Rotary folding empennage of aircraft and use method of rotary folding empennage

Abstract

According to the rotary folding empennage of the aircraft and the using method, two or more empennages are arranged at the tail of a fuselage of the aircraft, each empennage is connected with a steering engine, each empennage is divided into a first empennage section and a second empennage section, the two empennage sections are connected through a folding and unfolding mechanism, and folding and unfolding of the empennages can be achieved. The first empennage is provided with a rotating shaft which penetrates through the fuselage tail skin to be connected with the steering engine, a gap is formed between the empennage and the fuselage tail, and when the empennage is in a folded state, the second empennage is close to the fuselage tail; when the empennage is in an unfolded state, the second empennage body rotates around the hinge to be flush with the first empennage body, after the empennage is unfolded, the empennage can rotate along with the rotating shaft under driving of the steering engine, and control over the flight attitude of the aircraft is achieved.

Description

Technical Field

[0001] The invention is applicable to the field of aircraft design with folding wings, in particular to an aircraft rotating folding tail wing and a use method thereof. Background Art

[0002] Folding wings can reduce the lateral size of the aircraft, reduce the size of the packaging box, facilitate storage, transportation and launch, and greatly increase its applicability. For aircraft using folding technology, the wings are folded before the aircraft is launched, and the wings can be quickly unfolded after launch, making the aircraft stable in flight, which plays an immeasurable role in improving the aircraft's maneuverability, combat effectiveness and wartime survivability.

[0003] The tail folding and unfolding mechanism is used to ensure the smooth folding and unfolding of the tail. Its performance directly affects the rapidity, stability and reliability of the tail unfolding. After the tail is unfolded, under the control of the servo, the tail can rotate around the rotation axis to achieve the control of the aircraft's attitude. The method of quickly unfolding and locking the tail is the key to the folding wing design, which is directly related to whether the aircraft can fly normally and whether it can successfully perform the mission. Summary of the invention

[0004] The purpose of the present invention is to provide a rotating folding tail of an aircraft and a method of using the same. After the aircraft is launched, the tail can be quickly unfolded and locked, and then the tail is rotated under the drive of a servo to control the flight attitude of the aircraft.

[0005] A rotating folding tail of an aircraft, wherein two or more tails are arranged at the tail of the fuselage, each tail being connected to a servo respectively, and characterized in that each tail is divided into a first section tail and a second section tail, and the two sections tail are connected by a folding and unfolding mechanism, so that the tail can be folded and unfolded. The first section tail is provided with a rotating shaft, which passes through the skin of the tail of the fuselage and is connected to the servo, and a gap is provided between the tail and the tail of the fuselage. When the tail is in a folded state, the second section tail is close to the tail of the fuselage; when the tail is in an unfolded state, the second section tail rotates around a hinge until it is flush with the first section tail. After the tail is unfolded, the tail can rotate along with the rotating shaft under the drive of the servo, so as to control the flight attitude of the aircraft.

[0006] The rotating folding tail wing of the aircraft is characterized in that the folding and unfolding mechanism comprises a hinge, a torsion spring, a push rod, a stop pin and a compression spring. The hinge comprises a first hinge, a second hinge and a hinge axis, and the first hinge and the second hinge can rotate relative to each other around the hinge axis under the action of the torsion spring; the first hinge is connected to the first section tail wing, and the second hinge is connected to the second section tail wing. A pin hole parallel to the hinge axis is provided on the first hinge, and a limit hole parallel to the hinge axis is provided on the end of the second hinge. When the first hinge and the second hinge are unfolded, the pin hole is coaxial with the limit hole. A strip hole connected to the pin hole is provided on the surface of the first section tail wing. A push rod, a stop pin and a compression spring are installed in the pin hole. The stop pin is embedded in the pin hole through the compression spring, and the push rod is installed on the stop pin. The push rod extends from the strip hole connected to the pin hole. By pushing the push rod, the stop pin can be translated along the axial direction of the pin hole, so that the end of the stop pin can be extended into or out of the limit hole on the second hinge.

