged to the rocker arm, and the power output rod can rotate with the rocker arm; the rocker arm is mounted on the rotating shaft, the wing spar is fixedly connected to the fuselage, the rotary joint of the wing surface is placed in the clamping ear of the wing spar, and the rotating shaft passes through the wing surface and is fixedly connected to the wing spar; the locking piece passes through the rotating shaft, the rocker arm, and the wing spar and is inserted into the wing surface, and a spring is connected between the locking piece and the fuselage for pressing the locking piece and the rotating shaft; the wing surface is provided with an initial locking hole for inserting the locking piece to form an initial locking of the wing surface, a locking hole for changing different sweep angles, and a groove for pushing the wing surface to rotate by the rocker arm, and the rocker arm drives the wing surface to rotate around the rotating shaft to realize the change of the sweep angle behind the wing surface at multiple angles; the locking piece is provided with a serrated groove for placing the rocker arm in the initial position.

2. A single-power-source airfoil variable sweep and locking mechanism according to claim 1, characterized in that: Two stop rings are installed on the rotating shaft.

3. The single-power source airfoil variable sweep and locking mechanism according to claim 1, characterized in that: The groove used to push the airfoil to rotate through the rocker arm is arranged on the rotary joint, and the groove is a U-shaped groove.

4. A single-power-source airfoil variable sweep and locking mechanism according to claim 3, characterized in that: The rocker arm includes a push rod and a push rod. The push rod is located at the initial position of the serrated groove of the locking member, and the push rod is located in the center of the U-shaped groove of the airfoil rotary joint.

5. The single-power source airfoil variable sweep and locking mechanism according to claim 1, characterized in that: A U-shaped groove is provided on the wing spar.

6. The single-power source airfoil variable sweep and locking mechanism according to claim 1, characterized in that: The locking member includes a locking pin which passes through the wing spar and is inserted into an initial locking hole on the wing surface.

7. The single-power source airfoil variable sweep and locking mechanism according to claim 1, characterized in that: The zigzag groove includes a horizontal section and a tooth groove.

8. The single-power source airfoil variable sweep and locking mechanism according to claim 1, characterized in that: The wing surface and the wing beam are respectively provided with a rotating shaft hole for the rotating shaft to pass through.

9. A single-power-source wing surface variable sweep and locking mechanism according to any one of claims 1 to 8, characterized in that: When the wing is in use, the power source pushes the power output rod forward, the power output rod drives the rocking arm to rotate around the rotating shaft, the push rod moves along the serrated groove on the locking piece to the horizontal section to push the locking piece upward, the locking pin disengages from the initial locking hole, and the wing surface is unlocked; at this time, the push rod is in close contact with the end of the U-shaped groove of the wing surface under the action of the power source, and the push rod pushes the wing surface to rotate. When the wing surface reaches the specified sweep angle, the power source acts in the opposite direction, and the power output rod and the rocker arm move in the opposite direction under the action of the power source, the push rod moves from the horizontal section of the serrated groove in the locking piece into the tooth groove, and the push rod moves in the opposite direction along the U-shaped groove of the wing surface to the center position of the U-shaped groove. The locking piece is pressed against the rotating shaft again under the action of the spring force, and the locking pin moves with the locking piece and is inserted into the locking hole under the corresponding sweep angle of the wing surface, and the wing surface is locked; repeat the above operation, and the wing surface continues to change the sweep angle in the same direction; when the wing surface changes the sweep angle in the opposite direction, the output direction of the power source needs to be reversed.

Images