Automatically-unfolded free rotating empennage mechanism on tube launch aircraft

Abstract

The utility model discloses a free rotating empennage mechanism capable of automatically unfolding on a tube launch aircraft, which comprises a rotating section cabin, a first-stage cabin, a second-stage cabin, a first-stage cabin, a second-stage cabin and a first-stage cabin, the rotating section cabin is positioned between a combustion chamber and the first-stage cabin of the aircraft and is fixedly mounted with the combustion chamber and the first-stage cabin through fasteners, and a section of thread is arranged on the outer side of a cylindrical section of the rotating section cabin; the rotating mechanism is connected to the outer side of the cylindrical section of the rotating section cabin body in a sleeving mode, and the rotating mechanism is screwed on the threads on the outer side of the cylindrical section of the rotating section cabin body through fixing nuts. Compared with the prior art, the unmanned aerial vehicle has the advantages that the empennage can be folded and rotated, and after the empennage is unfolded, only the empennage and the root part rotate automatically, so that the inclination stability of the flying of a projectile body can be well ensured, and stable rolling control is realized.

Description

Technical Field

[0001] The utility model relates to the technical field of barrel-launched high-speed aircraft, in particular to a freely rotating tail wing mechanism that automatically unfolds on a tube-launched aircraft. Background Art

[0002] For the barrel-launched aircraft, its overall layout is a canard layout, which has many advantages such as high control efficiency and small hinge moment. However, when the canard deflects for roll control, the canard will generate an asymmetric wash flow field that induces the tail wing to generate a reverse rolling moment, making it impossible for the aircraft to perform good roll control. Currently, it is mostly to make the tail wing rotate freely, so that the generated reverse rolling moment is decoupled from the fuselage, and the rolling moment on the tail wing is not transmitted to the fuselage. However, if the mass of the rotating tail wing part is too large, the decoupling efficiency will also be reduced due to its own large moment of inertia, thus reducing the control efficiency. Moreover, due to the space limitation of the barrel-launch carrier for the barrel-launched aircraft, its rotating tail wing needs to be stored in the launch tube before launch.

[0003] However, the existing patents have the following several disadvantages:

[0004] (1) The existing utility model tail wing mechanism and the rotating section cabin are integrally designed, which increases the mass of the tail wing mechanism, and the reverse rolling moment generated when the tail wing mechanism and the rotating section cabin rotate is transmitted to the aircraft through the rotating section cabin, making it impossible for the aircraft to perform good roll control. Moreover, the existing tail wing mechanism is not convenient to fold and store in the limited storage space inside the launch tube, which is not conducive to the launch of the aircraft. Summary of the Utility Model

[0005] The technical problem to be solved by the utility model is to overcome the above technical defects, and provide a rotatable tail wing that can be folded. After the tail wing unfolds, only the tail wing and the root rotate freely, which can well ensure the tilt stability of the flight of the projectile body and realize the stable roll control of the freely rotating tail wing mechanism that automatically unfolds on the tube-launched aircraft.

[0006] To solve the above problems, the technical solution of the utility model is: a freely rotating tail wing mechanism that automatically unfolds on a tube-launched aircraft, including:

[0007] A rotating section cabin, which is located between the combustion chamber and the first stage cabin of the aircraft and is fixedly installed with the combustion chamber and the first stage cabin through fasteners. A section of thread is provided on the outer side of the cylindrical section of the rotating section cabin;

[0008] A rotating mechanism, which is sleeved on the outer side of the cylindrical section of the rotating section cabin, and the rotating mechanism is tightened on the thread on the outer side of the cylindrical section of the rotating section cabin through a fixing nut.

[0009] Further, the rotating mechanism includes:

[0010] Bearing 1, Bearing 1 is sleeved on the outside of the rotating section cabin body. One end of the rotating section cabin body is provided with a step, and the height of the step is between the inner ring and the outer ring of Bearing 1. The inner ring of Bearing 1 is in contact with the end face of the step;

[0011] Sleeve group, the sleeve group is located on one side of Bearing 1 and is sleeved on the outside of the rotating section cabin body. The sleeve group includes an inner sleeve and an outer sleeve. The inner sleeve and the outer sleeve have the same width and are respectively close to one side of the inner ring and the outer ring of Bearing 1. A sufficient gap is left between the inner sleeve and the outer sleeve;

