Wing folding mechanism of patrol aircraft
By designing a cruiser wing folding mechanism including dual torsion springs and locking components, the problem of difficult to ensure wing expansion synchronization in the prior art is solved, and the synchronization and locking of wing expansion are achieved, thereby improving the improvement of wing expansion. Flight stability and storage convenience.
Patent Information
- Application Number
- CN202323608672.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2023-12-28
- Publication Date
- 2025-02-07
- Estimated Expiration
- 2033-12-28
AI Technical Summary
The synchronization of the existing cruiser wing folding mechanism is difficult to ensure when deployed, which affects flight performance.
A wing folding mechanism including a shaft cover, a small shaft sleeve, a right front wing, a double torsion spring, a large shaft sleeve, a left front wing, a wing rotation shaft, a locking shaft and a locking assembly are designed, through a double torsion The cooperation of the spring and locking assembly ensures synchronization and locking when the wing is deployed.
The synchronous and coaxial wing spread is achieved, flight stability and reliability are ensured, and convenience is provided during storage and transportation.
Smart Images
Figure CN222432577U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of aircraft, and in particular relates to a wing folding mechanism for a patrol aircraft. Background Art
[0002] The wing is an important component that provides lift for the patrol vehicle. It is generally designed to be long and takes up a large space when unfolded. According to the current new requirements for combat capabilities such as "high maneuverability, high camouflage, and high time sensitivity", wings that are long and occupy a lot of space are not advantageous. Therefore, it is very necessary to design the wings to be folded for transportation and only unfolded during flight.
[0003] The existing wing folding mechanism of patrol aircraft has a very difficult time ensuring the synchronization of the unfolding. Whether the wings unfold synchronously has a very large impact on the flight performance of the aircraft. Therefore, it is very promising to develop a device that can ensure the synchronization of the wings when unfolding. Utility Model Content
[0004] The utility model aims to solve the problems of the prior art and provides a wing folding mechanism for a patrol aircraft.
[0005] In order to solve the technical problem, the technical solution of the utility model is: a wing folding mechanism of a patrol aircraft, including a shaft cover, a small shaft sleeve, a right front wing, a double torsion spring, a large shaft sleeve, a left front wing, a wing shaft, a locking shaft and a locking assembly, wherein the small shaft sleeve is sleeved in the connecting hole groove of the right front wing, the large shaft sleeve is sleeved in the connecting hole groove of the left front wing, the left front wing, the double torsion spring and the right front wing are sleeved on the wing shaft in sequence, the end of the wing shaft is fixedly connected to the shaft cover, and the double torsion spring is sleeved in the connecting hole groove of the left front wing. The torsion spring is located in the connecting hole groove where the right front wing and the left front wing are connected, one end of the double torsion spring is clamped in the first limiting hole of the right front wing, and the other end of the double torsion spring is clamped in the second limiting hole of the left front wing. When the double torsion spring is not subjected to torsion, the right front wing and the left front wing are in a straight line, and the locking assembly and the wing shaft are fixedly connected to the fuselage by screws respectively. The locking assembly is located on the front side of the right front wing and the left front wing, and the locking assembly locks the right front wing and the left front wing in a straight line.
[0006] Preferably, the locking assembly includes a locking shaft, a limit block cover, a second hexagon socket head screw, a limit spring and a limit frame. The limit block cover is fixedly installed in the limit frame by the second hexagon socket head screw. One end of the locking shaft is fitted with a limit spring and installed on the limit block cover. The other end of the locking shaft passes through the limit frame and is then inserted into the keyholes of the right front wing and the left front wing. A long hole is provided on the side of the limit frame, and the position of the long hole corresponds to the pressing hole of the locking shaft.
[0007] Preferably, the locking shaft is an "I"-shaped structure, a pressing hole is provided at the center position of the "I"-shaped structure, two through holes are respectively provided on the limit block cover and the limit frame, a limit spring is installed on one side of the locking shaft and passes through the two through holes of the limit block cover, and the other side of the locking shaft passes through the two through holes on the limit frame for locking the right front wing and the left front wing.
