Control surface separation device applied to cross-medium aircraft

Abstract

A control surface separation device applied to a cross-medium aircraft is applied to the field of cross-medium aircrafts, and before the aircraft enters water, a tail air rudder needs to be separated to reduce the resistance of the aircraft; comprising a control surface, a servo cabin, a pin puller, a locking pin, a driving shaft, an inner bearing, an outer bearing, a bearing gland, a locking nut, a disc spring assembly, a sealing sleeve, a guide rod, a retainer, a retainer base, a bearing sleeve and a sealing assembly. The servo cabin serves as a basic carrier of the whole device, and all parts are installed on the servo cabin. The pin puller is an initiating explosive device and forms an unlocking device together with the locking pin; the driving shaft, the inner bearing, the outer bearing and the locking nut form a driving shaft system to provide torque for the rotation of the control surface; the disc spring assembly, the sealing sleeve, the guide rod, the retainer and the base form a separating device; the sealing assembly can reduce friction force of interfaces of adjacent parts while guaranteeing sealing, the sealing assembly and the sealing sleeve jointly form a sealing system, and the sealing performance of the separating device is guaranteed.

Description

Technical Field

[0001] This application belongs to the field of deformable control surfaces of aircraft, and more specifically, relates to a control surface separation device for a trans-medium aircraft, which is used to reduce the resistance of the aircraft after entering the water. Background Art

[0002] The control surface is a main component in aircraft design and is used to control the attitude of the aircraft. In an amphibious trans-medium aircraft, the requirements for stability and lift-to-drag ratio are different in different flight stages, and the requirements for the aircraft's external shape are also different. A fixed-shape aircraft is difficult to be suitable for different flight missions. Deformable wing surfaces and control surfaces can change the shape of the wing surfaces and control surfaces to achieve changes in the external shape, so as to adapt to different flight environments.

[0003] Conventional deformable control surfaces cannot adjust the control surface in real time according to the actual flight environment and flight attitude. Utility Model Content

[0004] The technical problem solved by this application is: overcoming the deficiencies of the prior art, providing a control surface separation device applied to a trans-medium aircraft, which can change different flight missions as needed, change the external shape of the aircraft, and play a role in reducing the resistance of the aircraft. It solves the problem in the prior art of changing the shape of the control surface in real time for a deformable aircraft under different flight missions and adjusting the lift-to-drag ratio of the aircraft.

[0005] The technical solution provided by this application is as follows:

[0006] A control surface separation device applied to a trans-medium aircraft includes a control surface, a servo cabin, an unlocking device, a drive shaft system, and a separation device;

[0007] The servo cabin is connected with a servo cabin bearing seat, the servo cabin bearing seat is provided with a separation hole, the cylindrical section of the control surface is located in the separation hole, and a sector-shaped groove is arranged on the side surface of the cylindrical section;

[0008] The unlocking device includes a pin puller and a locking pin. The pin puller is an explosive device, the pin puller is installed on the servo cabin, the locking pin is connected with the pin puller, and the locking pin passes through the locking pin hole on the servo cabin. The pin puller is used to drive the locking pin to move axially along the axis of the locking pin hole; the end of the locking pin is inserted into the sector-shaped groove of the cylindrical section;

[0009] The drive shaft system is used to drive the cylindrical section to rotate, and the cylindrical section drives the control surface to rotate. At this time, the locking pin slides in the sector-shaped groove, and the sector-shaped groove is filled with a solid lubricant to reduce the friction force;

[0010] When the pin puller drives the locking pin to disengage from the sector-shaped groove, the cylindrical section moves along the axis of the separation hole under the drive of the separation device and disengages from the servo cabin.

[0011] The drive shaft system includes a drive shaft. The drive shaft is located within the separation hole and is rotatably connected to the servo cabin. The drive shaft is provided with an inner hole, and the end of the drive shaft near the rudder surface is provided with a square groove. The cylindrical section is inserted into the inner hole of the drive shaft. The end of the cylindrical section near the rudder surface is a square head, and the square head is inserted into the square groove.

[0012] The drive shaft is provided with a drive assembly for driving itself to rotate.