[0012] Bearing 2, Bearing 2 is located on one side of the sleeve group and is sleeved on the outside of the rotating section cabin body. The inner ring and the outer ring of Bearing 2 are close to one side of the inner sleeve and the outer sleeve of the sleeve group. The outer diameter of the pressing end of the fixing nut is smaller than the inner diameter of the outer ring of Bearing 2, and the pressing end face of the fixing nut does not contact the outer ring of Bearing 2;

[0013] Installation ring, the inner ring of the installation ring is provided with two step surfaces. The first step surface is in contact with the end face of the outer ring of Bearing 1, and the second step surface is evenly distributed with threaded holes. The installation ring fixedly installs the pressing ring on the second step surface of the installation ring through fasteners. The inner diameter of the pressing ring is larger than the outer diameter of the inner ring of Bearing 2 and the pressing ring does not contact the inner ring of Bearing 2;

[0014] Folding wing mechanism, there are six folding wing mechanisms in total and they are evenly distributed inside the installation ring. The folding wing mechanism is fixedly installed with the installation ring through fasteners.

[0015] Further, the folding wing mechanism includes:

[0016] Rudder blade mounting base, the rudder blade mounting base is fixedly installed on the inside of the installation ring through fasteners. A limiting groove is opened inside the rudder blade mounting base, and a shaft is rotatably connected inside the limiting groove;

[0017] Rudder blade, the rudder blade is fixedly connected to the outside of the shaft;

[0018] Double torsion spring, the double torsion spring is sleeved on the outside of the shaft and both ends are fixedly connected to the rudder blade mounting base. The protruding end of the double torsion spring supports the rotation of the rudder blade.

[0019] The advantages of the present utility model compared with the existing technology are as follows:

[0020] (1) The automatically deployed free-rotating tail wing mechanism on the tube-launched aircraft of the present utility model separates the folding wing mechanism from the rotating section cabin through a rotating mechanism, so that when the folding wing mechanism rotates during flight, the rotating section cabin will not rotate, reducing the influence of the reverse rolling moment generated by the folding wing mechanism on the rotating section cabin and the aircraft, enabling the aircraft to better perform rolling control. The folding wing mechanism is convenient for folding and storage, greatly reducing the space it occupies in the launch tube, making the launch tube more conducive to the stable launch of the aircraft. Brief Description of the Drawings

[0021] Figure 1 is a schematic diagram of the position of the rotating tail wing of the automatically deployed free-rotating tail wing mechanism on the tube-launched aircraft of the present utility model.

[0022] Figure 2 is an assembly schematic diagram of the rotating tail wing of the automatically deployed free-rotating tail wing mechanism on the tube-launched aircraft of the present utility model.

[0023] Figure 3 is an enlarged view of A of the automatically deployed free-rotating tail wing mechanism on the tube-launched aircraft of the present utility model.

[0024] Figure 4 is an exploded view of the aircraft rotating mechanism of the automatically deployed free-rotating tail wing mechanism on the tube-launched aircraft of the present utility model.

[0025] Figure 5 is an exploded view of the folding wing mechanism of the automatically deployed free-rotating tail wing mechanism on the tube-launched aircraft of the present utility model.

[0026] Figure 6 is a state diagram of the folding wing before it exits the tube of the automatically deployed free-rotating tail wing mechanism on the tube-launched aircraft of the present utility model.

[0027] Figure 7 is a state diagram of the folding wing after it exits the tube of the automatically deployed free-rotating tail wing mechanism on the tube-launched aircraft of the present utility model.

[0028] As shown in the figure: 1. Combustion chamber; 2. Rotating section cabin; 3. Rotating mechanism; 4. First-stage cabin; 5. Fixed nut; 6. Folding wing mechanism; 7. Bearing one; 8. Outer sleeve; 9. Inner sleeve; 10. Bearing two; 11. Installation ring; 12. Pressure ring; 13. Shaft; 14. Rudder blade; 15. Rudder blade installation base; 16. Double torsion spring. Detailed Embodiment

[0029] Exemplary embodiments will be described in detail herein, and examples thereof are shown in the accompanying drawings. When the following description refers to the accompanying drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present disclosure. On the contrary, they are merely examples of devices consistent with some aspects of the present disclosure as detailed in the appended claims.

