Empennage locking and unlocking structure of embedded launched aircraft and aircraft

Abstract

The invention provides an embedded launching aircraft empennage locking and unlocking structure and an aircraft, and relates to the technical field of empennage locking and unlocking, the embedded launching aircraft empennage locking and unlocking structure comprises an empennage, the empennage comprises a connecting section and a folding section, the folding section is elastically connected with the connecting section in a folding manner, and the connecting section is connected with a steering engine; the lock hook is arranged on the outer side of the aircraft, the lock hook is clamped and matched with the outer end of the folding section, the folding section can be locked at the folding position, and when the steering engine drives the empennage to rotate, the outer end of the folding section can be separated from the lock hook, so that the empennage is unfolded; the problems that an existing empennage passive unfolding mode of an embedded launching aircraft is complex in structure, the size of a launching cylinder is large, and the unfolding time is uncontrollable are solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of tail wing locking and unlocking, and more specifically, relates to a tail wing locking and unlocking structure of an internally launched aircraft and the aircraft. Background Art

[0002] The use of folding tail technology is an effective way to improve the utilization of the limited space of internally launched aircraft. By reducing the space occupied by the tail, the combat effectiveness of the carrier aircraft can be effectively enhanced, and at the same time, the overall layout space of the aircraft can be increased under limited space.

[0003] Existing tail folding rudders mostly restrict the rotational freedom of the folding rudder surface by adding a pressure rudder structure on the inner wall of the launch tube. When the embedded launch aircraft is separated from the launch tube, the folding rudder constraint is released, and it is passively unlocked and deployed. Since there is friction contact between the folding rudder surface and the constraint structure, this design also needs to consider the protection of the folding rudder surface. At the same time, this unlocking method requires adding redundant structures in the launch tube, resulting in a larger launch tube volume that affects the safety of the carrier aircraft, and the tail wing deployment time cannot be controlled. These factors limit the mounting occasions of embedded launch aircraft. Summary of the invention

[0004] The purpose of the present invention is to address the deficiencies in the prior art and to provide a tail wing locking and unlocking structure and an aircraft for an internally launched aircraft, so as to solve the problems of the passive deployment method of the tail wing of the existing internally launched aircraft, such as complex structure, large launch tube volume and uncontrollable deployment timing.

[0005] In order to achieve the above object, the present invention provides a tail wing locking and unlocking structure of an aircraft with an internally embedded launch, comprising:

[0006] A tail wing, the tail wing comprising a connecting section and a folding section, the folding section is elastically foldably connected to the connecting section, and the connecting section is connected to a steering gear;

[0007] A locking hook is arranged on the outside of the aircraft, and the locking hook is engaged with the outer end of the folding section to lock the folding section in a folded position. When the servo drives the tail to rotate, the outer end of the folding section can be separated from the locking hook to allow the tail to unfold.

[0008] Optionally, the connecting section is rotatably connected to the folding section via a rotating shaft, and a first elastic component is provided between the connecting section and the folding section, and the first elastic component can apply an elastic force to the folding section to restore it to an unfolded state.

[0009] Optionally, the ends of the connecting section and the folding section that are close to each other are respectively provided with a first connecting sleeve and a second connecting sleeve, the rotating shaft is passed through the first connecting sleeve and the second connecting sleeve, and a limiting portion is provided on one side of the connecting section or the folding section, and the limiting portion can limit the folding portion from continuing to rotate when it returns to the unfolded state.

[0010] Optionally, the first elastic component is a torsion spring sleeved on the outer side of the rotating shaft.

[0011] Optionally, the locking hook is connected to the outer shell of the aircraft via an elastic retracting component, and the elastic retracting component can drive the locking hook to retract to a state where it is flush with the outer surface of the outer shell.

[0012] Optionally, a groove matching the shape of the locking hook is provided on the outer side of the shell, a through hole is provided at the bottom of the groove, and the elastic retractable component is provided inside the shell and passes through the through hole to be connected with the locking hook.

[0013] Optionally, the elastic retraction component includes a connecting rod, one end of which is connected to the locking hook, the middle part of the connecting rod slides through the through hole, and the other end of the connecting rod is connected to a second elastic component, which can apply an elastic force to the connecting rod to retract it toward the interior of the shell.

[0014] Optionally, the second elastic component is a compression spring.

[0015] Optionally, when the locking hook locks the folding section in the folding position, the servo is in a set deflection angle state, and when the tail wing is unfolded, the servo is reset to a zero position state.