[0008] Preferably, a first limiting hole is provided on the end surface of the right front wing close to the double torsion spring, and a second limiting hole is provided on the end surface of the left front wing close to the double torsion spring. One end of the double torsion spring is clamped in the first limiting hole of the right front wing, and the other end of the double torsion spring is clamped in the second limiting hole of the left front wing. The torsion at both ends of the double torsion spring is the same, and the angle between the two ends of the double torsion spring and the center of the double torsion spring is 30°. The angle between the first limiting hole and the second limiting hole and the center of the double torsion spring is also 30°, so that when the double torsion spring is not subjected to torsion, the right front wing and the left front wing are in a straight line.
[0009] Preferably, a first sliding track is provided on the side of the right front wing close to the locking assembly, and a second sliding track is provided on the side of the left front wing close to the locking assembly, the angles between the two ends of the first sliding track and the center line of the connecting hole groove of the right front wing are both 90°, the angles between the two ends of the second sliding track and the center line of the connecting hole groove of the left front wing are both 90°, a first wing root lockhole is provided on the rightmost side of the first sliding track, and a second wing root lockhole is provided on the leftmost side of the second sliding track, when the right front wing and the left front wing are in a straight line, the second wing root lockhole is directly below the first wing root lockhole, and the locking shaft passes through the limit frame and is inserted into the first wing root lockhole and the second wing root lockhole to lock it.
[0010] Preferably, a gasket is provided on one end surface where the right front wing and the left front wing are connected, so as to reduce the sliding friction between the right front wing and the left front wing.
[0011] Preferably, the shaft cover and the end of the wing shaft are fixedly connected by a first hexagon socket head screw.
[0012] Preferably, the small shaft sleeve is sleeved in the connection hole slot of the right front wing and fixed by screws, and the large shaft sleeve is sleeved in the connection hole slot of the left front wing and fixed by screws.
[0013] Compared with the prior art, the advantages of the utility model are:
[0014] (1) The utility model discloses a wing folding mechanism for a patrol aircraft, comprising a right front wing, a double torsion spring, a left front wing and a wing shaft, wherein two ends of the double torsion spring are respectively connected to the right front wing and the left front wing, and the right front wing, the double torsion spring and the left front wing are mounted on the wing shaft. When the double torsion spring is not subjected to torsion, the right front wing and the left front wing are in a straight line. The folding mechanism of the present invention can make both wings of the patrol aircraft fold toward the fuselage, and the folding process is simple and smooth. After folding, the wings fit perfectly with the fuselage, and the appearance of the whole aircraft is smooth and beautiful. At the same time, when the wings of the patrol aircraft are unfolded, due to the connection relationship between the double torsion spring and the right front wing and the left front wing, the double torsion spring rebounds to a state where there is no torsion, so that the right front wing and the left front wing are in a straight line, thereby ensuring the synchronization and coaxiality of the wing unfolding.
[0015] (2) The folding mechanism of the utility model also includes a locking assembly. The locking assembly and the wing shaft are fixed to the fuselage by screws. The locking shaft limit of the locking assembly is located in the sliding track of the right front wing and the left front wing. When the wings of the patrol aircraft are unfolded, the right front wing and the left front wing are in a straight line. At this time, the locking shaft is stuck in the keyhole, so that the right front wing and the left front wing are locked, ensuring the timeliness of locking after the wings are unfolded. The mechanism can ensure the flight stability and reliability of the patrol aircraft and meet the convenience of the patrol aircraft during storage and transportation;
[0016] (3) The folding mechanism of the utility model has a high degree of integration, a simple structure, and is easy to install; the locking mechanism automatically locks when unfolded, and no manual operation is required. The folding action is simple and easy to operate. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 , a disassembled exploded view of a wing folding mechanism of a patrol aircraft of the utility model;
[0018] Figure 2 , a schematic assembly diagram of a patrol aircraft wing folding mechanism of the utility model.