[0013] The drive assembly includes a rocker arm and a linear servo. The drive shaft is provided with a rocker arm mounting hole for mounting the rocker arm. The rocker arm is connected to the linear servo, and the linear servo drives the drive shaft to rotate through the rocker arm.

[0014] The drive shaft system further includes an inner bearing, an outer bearing, and a locking nut. The servo cabin bearing seat is sequentially provided with a first inner hole and a second inner hole at the end of the separation hole away from the rudder surface. The diameters of the separation hole, the first inner hole, and the second inner hole increase in sequence. The inner bearing is installed in the first inner hole, the bearing sleeve is installed in the second inner hole, the outer bearing is installed in the inner hole of the bearing sleeve, the inner diameter of the bearing sleeve is smaller than the aperture of the first inner hole, and the outer diameter of the bearing sleeve is matched with the second inner hole.

[0015] The drive shaft passes through the two bearings. One end of the drive shaft near the rudder surface is provided with an end face flange, and the outer diameter of the end face flange is larger than the diameter of the separation hole. The other end of the drive shaft away from the rudder surface is provided with an external thread to form a threaded section. The locking nut is tightened on the threaded section. The locking nut presses the inner ring of the outer bearing. The bearing gland is installed at the end of the servo cabin bearing seat away from the rudder surface, and the bearing gland presses the outer ring of the outer bearing to fix the two bearings in the bearing seat and simultaneously fix the drive shaft.

[0016] A sealing groove is provided on the side of the end face flange facing away from the rudder surface for installing a sealing assembly.

[0017] The sealing assembly includes a graphite washer and a rubber washer. The rubber washer is sleeved outside the graphite washer, and the rubber washer ensures a compression amount of 1.5 mm. The rubber washer ensures the seal between the drive shaft and the servo cabin by its own elasticity. The graphite washer reduces the friction force when the drive shaft and the servo cabin rotate relative to each other.

[0018] The separation device includes a disc spring assembly, a sealing sleeve, a guide rod, a cage and a cage base. One end of the sealing sleeve is located inside the drive shaft, and the other end is open and provided with an end flange. The disc spring assembly consists of multiple disc springs placed face to face, and the disc spring assembly is placed in the inner hole of the sealing sleeve. The guide rod is installed in the inner hole of the sealing sleeve, and there is a 0.5mm gap between the outer cylindrical surface of the guide rod and the inner hole of the sealing sleeve. The guide rod includes an upper end face and a guide cylindrical section. The upper end face is connected to one end of the guide cylindrical section, and the upper end face abuts against the disc spring assembly. The guide cylindrical section is inserted into the inner hole of the cage, and the two are in clearance fit. The cage is tightened on the cage base through a threaded section, and the cage base is installed on the servo cabin through screws.

[0019] The outer cylindrical surface of the sealing sleeve fits with the inner hole of the drive shaft and is filled with grease to achieve a partial sealing effect. When the function of the disc spring assembly ends, there is still a restoring force to press the end flange of the sealing sleeve against the lower end face of the drive shaft to achieve end face sealing.

[0020] When separating through the unlocking device, the pull pin actuator acts, driving the locking pin to move out of the sector groove of the cylindrical section. Under the action of the restoring force of the disc spring assembly, the disc spring assembly pushes the rudder surface to eject, completing the separation of the rudder surface and the servo cabin.

[0021] In summary, the present application at least includes the following beneficial technical effects:

[0022] Aiming at the deformable aircraft to change the shape of the rudder surface in real time under different flight missions and adjust the lift-drag ratio of the aircraft.

[0023] It not only ensures the normal movement of the rudder surface but also ensures reliable separation. The separation device is designed with the disc spring assembly as the power source to ensure the reliability of the product. The remaining restoring force is used to strengthen the sealing system. The locking device is designed based on pyrotechnics to improve the reliability of unlocking. Description of the Drawings

[0024] Figure 1 Shows a full cross-sectional view of a rudder surface separation device.

[0025] Figure 2 Shows the rudder surface structure diagram.

[0026] Figure 3 Shows the servo cabin structure diagram.