[0016] The present invention also provides an aircraft, comprising:

[0017] an aircraft body, the aircraft body comprising an outer shell;

[0018] In the above-mentioned tail wing locking and unlocking structure of the embedded launching aircraft, the output shaft of the servo rotates through the outer shell and is connected to the tail wing located outside the outer shell.

[0019] The present invention provides a tail wing locking and unlocking structure for an aircraft that is embedded in a launch mode, and its beneficial effects are as follows: the tail wing locking and unlocking structure for the aircraft that is embedded in a launch mode is designed for a two-stage elastic folding tail wing, the connecting section of the tail wing is connected to the outer side of the aircraft through a steering gear, and is provided with a locking hook, when the tail wing of the aircraft is in a folded state, the folding section of the tail wing is engaged with the locking hook, and the locking hook keeps the folding section locked, and when the tail wing needs to be unfolded, the steering gear drives the connecting section of the tail wing to rotate, thereby driving a relative displacement between the folding section and the locking hook, the outer end of the folding section is separated from the locking hook, the locking hook of the folding section is released, and the unlocking is completed, and the unlocked folding section automatically returns to the unfolded state due to the elastic effect, thereby realizing the unfolding of the tail wing; the tail wing locking and unlocking structure for the aircraft that is embedded in a launch mode The structure ensures that the servo is at a fixed angle and the tail is in a folded state when the aircraft is stored, transported, or mounted. When the aircraft needs to unfold the tail during flight, it only needs to send a command to the servo to achieve the unfolding purpose. Except for the servo of the tail, the other components are purely mechanical components with a simple structure and high reliability. There are no flammable and explosive dangerous goods such as pyrotechnics and high-pressure gases, which have significant advantages in testing, transportation, and storage. The servo is used as an unlocking excitation for the elastic foldable tail without adding redundant equipment, thus achieving the dual purpose of the servo. At the same time, when the servo is not powered on, the servo shaft can also provide a certain locking torque to improve the reliability of locking the tail in the folded state. In the absence of external constraints, the tail can be folded and locked using only the aircraft's own components without generating any redundant objects.

[0020] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0022] Figure 1 A schematic diagram of a tail locking and unlocking structure of an internally launched aircraft in a tail folded state is shown according to an embodiment of the present invention.

[0023] Figure 2 A schematic diagram of a tail locking and unlocking structure of an internally launched aircraft in a tail deployed state according to an embodiment of the present invention is shown.

[0024] Figure 3 A schematic diagram of the tail deployment process of a tail locking and unlocking structure of an internally launched aircraft according to an embodiment of the present invention is shown.

[0025] Description of reference numerals:

[0026] 1. Connecting section; 2. Folding section; 3. Lock hook; 4. Housing; 5. Connecting rod; 6. Second elastic component; 7. Mounting block; 8. Servo. DETAILED DESCRIPTION

[0027] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0028] like Figures 1 to 3 As shown, the present invention provides a tail wing locking and unlocking structure for an aircraft with an internally embedded launch, comprising:

[0029] The tail wing comprises a connecting section 1 and a folding section 2, the folding section 2 is elastically foldably connected to the connecting section 1, and the connecting section 1 is connected to a steering gear 8;

[0030] The locking hook 3 is arranged on the outside of the aircraft. The locking hook 3 is engaged with the outer end of the folding section 2 to lock the folding section 2 in the folded position. When the servo 8 drives the tail to rotate, the outer end of the folding section 2 can be separated from the locking hook 3 to unfold the tail.

[0031] Specifically, in order to solve the problems that the passive deployment method of the tail of the existing embedded launch aircraft has a complex structure, a large launch tube volume, and uncontrollable deployment timing; the tail locking and unlocking structure of the embedded launch aircraft provided by the present invention is designed for a two-stage elastic folding tail, and the connecting section 1 of the tail is connected to the outside of the aircraft through a steering gear 8 and has a locking hook 3. When the tail of the aircraft is in a folded state, the folding section 2 of the tail is engaged with the locking hook 3, and the folding section 2 is kept locked by the locking hook 3. When the tail needs to be deployed, the steering gear 8 drives the connecting section 1 of the tail to rotate, thereby driving the folding section 2 and the locking hook 3 to generate relative displacement, the outer end of the folding section 2 separates from the locking hook 3, the locking of the folding section 2 by the locking hook 3 is released, and the unlocking is completed. The unlocked folding section 2 automatically returns to the deployed state due to the elastic effect, thereby realizing the deployment of the tail; The tail lock and unlock structure of the embedded launch aircraft ensures that the servo 8 is at a fixed angle and the tail is in a folded state when the aircraft is stored, transported, or mounted. When the aircraft needs to unfold the tail during flight, it only needs to send a command to the servo 8 to achieve the unfolding purpose. Except for the servo 8 of the tail, the other components are purely mechanical components with a simple structure and high reliability. There are no flammable and explosive dangerous goods such as pyrotechnics and high-pressure gases, which have significant advantages in testing, transportation, storage, etc. The servo 8 is used as an unlocking excitation for the elastic foldable tail without adding redundant equipment, so that the servo 8 can be used for two purposes. At the same time, when the servo 8 is not powered on, the servo 8 shaft can also provide a certain locking torque to improve the reliability of locking the tail in the folded state. In the absence of external constraints, the tail can be folded and locked using only the aircraft's own components without generating any redundant objects.