[0007] The rotating folding tail of the aircraft is characterized in that a locking mechanism is provided between the second tail section and the tail of the fuselage, and the locking mechanism includes a locking rod, a locking seat, a baffle and a compression spring. The front end of the locking rod is provided with a T-shaped end, and the locking rod is connected to the second tail section. The baffle is provided with a compression groove matching the T-shaped end of the locking rod, one end of the baffle is hinged in the cavity of the locking seat, and the other end of the baffle extends out of the locking seat and is connected to a rope or a pull rod providing unlocking power, and a compression spring is provided between the baffle and the locking seat, and the compression spring is embedded in the blind hole of the locking seat. If the influence of aerodynamic force is not considered, the locking rod can be directly fixed to the second tail section, so that part of the locking rod protrudes from the skin of the second tail section; in order to reduce the influence of the locking rod on aerodynamic force and to improve the appearance, a compression spring can be installed on the locking rod, and when the baffle of the locking mechanism releases the blocking of the locking rod, the locking rod can be retracted into the second tail section under the action of the compression spring.

[0008] The method for using the rotating and folding tail of an aircraft is characterized in that, when the tail is in a folded state, the second tail is attached to the tail of the fuselage around the hinge axis, the locking rod on the second tail is inserted into the locking seat at the tail of the fuselage, and the pressing groove of the baffle in the lock seat is pressed against the front end of the locking rod, thereby completing the locking of the second tail relative to the tail of the fuselage. At this time, the compression spring embedded in the first hinge pin hole presses the front end of the baffle pin to the outside of the limiting hole of the second hinge; when the tail needs to be unfolded, a rope or pull rod providing unlocking power pulls the baffle of the locking mechanism to release the lock of the baffle on the locking rod, so that the second tail rotates around the hinge axis under the action of the torsion spring and away from the tail end of the fuselage. After the second tail is unfolded to be flush with the first tail, the compression spring embedded in the first hinge pin hole presses the front end of the baffle pin into the limiting hole of the second hinge, thereby locking the relative positions of the first hinge and the second hinge so that they cannot rotate around the hinge axis, thereby preventing the tail from folding.

[0009] The advantages of the present invention are that the rotating folding and unfolding mechanism of the rotating folding tail of the aircraft is simple, the tail can be quickly unfolded and positioned and locked, and the tail can also be fixed when folding the tail. The entire mechanism has high reliability and good processability and interchangeability. 1) The baffle is pulled by the unlocking power to release the lock on the locking rod, and the second section of the tail is rotated under the action of the torsion spring to achieve rapid unfolding of the tail. 2) Through the combined action of the hinge and the stop pin, the folding wing is locked after it is unfolded to a set angle. 3) The push of the stop pin by the push rod realizes unlocking after the tail is unfolded, ensuring the folding function of the aircraft. 4) By connecting the rotating shaft with the servo, the entire wing surface can be deflected, realizing the attitude control of the aircraft and maintaining flight stability. 5) The structure of this mechanism is simple and easy to implement, and it saves space and weight. It is suitable for various types of aircraft and solves the technical difficulties of realizing the folding, unfolding, locking and rotating functions of the tail under small space and small volume conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 This is a schematic diagram of the rotating and folding tail structure of the aircraft.

[0011] Figure 2 This is a schematic diagram of the aircraft's rotating folding tail in the folded state.

[0012] Figure 3 Schematic diagram of the folding and unfolding mechanism.

[0013] Figure 4 Schematic diagram of the tail wing locking mechanism.

[0014] Figure 5 for Figure 4 AA direction view locking rod installation diagram.

[0015] Figure 6 It is a schematic diagram of the first hinge structure.

[0016] Figure 7 It is a schematic diagram of the second hinge structure.

[0017] Name of the numbers in the figure:

[0018] Explanation of numbers in the figure: 1. tail of fuselage, 2. first section of tail wing, 3. second section of tail wing, 4. locking rod, 5. rotating shaft, 6. locking seat, 7. first hinge, 8. push rod, 9. stop pin, 10. limiting hole, 11. first compression spring, 12. second hinge, 13. torsion spring, 14. hinge axis, 15. pin, 16. baffle, 17. blind hole, 18. pin shaft, 19. second compression spring, 20. through hole, 21. third compression spring, 22. pin hole, 23. hinge axis hole. DETAILED DESCRIPTION

[0019] With reference to the accompanying drawings, the present invention will be further described in detail in combination with the accompanying drawings and embodiments, but they are not intended to be a basis for limiting the present invention in any way.