[0027] Figure 4 Shows the drive shaft structure diagram.

[0028] Figure 5 Shows the guide rod structure diagram.

[0029] Figure 6 Shows the sealing component structure diagram.

[0030] Description of the attached reference numerals:

[0031] 1. Control surface; 2. Servo cabin; 3. Pin puller; 4. Locking pin; 5. Drive shaft; 6. Inner bearing; 7. Outer bearing; 8. Bearing gland; 9. Locking nut; 10. Disc spring assembly; 11. Sealing sleeve; 12. Guide rod; 13. Cage; 14. Cage base; 15. Bearing sleeve; 16. Sealing assembly; 101. Cylindrical section; 102. Sector groove; 21. First inner hole; 22. Second inner hole; 51. Threaded section; 52. End face flange; 53. Sealing groove; 54. Rocker arm mounting hole; 55. Square groove; 121. Upper end face; 122. Guide cylindrical section; 161. Graphite washer; 162. Rubber washer. Detailed implementation manners

[0032] To make the objectives, technical solutions and advantages of the present utility model clearer, the following will further describe in detail the disclosed implementation manners of the present utility model with reference to the accompanying drawings.

[0033] The embodiment of the present application discloses a control surface separation device applied to a cross-media aircraft, which is applied to the field of cross-media aircraft, such as Figure 1 shown, and includes: a control surface 1, a servo cabin 2, a pin puller 3, a locking pin 4, a drive shaft 5, an inner bearing 6, an outer bearing 7, a bearing gland 8, a locking nut 9, a disc spring assembly 10, a sealing sleeve 11, a guide rod 12, a cage 13, a cage base 14, a bearing sleeve 15 and a sealing assembly 16.

[0034] As Figure 3 shown, the servo cabin 2 serves as the basic carrier of the entire device, and all components are installed on the servo cabin 2. The servo cabin also serves as a cabin section of the aircraft, and the attitude of the aircraft is controlled through the control surface 1. The servo cabin adopts a modular design and can be replaced quickly as a whole.

[0035] As Figure 1 and Figure 2 shown, the pin puller 3 is an explosive device and jointly forms an unlocking device with the locking pin 4. The pin puller 3 is installed on the servo cabin 2 using screws, and the locking pin 4 is tightened on the threaded joint of the pin puller 3; the locking pin 4 passes through the locking pin hole on the servo cabin 2 and can move axially along the hole axis; the end of the locking pin 4 is inserted into the sector groove 102 of the cylindrical section 101 of the control surface 1. When the control surface rotates, the locking pin 4 slides in the sector groove 12, and the groove is filled with a solid lubricant to reduce the friction between the control surface 1 and the locking pin 4. The unlocking process is as follows: after receiving the separation instruction, the pin puller 3 actuates, driving the locking pin 4 to be withdrawn from the sector groove 102 of the cylindrical section 101 of the control surface 1, completing the unlocking of the control surface 1.

[0036] As Figure 1 、 Figure 3 and Figure 4As shown in the figure, the drive shaft 5, inner bearing 6, outer bearing 7, and lock nut 8 form a drive shaft system to provide torque for the rotation of the control surface. The bearing seat of the servo compartment is successively provided with a first inner hole 21 and a second inner hole 22 at the end of the separation hole away from the control surface 1. The diameters of the separation hole, the first inner hole 21, and the second inner hole 22 increase in sequence. The inner bearing 6 is installed in the first inner hole 21 of the bearing seat of the servo compartment 2. To ensure smooth installation, the bearing sleeve 15 is first installed in the second inner hole 22 of the bearing seat of the servo compartment 2, and the outer bearing 7 is installed in the inner hole of the bearing sleeve 15. The inner diameter of the bearing sleeve 15 is smaller than the aperture of the first inner hole 21, and the outer diameter of the bearing sleeve 15 is matched with the second inner hole 22. Through the above settings, it is beneficial to reduce the clearance. The lock nut 9 presses the inner ring of the outer bearing 7, and the bearing gland 8 is connected to the bearing seat of the servo compartment 2 by bolts, and the bearing gland 8 presses the outer ring of the outer bearing 7 to fix the two bearings in the bearing seat. The drive shaft 5 passes through the two bearings. One end of the drive shaft 5 away from the control surface 1 is provided with an external thread to form a threaded section 51. The lock nut 9 is tightened on the threaded section 51 to complete the fixation of the drive shaft 5. At the same time, the lock nut 9 presses the inner ring of the bearing. A sealing groove 53 is provided on the end face flange 52 of the drive shaft 5 to install the sealing component 16.