[0019] Description of reference numerals:
[0020] 1. First hexagon socket head screw, 2. Shaft cover, 3. Small sleeve, 4. Right front wing, 5. Washer, 6. Double torsion spring, 7. Large sleeve, 8. Left front wing, 9. Wing shaft, 10. Locking shaft, 11. Limit block cover, 12. Second hexagon socket head screw, 13. Limit spring, 14. Limit frame;
[0021] 4-1, first limiting hole, 4-2, first sliding track, 4-3, first wing root keyhole;
[0022] 8-1, second limiting hole, 8-2, second sliding track, 8-3, second wing root keyhole;
[0023] 10-1, press hole;
[0024] 14-1. Long holes. DETAILED DESCRIPTION
[0025] The following describes the specific implementation of the utility model in conjunction with embodiments:
[0026] It should be noted that the structures, proportions, sizes, etc. shown in this specification are only used to match the contents disclosed in the specification so that people familiar with this technology can understand and read them, and are not used to limit the conditions under which the present invention can be implemented. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical content disclosed in the present invention without affecting the effects and purposes that can be achieved by the present invention.
[0027] Example 1
[0028] like Figure 1~2 As shown, the utility model discloses a wing folding mechanism of a patrol aircraft, including a shaft cover 2, a small shaft sleeve 3, a right front wing 4, a double torsion spring 6, a large shaft sleeve 7, a left front wing 8, a wing shaft 9, a locking shaft 10 and a locking assembly, wherein the small shaft sleeve 3 is sleeved in the connecting hole groove of the right front wing 4, the large shaft sleeve 7 is sleeved in the connecting hole groove of the left front wing 8, the left front wing 8, the double torsion spring 6 and the right front wing 4 are sleeved on the wing shaft 9 in sequence, the end of the wing shaft 9 is fixedly connected to the shaft cover 2, and the double torsion spring 6 is located at In the connecting hole groove where the right front wing 4 and the left front wing 8 are connected, one end of the double torsion spring 6 is clamped in the first limiting hole 4-1 of the right front wing 4, and the other end of the double torsion spring 6 is clamped in the second limiting hole 8-1 of the left front wing 8. When the double torsion spring 6 is not subjected to torsion, the right front wing 4 and the left front wing 8 are in a straight line, and the locking assembly and the wing shaft 9 are fixedly connected to the fuselage by screws respectively. The locking assembly is located at the front side of the right front wing 4 and the left front wing 8, and the locking assembly locks the right front wing 4 and the left front wing 8 in a straight line.
[0029] The folding mechanism is that the left and right wings are automatically unfolded by the elastic force of the double torsion springs 6, and the locking assembly is locked after unfolding, and the unidirectional force is pressed horizontally and then manually folded.
[0030] Example 2
[0031] like Figure 1As shown, preferably, the locking assembly includes a locking shaft 10, a limit block cover 11, a second hexagon socket head screw 12, a limit spring 13 and a limit frame 14, the limit block cover 11 is fixedly installed in the limit frame 14 by the second hexagon socket head screw 12, one end of the locking shaft 10 is sleeved with the limit spring 13 and installed on the limit block cover 11, the other end of the locking shaft 10 passes through the limit frame 14 and then inserted into the keyholes of the right front wing 4 and the left front wing 8, the side of the limit frame 14 is provided with a long hole 14-1, the position of the long hole 14-1 corresponds to the pressing hole 10-1 of the locking shaft 10, and the locking assembly and the wing shaft 9 are fixedly connected to the fuselage by screws respectively.
[0032] like Figure 1 As shown, preferably, the locking shaft 10 is an "I"-shaped structure, a pressing hole 10-1 is arranged at the center position of the "I"-shaped structure, two through holes are arranged on the limit block cover 11 and the limit frame 14 respectively, a limit spring 13 is installed on one side of the locking shaft 10 and passes through the two through holes of the limit block cover 11, and the other side of the locking shaft 10 passes through the two through holes on the limit frame 14 for locking the right front wing 4 and the left front wing 8.