[0020] See the attached figure, Figure 1 , Figure 2 As shown, the rotating folding tail of the present application is mainly arranged with two or more tails on both sides of the fuselage tail 1, each tail is connected to a servo respectively, each tail is divided into a first section tail 2 and a second section tail 3, and the two sections of the tail are connected by a folding and unfolding mechanism, which can realize the folding and unfolding of the tail; the first section tail 1 is provided with a rotating shaft 5, and the rotating shaft 5 passes through the skin of the fuselage tail 1 and is connected to the servo, and the tail is not in contact with the fuselage tail 1, and an appropriate gap is provided. When the tail is in the folded state, the second section tail 3 is close to the fuselage tail 1; when the tail is in the unfolded state, the second section tail 3 rotates around the hinge to be flush with the first section tail 2. After the tail is unfolded, under the drive of the servo, the tail can realize the deflection of the tail with the rotation of the rotating shaft 5.

[0021] The rotating shaft 5 can be a part of the first tail section 2, or a part of the first hinge 7 connected to the first tail section 2. The other end of the rotating shaft 5 is connected to the steering gear and can rotate around the through hole of the tail part 1 of the fuselage under the drive of the steering gear.

[0022] like Figure 3 As shown, the folding and unfolding mechanism of the rotating folding tail wing comprises a first hinge 7 and a second hinge 12, a push rod 8, a stop pin 9, a first compression spring 11, a torsion spring 13, a hinge shaft 14 and a pin 15. The first hinge 7 is fixedly connected to the first section tail wing 2, and the second hinge 12 is fixedly connected to the second section tail wing 3. The first hinge 7 and the second hinge 12 can rotate around the hinge shaft 14 under the action of the torsion spring 13, thereby realizing the folding and unfolding of the tail wing. The first hinge 7 is provided with a pin hole 22, in which the push rod 8, the stop pin 9 and the first compression spring 11 are installed. The push rod 8 is installed at the tail of the stop pin 9. A strip hole connected to the pin hole 22 is provided on the surface of the first section tail wing 2. The push rod 8 extends out of the strip hole connected to the pin hole to form the skin of the first section tail wing 2. Pushing the push rod 8 can realize the extension and retraction of the stop pin 9 in the pin hole 22. When the tail is folded, the second hinge 12 compresses the stop pin 9 into the pin hole 22 of the first hinge 7; when the tail is unfolded, the second tail 3 rotates to be flush with the first tail 2, and the stop pin 9, under the action of the first compression spring 11, extends from the first hinge 7 and is inserted into the limiting hole 10 of the second hinge 12, thereby locking the tail and ensuring that the tail is no longer folded or unfolded. When the tail needs to be folded, the push rod 8 is pushed from the opening of the skin of the first section of the tail 2 to withdraw the stop pin 9 from the limiting hole 10 of the second hinge 12, and then the second section of the tail 3 is pressed to achieve the folding of the tail.

[0023] like Figure 6 , Figure 7As shown, the axis of the pin hole 22 in the first hinge 7 is not on the same axis as the axis of the hinge shaft hole 23, and the axis of the limiting hole 10 in the second hinge 12 is not on the same axis as the axis of the hinge shaft hole 23, so that the tail wing can be locked after rotating a certain angle; the hinge shaft 14 is fixed to the hinge with a pin 15, so as to ensure that the hinge shaft 14 does not fall out of the hinge, preventing the first hinge 7 and the second hinge from separating 12.

[0024] like Figure 4 As shown, the locking mechanism of the rotating folding tail wing comprises a lock rod 4, a lock seat 6, a baffle 16, a pin 18 and a second compression spring 19. One end of the baffle 16 is installed in the slot of the lock seat 6 by the pin 18, and the baffle 16 can rotate in the slot around the pin 18. The other end of the baffle 16 is provided with a through hole 20, which is connected to a rope or a pull rod providing unlocking power. A blind hole 17 is provided in the lock seat 6, and a second compression spring 19 is installed in the blind hole 17. The baffle 16 is squeezed by the second compression spring 19 installed in the lock seat 6, so that the baffle 16 blocks the T-shaped end of the lock rod 4, thereby realizing the locking function when the tail wing is folded; when the tail wing needs to be unfolded, the rope or pull rod providing the unlocking power pulls the baffle 16, and the baffle 16 overcomes the thrust of the second compression spring 19 and rotates around the pin 18 to eliminate the obstruction to the T-shaped end of the lock rod 4. The lock rod 4 is disengaged from the lock seat 6 under the push of the torsion spring 13 in the hinge, and the lock rod 4 rotates to the unfolded position together with the second section of the tail wing 3.

[0025] If the influence of aerodynamic force is not considered, the locking rod 4 can be directly fixed to the second tail section 3 so that part of the locking rod protrudes out of the skin of the second tail section 3.