[0037] As Figure 1 and Figure 4 shown in the figure, a rocker arm mounting hole 54 is provided on the drive shaft 5 to install the rocker arm. A square groove 55 is provided on the end face flange 52 of the drive shaft 5. The cylindrical section 11 of the control surface 1 is inserted into the inner hole of the drive shaft 5, and the square head 12 of the control surface 1 is inserted into the square groove 55. Torque is transmitted by relying on the square groove 55 and the square head 12. The rocker arm is connected to the linear servo. The linear servo pushes the drive shaft 5 to rotate through the rocker arm to provide power for the rotation of the control surface. The rotation of the drive shaft 5 can be controlled in real time according to the received control signal, so as to realize the real-time adjustment of the control surface according to the actual flight environment and flight attitude.

[0038] As shown in the attached Figure 1 and attached Figure 5 figure, the disc spring assembly 10, sealing sleeve 11, guide rod 12, cage 13, and cage base 14 constitute a separation device.

[0039] As Figure 5 shown in the figure, the outer cylindrical surface of the sealing sleeve 11 is matched with the inner hole of the drive shaft 5. The disc spring assembly 10 is composed of 28 disc springs placed face to face. The disc spring assembly 10 is placed in the inner hole of the sealing sleeve 11, and the disc spring assembly 10 is in a compressed state. The guide rod 12 is installed in the inner hole of the sealing sleeve 11. A clearance of 0.5 mm is maintained between the outer cylindrical surface of the guide rod 12 and the inner hole of the sealing sleeve 11. The upper end face 121 of the guide rod 12 abuts against the disc spring assembly, and the guide cylindrical section 122 is inserted into the inner hole of the cage 13, and the two are in clearance fit. The cage 13 is tightened on the cage base 14 through a threaded section, and the cage base 14 is installed on the servo compartment 2 by screws.

[0040] As shown in the appendix Figure 6 As shown, the sealing assembly 16 includes a graphite gasket 161 and a rubber gasket 162. The rubber gasket 162 is sleeved outside the graphite gasket 161. The sealing assembly 16 is installed in a sealing groove 53 provided on the end face flange 52 of the drive shaft 5. Among them, the rubber gasket 162 ensures a compression amount of 1.5 mm; the rubber gasket 162 relies on its own elasticity to ensure the seal between the drive shaft 5 and the servo cabin 2; the graphite gasket 161 can reduce the friction force when the drive shaft 5 and the servo cabin 2 rotate relative to each other.

[0041] A rudder surface separation device applied to a cross-media aircraft, whose functions include: during the flight of the aircraft in the air, the rudder surface 1 serves as a control surface to control the attitude of the aircraft; before entering the water, the rudder surface 1 separates from the aircraft to reduce the resistance of the aircraft during navigation in the water; when the aircraft is navigating in the water, the separation part (the installation position on the separation cabin 2 that cooperates with the cylindrical section 101 of the rudder surface 1) needs to ensure sealing.

[0042] A rudder surface separation device applied to a cross-media aircraft has the following operating principle:

[0043] During the flight of the aircraft in the air, the linear actuator installed on the servo cabin drives the drive shaft to rotate through a rocker arm. The drive shaft in the axially locked state transmits torque to the rudder surface through the cooperation of the square groove and the square head. At this time, the disc spring assembly abuts against the end 11 of the cylindrical section of the rudder surface 1, and the disc spring assembly is in a compressed state. The sealing sleeve is tightly pressed against the lower bottom surface of the cylindrical section of the rudder surface. A solid lubricant coating is applied on the contact surface to prevent the rudder surface from rotating and driving the sealing sleeve to rotate.