[0033] The cylindrical bidirectional locking shaft is displaced horizontally by a spring. When the wing is in a folded state, the locking shaft spring is in a compressed state. After the wing is unfolded, the front end of the locking shaft enters the keyhole at the root of the wing to lock the wing.
[0034] The locking assembly is for horizontally pressing the locking shaft 10, and the locking shaft 10 rebounds and disengages from the lock holes at the roots of the right front wing 4 and the left front wing 8, and then the wings are manually folded.
[0035] The locking assembly is located at the front end of the right front wing 4 and the left front wing 8, and the locking and opening and closing of the wings are achieved through the horizontal displacement of the locking shaft 10.
[0036] Example 3
[0037] like Figure 1 As shown, preferably, the end surface of the right front wing 4 close to the double torsion spring 6 is provided with a first limiting hole 4-1, and the end surface of the left front wing 8 close to the double torsion spring 6 is provided with a second limiting hole 8-1, one end of the double torsion spring 6 is clamped in the first limiting hole 4-1 of the right front wing 4, and the other end of the double torsion spring 6 is clamped in the second limiting hole 8-1 of the left front wing 8, the torsion at both ends of the double torsion spring 6 is the same, the angle between the two ends of the double torsion spring 6 and the center of the double torsion spring 6 is 30°, and the angle between the first limiting hole 4-1 and the second limiting hole 8-1 and the center of the double torsion spring 6 is also 30°, so that when the double torsion spring 6 is not subjected to torsion, the right front wing 4 and the left front wing 8 are in a straight line.
[0038] The angles between the two ends of the double-torsion torsion spring 6 and the center of the double-torsion torsion spring 6 can be adjusted as needed, and similarly, the first limiting hole 4-1 and the second limiting hole 8-1 also need to be adjusted accordingly.
[0039] The torsion forces at both ends of the double torsion spring 6 are the same, which can ensure that the left and right wings are unfolded to the horizontal position at the same time.
[0040] like Figure 1 As shown, preferably, a first sliding track 4-2 is provided on the side of the right front wing 4 close to the locking assembly, and a second sliding track 8-2 is provided on the side of the left front wing 8 close to the locking assembly, both ends of the first sliding track 4-2 form an angle of 90° with a line connecting the centers of the connecting holes and grooves of the right front wing 4, and both ends of the second sliding track 8-2 form an angle of 90° with a line connecting the centers of the connecting holes and grooves of the left front wing 8, a first wing root lockhole 4-3 is provided on the rightmost side of the first sliding track 4-2, and a second wing root lockhole 8-3 is provided on the leftmost side of the second sliding track 8-2, when the right front wing 4 and the left front wing 8 are in a straight line, the second wing root lockhole 8-3 is directly below the first wing root lockhole 4-3, and the locking shaft 10 passes through the limit frame 14 and is inserted into the first wing root lockhole 4-3 and the second wing root lockhole 8-3 to lock it.
[0041] Example 4
[0042] like Figure 1 As shown, preferably, a gasket 5 is provided on one end surface where the right front wing 4 and the left front wing 8 are connected, so as to reduce the sliding friction between the right front wing 4 and the left front wing 8.
[0043] like Figure 1 As shown, preferably, the shaft cover 2 and the end of the wing shaft 9 are fixedly connected by a first hexagon socket head screw 1.
[0044] like Figure 1 As shown, preferably, the small shaft sleeve 3 is sleeved in the connection hole groove of the right front wing 4 and fixed by screws, and the large shaft sleeve 7 is sleeved in the connection hole groove of the left front wing 8 and fixed by screws.
[0045] The right front wing 4 and the left front wing 8 of the utility model are also universal for the front and rear wings, and are fixedly connected to the fuselage through the built-in wing shaft of the mechanism. The front and rear wings can be coaxially folded toward the fuselage, and can be locked in a horizontal position after the wings are unfolded.