[0026] In order to reduce the influence of the locking rod 4 on the aerodynamic force and improve the appearance, the locking rod 4 can be Figure 5 As shown, a third compression spring 21 is installed on the locking rod 4. When the baffle 16 of the locking mechanism releases the blocking of the locking rod 4, the locking rod 4 can be retracted into the second tail section 3 under the action of the third compression spring 21.

Claims

1. An aircraft with a rotating folding tail, wherein two or more tails are arranged at the tail of the aircraft, each tail being connected to a steering gear, characterized in that: Each tail wing is divided into a first section and a second section. The two sections are connected by a folding and unfolding mechanism, which can realize the folding and unfolding of the tail wing. The first section of the tail wing is provided with a rotating shaft, which passes through the tail skin of the fuselage and is connected to the servo. There is a gap between the tail wing and the tail of the fuselage. When the tail wing is folded, the second section of the tail wing is close to the tail of the fuselage; when the tail wing is unfolded, the second section of the tail wing rotates around the hinge to be flush with the first section of the tail wing. After the tail wing is unfolded, the tail wing can rotate with the rotating shaft under the drive of the servo to realize the control of the flight attitude of the aircraft.

2. The rotating folding tail of an aircraft according to claim 1, characterized in that: The folding and unfolding mechanism comprises a hinge, a torsion spring, a push rod, a stop pin and a compression spring. The hinge comprises a first hinge, a second hinge and a hinge axis. The first hinge and the second hinge can rotate relative to each other around the hinge axis under the action of the torsion spring; the first hinge is connected to the first section tail wing, and the second hinge is connected to the second section tail wing. A pin hole parallel to the hinge axis is provided on the first hinge, and a limiting hole parallel to the hinge axis is provided on the end head of the second hinge. When the first hinge and the second hinge are in the unfolded state, the pin hole is coaxial with the limiting hole. A strip hole connected to the pin hole is provided on the surface of the first section tail wing, and a push rod, a stop pin and a compression spring are installed in the pin hole. The stop pin is embedded in the pin hole through the compression spring, and the push rod is installed on the stop pin. The push rod extends from the strip hole connected to the pin hole. The stop pin can be translated along the axial direction of the pin hole by pushing the push rod, so that the end head of the stop pin can extend into or exit the limiting hole on the second hinge.

3. The rotating folding tail wing of an aircraft according to claim 1, characterized in that: A locking mechanism is provided between the second tail section and the tail of the fuselage, and the locking mechanism includes a locking rod, a locking seat, a baffle and a compression spring. The front end of the locking rod is provided with a T-shaped end, and the locking rod is connected to the second tail section. The baffle is provided with a compression groove matching the T-shaped end of the locking rod, one end of the baffle is hinged in the cavity of the locking seat, and the other end of the baffle extends out of the locking seat and is connected to a rope or a pull rod providing unlocking power. A compression spring is provided between the baffle and the locking seat, and the compression spring is embedded in the blind hole of the locking seat.

4. The rotating folding tail of an aircraft according to claim 1, characterized in that: If the influence of aerodynamic force is not taken into consideration, the locking rod can be directly fixed to the second tail section so that part of the locking rod protrudes out of the skin of the second tail section; in order to reduce the influence of the locking rod on aerodynamic force and improve the appearance, a compression spring can be installed on the locking rod. When the baffle of the locking mechanism releases the obstruction to the locking rod, the locking rod can be retracted into the second tail section under the action of the compression spring.

5. The method for using the rotating folding tail of an aircraft as claimed in claim 1, 2, 3 or 4, characterized in that: When the tail is in a folded state, the second tail is attached to the tail of the fuselage around the hinge axis, the locking rod on the second tail is inserted into the lock seat at the tail of the fuselage, and the pressure groove of the baffle in the lock seat is pressed against the front end of the locking rod, thereby completing the locking of the second tail relative to the tail of the fuselage. At this time, the compression spring embedded in the pin hole of the first hinge presses the front end of the baffle pin to the outside of the limiting hole of the second hinge; when the tail needs to be unfolded, the rope or pull rod providing unlocking power pulls the baffle of the locking mechanism to release the lock of the baffle on the locking rod, so that the second tail rotates around the hinge axis under the action of the torsion spring and away from the tail end of the fuselage. After the second tail is unfolded to be flush with the first tail, the compression spring embedded in the pin hole of the first hinge presses the front end of the baffle pin into the limiting hole of the second hinge, locking the relative position of the first hinge and the second hinge so that they cannot rotate around the hinge axis, thereby preventing the tail from folding.

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