[0044] During the separation process before the aircraft enters the water, after the flight control computer sends a separation instruction, the ignition and detonating assembly ignites the actuator, and the actuator acts backward (i.e., the pull pin 3 acts), pulling out the locking pin 4 from the fan-shaped groove of the rudder surface to complete the unlocking action; after the rudder surface is unlocked, it loses restraint along the axis of the drive shaft. Under the action of the restoring force of the disc spring assembly, the sealing sleeve pushes the rudder surface to move upward along the inner hole of the drive shaft, ejecting the rudder surface from the servo cabin of the aircraft. After the ejection action is completed, the flange of the sealing sleeve is tightly pressed against the lower end surface of the drive shaft. At this time, the disc spring assembly is still in a compressed state. Under the action of the remaining restoring force, the lower flange of the sealing sleeve and the lower end surface of the drive shaft are completely pressed together. At the same time, the outer cylindrical surface of the sealing sleeve and the inner hole of the drive shaft are in a mating state and lubricating grease is applied. The combined action of the two can effectively ensure the seal of the servo cabin under the action of water pressure.

[0045] The content not described in detail in the specification of this application belongs to the well-known technology of those skilled in the art.

[0046] The present application has been described in detail above in conjunction with specific embodiments and exemplary examples. However, these descriptions should not be construed as limiting the present application. Those skilled in the art understand that without departing from the spirit and scope of the present application, various equivalent substitutions, modifications, or improvements can be made to the technical solutions and their implementation manners of the present application, and all of these fall within the scope of the present application. The protection scope of the present application shall be subject to the appended claims.

Claims

1. A rudder surface separation device applied to a cross-medium aircraft, characterized in that: It includes a control surface (1), a servo cabin (2), an unlocking device, a drive shaft system, and a separation device; The servo cabin (2) is connected with a servo cabin bearing seat which is provided with a separation hole. The cylindrical section (101) of the control surface (1) is located in the separation hole, and a sector-shaped groove (102) is arranged on the side surface of the cylindrical section (101); The unlocking device includes a pin puller (3) and a locking pin (4). The pin puller (3) is installed on the servo cabin (2), the locking pin (4) is connected with the pin puller (3), and the locking pin (4) passes through a locking pin hole on the servo cabin (2). The pin puller (3) is used to drive the locking pin (4) to move axially along the axis of the locking pin hole; the end of the locking pin (4) is inserted into the sector-shaped groove (102) of the cylindrical section (101); The drive shaft system is used to drive the cylindrical section (101) to rotate, and the cylindrical section (101) drives the control surface (1) to rotate. At this time, the locking pin (4) slides in the sector-shaped groove (102); The drive shaft system includes a drive shaft (5). The drive shaft (5) is located in the separation hole and is rotationally connected with the servo cabin (2). The drive shaft (5) is provided with an inner hole. The end of the drive shaft (5) close to the control surface (1) is provided with a square groove (55). The cylindrical section (101) is inserted into the inner hole of the drive shaft (5). The end of the cylindrical section (101) close to the control surface (1) is a square head which is inserted into the square groove (55); the drive shaft (5) is provided with a drive component for driving itself to rotate; When the pin puller (3) drives the locking pin (4) to disengage from the sector-shaped groove (102), the cylindrical section (101) moves along the axis of the separation hole to disengage from the servo cabin (2) under the drive of the separation device.

2. The rudder surface separation device for a cross-media aircraft according to claim 1, wherein: The drive component includes a rocker arm and a linear servo. A rocker arm mounting hole (54) is arranged on the drive shaft (5), and the rocker arm mounting hole (54) is used to mount the rocker arm. The rocker arm is connected with the linear servo, and the linear servo pushes the drive shaft (5) to rotate through the rocker arm.