[0032] Optionally, the connecting section 1 and the folding section 2 are rotatably connected via a rotating shaft, and a first elastic component is provided between the connecting section 1 and the folding section 2, and the first elastic component can exert an elastic force on the folding section 2 to restore it to an unfolded state.

[0033] Specifically, the tail wing is divided into two ends. The connecting section 1 can be rotated by connecting to the servo 8 to adjust the angle of the rudder surface. The folding section 2 is rotatably connected to the outer end of the connecting section 1 to achieve folding and unfolding. The elastic force applied by the first elastic component to the folding section 2 can enable the folding section 2 to automatically unfold to the unfolded state by utilizing the elastic force after being unlocked.

[0034] Optionally, a first connecting sleeve and a second connecting sleeve are respectively provided at the ends of the connecting section 1 and the folding section 2 that are close to each other, and the rotating shaft is passed through the first connecting sleeve and the second connecting sleeve. A limiting portion is provided on one side of the connecting section 1 or the folding section 2, and the limiting portion can limit the continued rotation of the folding portion when it returns to the unfolded state.

[0035] Specifically, the limiting portion can adopt a raised structure, which can be on the connecting section 1 or the folding section 2, and can prevent the folding section 2 from continuing to rotate when the folding section 2 is in the unfolded state. The limiting portion cooperates with the first elastic component to maintain the unfolded state of the tail wing.

[0036] In this embodiment, the first elastic component is a torsion spring sleeved on the outer side of the rotating shaft.

[0037] Optionally, the locking hook 3 is connected to the outer shell 4 of the aircraft via an elastic retracting component, and the elastic retracting component can drive the locking hook 3 to retract to a state flush with the outer surface of the outer shell 4 .

[0038] Specifically, after the folding section 2 in the folded state is released from the locking hook 3 by the rotation of the servo 8, the elastic retracting component can automatically drive the locking hook 3 to retract on the outer shell 4 of the aircraft. The retracted locking hook 3 does not protrude from the outer surface of the outer shell 4, affecting the aerodynamic shape of the aircraft.

[0039] Optionally, a groove matching the shape of the lock hook 3 is provided on the outer side of the shell 4, a through hole is provided at the bottom of the groove, and the elastic retractable component is provided inside the shell 4 and passes through the through hole to be connected with the lock hook 3.

[0040] Specifically, after the lock hook 3 is retracted, it can be just embedded in the groove on the outside of the shell 4, so that the outer surface of the lock hook 3 follows the outer surface of the shell 4.

[0041] Optionally, the elastic retraction component includes a connecting rod 5, one end of the connecting rod 5 is connected to the locking hook 3, the middle of the connecting rod 5 slides through the through hole, and the other end of the connecting rod 5 is connected to a second elastic component 6, which can apply an elastic force to the connecting rod 5 to retract it toward the inside of the shell 4.

[0042] Specifically, one end of the second elastic component 6 is connected to the other end of the connecting rod 5, and the other end can be connected to the housing 4. The second elastic component 6 applies elasticity to the connecting rod 5, so that when the locking hook 3 is disengaged from the folding section 2, the connecting rod 5 can drive the locking hook 3 to automatically retract into the groove under the action of the elastic force.

[0043] In this embodiment, a mounting block 7 is provided on the inner side of the housing 4 , and the second elastic component 6 and the connecting rod 5 are mounted on the inner side of the housing 4 through the mounting block 7 .

[0044] In this embodiment, the second elastic component 6 is a compression spring.

[0045] Optionally, when the locking hook 3 locks the folding section 2 in the folding position, the steering gear 8 is in a state of setting a deflection angle, and when the tail wing is unfolded, the steering gear 8 is reset to a zero position state.