[0046] The working principle of the utility model is as follows:
[0047] like Figure 1~2As shown, the utility model discloses a wing folding mechanism of a patrol aircraft, including a shaft cover 2, a small shaft sleeve 3, a right front wing 4, a double torsion spring 6, a large shaft sleeve 7, a left front wing 8, a wing shaft 9, a locking shaft 10 and a locking assembly. The right front wing 4 and the left front wing 8 are connected to the wing shaft 9 through the small shaft sleeve 3 and the large shaft sleeve 7. The shaft cover 2 is fixedly connected to the end of the wing shaft 9 in a vertical direction. A washer 5 is used between the left front wing 8 and the right front wing 4 to reduce sliding friction. One end of the double torsion spring 6 is connected to the right front wing 4, and the other end is connected to the left front wing 8. The double torsion spring 6 built in the right front wing 4 and the left front wing 8 has the function of ensuring that the wing is always in a state to be unfolded inside the wing root. The wing shaft 9 is fixedly connected to the fuselage through screws. When folding is required, a fine The shaft is inserted into the pressing hole 10-1 of the locking shaft 10 from the long hole 14-1, and the locking shaft 10 is pushed horizontally. After the limit spring 13 is subjected to force, it is displaced horizontally. At the same time, the front end of the locking shaft 10 leaves the first wing root lockhole 4-3 and the second wing root lockhole 8-3, and the wings can be manually folded to be parallel to the fuselage for easy transportation and storage; when it needs to be unfolded, it is only necessary to manually release the folded wings, and the left and right wings will be quickly unfolded due to the elastic force of the double torsion spring 6. At the same time, the front end of the locking shaft 10 slides in the first sliding track 4-2 and the second sliding track 8-2 until the front end of the locking shaft 10 enters the first wing root lockhole 4-3 and the second wing root lockhole 8-3. At this moment, the left and right wings are unfolded to a completely horizontal state of 180°, and the locking assembly locks the wings to complete the locking.
[0048] The double torsion springs of the folding mechanism of the present invention can ensure the synchronization and coaxiality of the wing unfolding, and the locking assembly can ensure the timeliness of locking after the wing unfolds. The mechanism can ensure the flight stability and reliability of the cruiser and meet the convenience of the cruiser during storage and transportation.
[0049] The preferred embodiments of the present invention are described in detail above, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of ordinary technicians in this field without departing from the purpose of the present invention.
[0050] Many other changes and modifications can be made without departing from the concept and scope of the utility model. It should be understood that the utility model is not limited to a specific embodiment, and the scope of the utility model is defined by the appended claims.
Claims
1. A wing folding mechanism for a patrol aircraft, characterized in that: The invention comprises a rotating shaft cover (2), a small shaft sleeve (3), a right front wing (4), a double torsion spring (6), a large shaft sleeve (7), a left front wing (8), a wing rotating shaft (9), a locking shaft (10) and a locking assembly, wherein the small shaft sleeve (3) is sleeved in a connecting hole groove of the right front wing (4), the large shaft sleeve (7) is sleeved in a connecting hole groove of the left front wing (8), the left front wing (8), the double torsion spring (6) and the right front wing (4) are sleeved on the wing rotating shaft (9) in sequence, the end of the wing rotating shaft (9) is fixedly connected to the rotating shaft cover (2), the double torsion spring (6) is located between the right front wing (4) and the left In the connection hole groove where the front wings (8) are connected, one end of the double torsion spring (6) is clamped in the first limiting hole (4-1) of the right front wing (4), and the other end of the double torsion spring (6) is clamped in the second limiting hole (8-1) of the left front wing (8). When the double torsion spring (6) is not subjected to torsion, the right front wing (4) and the left front wing (8) are in a straight line. The locking assembly and the wing shaft (9) are respectively fixedly connected to the fuselage by screws. The locking assembly is located at the front side of the right front wing (4) and the left front wing (8). The locking assembly locks the right front wing (4) and the left front wing (8) in a straight line.