3. The rudder surface separation device for a cross-media aircraft according to claim 1, wherein: The drive shaft system further includes a bearing and a locking nut (9). The bearing is located between the inner hole inner walls of the drive shaft (5) and the servo cabin bearing seat. One end of the drive shaft (5) close to the control surface (1) is provided with an end face flange (52), and the outer diameter of the end face flange (52) is larger than the diameter of the separation hole; the end of the drive shaft (5) far from the control surface (1) is provided with an external thread to form a threaded section (51), and the locking nut (9) is screwed tightly on the threaded section (51). The locking nut (9) presses the inner ring of the bearing, and a bearing cover (8) is installed at the end of the servo cabin bearing seat far from the control surface (1), and the bearing cover (8) presses the outer ring of the bearing to fix the bearing in the servo cabin bearing seat and fix the drive shaft (5) at the same time.

4. The rudder surface separation device for a cross-media aircraft according to claim 3, characterized in that: The bearing includes an inner bearing (6) and an outer bearing (7). At the end of the separation hole away from the rudder surface (1), the servo cabin bearing seat is successively provided with a first inner hole (21) and a second inner hole (22). The diameters of the separation hole, the first inner hole (21), and the second inner hole (22) increase in sequence. The inner bearing (6) is installed in the first inner hole (21), the bearing sleeve (15) is installed in the second inner hole (22), the outer bearing (7) is installed in the inner hole of the bearing sleeve (15). The inner diameter of the bearing sleeve (15) is smaller than the aperture of the first inner hole (21), and the outer diameter of the bearing sleeve (15) is matched with the second inner hole (22).

5. The rudder surface separation device for a cross-media aircraft according to claim 3, characterized in that: On the side of the end face flange (52) facing away from the rudder surface (1), a sealing groove (53) is provided, and the sealing groove (53) is used to install the sealing component (16).

6. The rudder surface separation device for a cross-media aircraft according to claim 5, wherein: The sealing component (16) includes a graphite washer (161) and a rubber washer (162). The rubber washer (162) is sleeved outside the graphite washer (161), and the rubber washer (162) ensures a compression amount of 1.5 mm; the rubber washer (162) relies on its own elasticity to ensure the seal between the drive shaft (5) and the servo cabin (2); the graphite washer (161) reduces the friction force when the drive shaft (5) and the servo cabin (2) rotate relatively.

7. The rudder surface separation device for a cross-medium aircraft according to claim 2, characterized in that: The separation device includes a disc spring assembly (10), a sealing sleeve (11), a guide rod (12), a cage (13), and a cage base (14). One end of the sealing sleeve (11) is located inside the drive shaft (5), the other end is open and provided with an end face flange, and the outer diameter of the end face flange is larger than the inner diameter of the drive shaft (5); the disc spring assembly (10) is composed of multiple disc springs placed face to face, and the disc spring assembly (10) is placed in the inner hole of the sealing sleeve (11); the guide rod (12) is installed in the inner hole of the sealing sleeve (11), and there is a 0.5 mm gap between the outer cylindrical surface of the guide rod (12) and the inner hole of the sealing sleeve (11); the guide rod (12) includes an upper end face (121) and a guide cylindrical section (122), the upper end face (121) is connected to one end of the guide cylindrical section (122), the upper end face (121) abuts against the disc spring assembly, and the guide cylindrical section (122) is inserted into the inner hole of the cage (13), and the two are in clearance fit; the cage (13) is tightened on the cage base (14) through a threaded section, and the cage base is installed on the servo cabin (2) by screws.

8. The rudder surface separation device for a cross-media aircraft according to claim 7, characterized in that: The outer cylindrical surface of the sealing sleeve (11) is matched with the inner hole of the drive shaft (5) and filled with grease to play a role in local sealing; When the end face flange contacts the end of the drive shaft (5), the action of the disc spring assembly (10) ends; when the action of the disc spring assembly (10) ends, there is still a restoring force to press the end face flange of the sealing sleeve (11) against the lower end face of the drive shaft (5) to achieve end face sealing.

9. The rudder surface separation device for a cross-medium aircraft according to claim 1, wherein, Including: When separated by the unlocking device, the puller (3) acts, driving the locking pin (4) to move out of the fan-shaped groove (102) of the cylindrical section (101). Under the action of the restoring force of the disc spring assembly (10), the disc spring assembly (10) pushes the rudder surface (1) to eject, completing the separation of the rudder surface and the servo cabin (2).

Images