[0030] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0031] Embodiment 1:

[0032] As Figures 1 to 7 shown, a freely rotatable tail wing mechanism that automatically unfolds on a tube-launched aircraft includes: a rotating section cabin body 2, the rotating section cabin body 2 is located between the combustion chamber 1 and the first-stage cabin 4 of the aircraft and is fixedly installed with the combustion chamber 1 and the first-stage cabin 4 through fasteners, and a section of thread is provided on the outer side of the cylindrical section of the rotating section cabin body 2; a rotating mechanism 3, the rotating mechanism 3 is sleeved on the outer side of the cylindrical section of the rotating section cabin body 2, and the rotating mechanism 3 is tightened on the thread on the outer side of the cylindrical section of the rotating section cabin body 2 through a fixing nut 5.

[0033] The rotating mechanism 3 includes: a bearing one 7, a sleeve group bearing two 10, a mounting ring 11, and a folding wing mechanism 6. The bearing one 7 is sleeved on the outer side of the rotating section cabin body 2. One end of the rotating section cabin body 2 is provided with a step, and the height of the step is between the inner ring and the outer ring of the bearing one 7. The inner ring of the bearing one 7 is attached to the end face of the step. The sleeve group is located on one side of the bearing one 7 and is sleeved on the outer side of the rotating section cabin body 2. The sleeve group includes an inner sleeve 9 and an outer sleeve 8. The inner sleeve 9 and the outer sleeve 8 have the same width and are respectively close to one side of the inner ring and the outer ring of the bearing one 7. A sufficient gap is left between the inner sleeve 9 and the outer sleeve 8. The bearing two 10 is located on one side of the sleeve group and is sleeved on the outer side of the rotating section cabin body 2. The inner ring and the outer ring of the bearing two 10 are close to one side of the inner sleeve 9 and the outer sleeve 8 of the sleeve group. The outer diameter of the pressing end of the fixing nut 5 is smaller than the inner diameter of the outer ring of the bearing two 10, and the pressing end face of the fixing nut 5 does not contact the outer ring of the bearing two 10. The inner ring of the mounting ring 11 is provided with two step surfaces. The first step surface is attached to the end face of the outer ring of the bearing one 7 and the second step surface is uniformly provided with threaded holes. The mounting ring 11 fixedly installs a pressing ring 12 on the second step surface of the mounting ring 11 through fasteners. The inner diameter of the pressing ring 12 is larger than the outer diameter of the inner ring of the bearing two 10 and the pressing ring 12 does not contact the inner ring of the bearing two 10. There are six folding wing mechanisms 6 in total and they are uniformly distributed inside the mounting ring 11. The folding wing mechanisms 6 are fixedly installed with the mounting ring 11 through fasteners.

[0034] Since the outer diameter of the clamping end of the fixing nut 5 is smaller than the inner diameter of the outer ring of the bearing 2 10 and the clamping end face of the fixing nut 5 does not contact the outer ring of the bearing 2 10, during installation, the fixing nut 5 is rotated and the fixing nut 5 moves through the thread on the outside of the cylindrical section of the rotating section cabin 2, so that the fixing nut 5 clamps and fixes the inner ring of the bearing 1 7, the inner sleeve 9 and the inner ring of the bearing 2 10 of the rotating mechanism 3 through the clamping end face and the step end face set at one end of the rotating section cabin 2, thereby completing the internal clamping installation of the rotating mechanism 3.

[0035] Afterwards, the outer ring of bearing 17 is fixed to the first step end face of the mounting ring 11 by fasteners, and the pressure ring 12 is fixed to the second step end face of the mounting ring 11 by fasteners, so that the outer ring of bearing 17, the outer sleeve 8 and the outer ring of bearing 2 10 are clamped and fixed, completing the external clamping installation of the rotating mechanism 3. At this time, the mounting ring 11 is turned, and the mounting ring 11 can drive the outer ring of bearing 17, the outer sleeve 8 and the outer ring of bearing 2 10 to rotate outside the inner ring of bearing 17, the inner sleeve 9 and the inner ring of bearing 2 10.

[0036] The folding wing mechanism 6 includes: a rudder blade mounting base 15, a rudder blade 14 and a double torsion spring 16. The rudder blade mounting base 15 is fixedly mounted on the inner side of the mounting ring 11 by fasteners. A limiting groove is provided on the inner side of the rudder blade mounting base 15. The inner side of the limiting groove is rotatably connected to the shaft 13. The rudder blade 14 is fixedly connected to the outer side of the shaft 13. The double torsion spring 16 is sleeved on the outer side of the shaft 13 and fixedly connected to the rudder blade mounting base 15 at both ends. The protruding end of the double torsion spring 16 supports the rotation of the rudder blade 14.