2. The wing folding mechanism of a patrol aircraft according to claim 1, characterized in that: The locking assembly comprises a locking shaft (10), a limit block cover plate (11), a second hexagon socket head screw (12), a limit spring (13) and a limit frame (14); the limit block cover plate (11) is fixedly mounted in the limit frame (14) by means of the second hexagon socket head screw (12); one end of the locking shaft (10) is sleeved with the limit spring (13) and mounted on the limit block cover plate (11); the other end of the locking shaft (10) passes through the limit frame (14) and is then inserted into the keyholes of the right front wing (4) and the left front wing (8); a long hole (14-1) is arranged on the side of the limit frame (14); the position of the long hole (14-1) corresponds to the pressing hole (10-1) of the locking shaft (10).
3. The wing folding mechanism of a patrol aircraft according to claim 2, characterized in that: The locking shaft (10) is an "I"-shaped structure, a pressing hole (10-1) is provided at the center of the "I"-shaped structure, two through holes are provided on the limit block cover plate (11) and the limit frame (14), respectively, a limit spring (13) is sleeved on one side of the locking shaft (10) and passes through the two through holes of the limit block cover plate (11), and the other side of the locking shaft (10) passes through the two through holes on the limit frame (14) for locking the right front wing (4) and the left front wing (8).
4. The patrol aircraft wing folding mechanism according to claim 3, characterized in that: The right front wing (4) is provided with a first limiting hole (4-1) on one end surface close to the double torsion spring (6), and the left front wing (8) is provided with a second limiting hole (8-1) on one end surface close to the double torsion spring (6). One end of the double torsion spring (6) is clamped in the first limiting hole (4-1) of the right front wing (4), and the other end of the double torsion spring (6) is clamped in the second limiting hole (8-1) of the left front wing (8). The torsion at both ends of the double torsion spring (6) is the same, and the angle between the two ends of the double torsion spring (6) and the center of the double torsion spring (6) is 30°. The angle between the first limiting hole (4-1) and the second limiting hole (8-1) and the center of the double torsion spring (6) is also 30°, so that when the double torsion spring (6) is not subjected to torsion, the right front wing (4) and the left front wing (8) are in a straight line.
5. The patrol aircraft wing folding mechanism according to claim 4, characterized in that: A first sliding track (4-2) is provided on one side of the right front wing (4) close to the locking assembly, and a second sliding track (8-2) is provided on one side of the left front wing (8) close to the locking assembly. The two ends of the first sliding track (4-2) are both at an angle of 90° to a line connecting the center of the connecting hole slot of the right front wing (4), and the two ends of the second sliding track (8-2) are both at an angle of 90° to a line connecting the center of the connecting hole slot of the left front wing (8). A first wing root lock eye (4-3) is provided on the rightmost side of the first sliding track (4-2), and a second wing root lock eye (8-3) is provided on the leftmost side of the second sliding track (8-2). When the right front wing (4) and the left front wing (8) are in a straight line, the second wing root lock eye (8-3) is directly below the first wing root lock eye (4-3), and the locking shaft (10) passes through the limiting frame (14) and is inserted into the first wing root lock eye (4-3) and the second wing root lock eye (8-3) to lock them.
6. The patrol aircraft wing folding mechanism according to claim 1, characterized in that: A gasket (5) is provided on one end surface where the right front wing (4) and the left front wing (8) are connected, and is used to reduce the sliding friction between the right front wing (4) and the left front wing (8).
7. The patrol aircraft wing folding mechanism according to claim 1, characterized in that: The rotating shaft cover (2) and the end of the wing rotating shaft (9) are fixedly connected via a first hexagon socket head screw (1).
8. The patrol aircraft wing folding mechanism according to claim 1, characterized in that: The small shaft sleeve (3) is sleeved in the connection hole groove of the right front wing (4) and fixed by screws, and the large shaft sleeve (7) is sleeved in the connection hole groove of the left front wing (8) and fixed by screws.