[0046] Specifically, in the locked state, the servo 8 is not in the zero position, but has a set deflection angle. When the tail needs to be unfolded, the servo 8 receives the command and rotates in the direction of resetting to the zero position, unlocking the folded tail, so that the servo 8 is reset to the zero position while the tail is unfolded. Compared with the servo 8 locking the folding section 2 in the zero position, the servo 8 is deflected when unlocking, which can simplify the operation and the actuation of the servo 8, so that the servo 8 is just in the zero position when the tail is unfolded.

[0047] In this embodiment, the surface shape of the side of the locking hook 3 away from the connecting rod 5 is matched with the outer surface shape of the housing 4 .

[0048] Specifically, the outer surface of the locking hook 3 retracted into the groove follows the outer surface of the housing 4 to maintain the desired aerodynamic shape of the housing 4 .

[0049] The present invention also provides an aircraft, comprising:

[0050] The aircraft body includes an outer shell 4;

[0051] In the tail wing locking and unlocking structure of the above-mentioned embedded launch aircraft, the output shaft of the servo 8 rotates through the outer shell 4 and is connected to the tail wing located outside the outer shell 4.

[0052] Specifically, the aircraft is an internally launched aircraft, and the tail wing of the aircraft adopts the above-mentioned tail wing locking and unlocking structure of the internally launched aircraft. When the servo 8 drives the connecting section 1 and the folding section 2 of the tail wing to rotate through the output shaft, the folding section 2 in the engaged state with the lock hook 3 disengages from the lock hook 3, completes the unfolding action under the action of the first elastic component, and enters the unfolded state. At the same time, under the action of the second elastic component 6, the lock hook 3 retracts into the groove on the outer shell 4 to avoid affecting the aerodynamic shape of the aircraft.

[0053] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A tail wing locking and unlocking structure for an internally launched aircraft, characterized in that: include: A tail wing, the tail wing comprising a connecting section and a folding section, the folding section is elastically foldably connected to the connecting section, and the connecting section is connected to a steering gear; A locking hook is arranged on the outside of the aircraft, and the locking hook is engaged with the outer end of the folding section to lock the folding section in a folded position. When the servo drives the tail to rotate, the outer end of the folding section can be separated from the locking hook to allow the tail to unfold.

2. The tail wing locking and unlocking structure of an internally launched aircraft according to claim 1, characterized in that: The connecting section is rotatably connected to the folding section via a rotating shaft. A first elastic component is provided between the connecting section and the folding section. The first elastic component can apply elastic force to the folding section to restore the folding section to an unfolded state.

3. The tail wing locking and unlocking structure of the internally launched aircraft according to claim 2, characterized in that: The ends of the connecting section and the folding section that are close to each other are respectively provided with a first connecting sleeve and a second connecting sleeve, the rotating shaft is inserted into the first connecting sleeve and the second connecting sleeve, and a limiting portion is provided on one side of the connecting section or the folding section, and the limiting portion can limit the folding portion from continuing to rotate when it returns to the unfolded state.

4. The tail wing locking and unlocking structure of the internally launched aircraft according to claim 3, characterized in that: The first elastic component is a torsion spring sleeved on the outer side of the rotating shaft.

5. The tail wing locking and unlocking structure of an internally launched aircraft according to claim 1, characterized in that: The locking hook is connected to the outer shell of the aircraft through an elastic retracting component, and the elastic retracting component can drive the locking hook to retract to a state flush with the outer surface of the outer shell.

6. The tail wing locking and unlocking structure of an internally launched aircraft according to claim 5, characterized in that: The outer side of the shell is provided with a groove matching the shape of the lock hook, the bottom of the groove is provided with a through hole, the elastic retractable component is arranged inside the shell and passes through the through hole to be connected with the lock hook.

7. The tail wing locking and unlocking structure of an internally launched aircraft according to claim 6, characterized in that: The elastic retracting component includes a connecting rod, one end of which is connected to the locking hook, the middle part of the connecting rod slides through the through hole, and the other end of the connecting rod is connected to a second elastic component, which can apply elastic force to the connecting rod to retract it toward the inside of the shell.

8. The tail wing locking and unlocking structure of an internally launched aircraft according to claim 7, characterized in that: The second elastic component is a compression spring.

9. The tail wing locking and unlocking structure of an internally launched aircraft according to claim 1, characterized in that: When the locking hook locks the folding section in the folding position, the steering gear is in a set deflection angle state, and when the tail wing is unfolded, the steering gear is reset to a zero position state.

10. An aircraft, characterized in that: include: an aircraft body, the aircraft body comprising an outer shell; The tail wing locking and unlocking structure of the internally launched aircraft as described in any one of claims 1 to 8, wherein the output shaft of the servo rotates through the outer shell and is connected to the tail wing located outside the outer shell.

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