[0037] The folding wing mechanism 6 is fixedly installed on the inner side of the mounting ring 11 by fasteners. Before the projectile is launched, the rudder blades 14 are evenly distributed in the storage grooves provided on the outer side of the rotating section cabin 2, and are limited to a folded state by the launch tube wall. When the aircraft leaves the launch tube, the folding tail wing is popped open by the double torsion spring 16. During the flight, the rudder blades 14 are kept in the unfolded state by the spring force and flight resistance, and the rudder blades 14 drive the mounting ring 11 fixed together, so that the mounting ring 11 drives the outer ring of bearing 1 7, the outer sleeve 8 and the outer ring of bearing 2 10 to rotate outside the inner ring of bearing 1 7, the inner sleeve 9 and the inner ring of bearing 2 10, thereby releasing the rolling moment generated by the flight of the projectile.

[0038] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An automatically deployed free-rotating tail fin mechanism on a tube-launched aircraft, characterized in that Comprising: A rotating section cabin body (2), which is located between the combustion chamber (1) and the first-stage cabin (4) of the aircraft and is fixedly installed with the combustion chamber (1) and the first-stage cabin (4) through fasteners. A section of thread is provided on the outer side of the cylindrical section of the rotating section cabin body (2). A rotating mechanism (3), which is sleeved on the outer side of the cylindrical section of the rotating section cabin body (2), and the rotating mechanism (3) is screwed tightly on the thread on the outer side of the cylindrical section of the rotating section cabin body (2) through a fixing nut (5).

2. The automatically deployed freely rotatable tail fin mechanism on a tube-launched flying vehicle according to claim 1, wherein: The rotating mechanism (3) includes: A first bearing (7), which is sleeved on the outer side of the rotating section cabin body (2). One end of the rotating section cabin body (2) is provided with a step, the height of the step is between the inner ring and the outer ring of the first bearing (7), and the inner ring of the first bearing (7) is attached to the end face of the step. A sleeve group, which is located on one side of the first bearing (7) and is sleeved on the outer side of the rotating section cabin body (2). The sleeve group includes an inner sleeve (9) and an outer sleeve (8). The widths of the inner sleeve (9) and the outer sleeve (8) are the same and are respectively close to one side of the inner ring and the outer ring of the first bearing (7). A sufficient gap is left between the inner sleeve (9) and the outer sleeve (8). A second bearing (10), which is located on one side of the sleeve group and is sleeved on the outer side of the rotating section cabin body (2). The inner ring and the outer ring of the second bearing (10) are close to one side of the inner sleeve (9) and the outer sleeve (8) of the sleeve group. The outer diameter of the pressing end of the fixing nut (5) is smaller than the inner diameter of the outer ring of the second bearing (10), and the pressing end face of the fixing nut (5) does not contact the outer ring of the second bearing (10). An installation ring (11), the inner ring of which is provided with two step faces. The first step face is attached to the end face of the outer ring of the first bearing (7), and the second step face is evenly distributed with threaded holes. The installation ring (11) fixedly installs a pressing ring (12) on the second step face of the installation ring (11) through fasteners. The inner diameter of the pressing ring (12) is larger than the outer diameter of the inner ring of the second bearing (10), and the pressing ring (12) does not contact the inner ring of the second bearing (10). A folding wing mechanism (6), there are six folding wing mechanisms (6) in total and they are evenly distributed inside the installation ring (11). The folding wing mechanism (6) is fixedly installed with the installation ring (11) through fasteners.

3. The automatically deployed freely rotatable tail fin mechanism on a tube-launched flying vehicle according to claim 2, characterized in that: The folding wing mechanism (6) includes: A rudder blade installation base (15), which is fixedly installed on the inner side of the installation ring (11) through fasteners. A limiting groove is provided on the inner side of the rudder blade installation base (15), and a shaft (13) is rotatably connected inside the limiting groove. A rudder blade (14), which is fixedly connected to the outer side of the shaft (13). A double torsion spring (16), which is sleeved on the outer side of the shaft (13) and both ends are fixedly connected to the rudder blade installation base (15). The protruding ends of the double torsion spring (16) support the rotation of the rudder blade (14).

Images