Aircraft arm with self-locking folding mechanism

Abstract

The invention relates to an aircraft arm with a self-locking folding mechanism, and belongs to the technical field of aircrafts. The machine arm comprises a fixing sleeve, a folding sleeve, a buckling piece and a self-locking bolt assembly. The fixing sleeve and the folding sleeve are arranged on the first vehicle arm and the second vehicle arm respectively in a sleeving mode and hinged. And a first hinge plate with a lateral clamping groove is arranged on the folding sleeve. One end of the fastener is hinged to the first hinge point of the fixing sleeve, and the other end is hinged to the first hinge plate through a connecting rod. The self-locking bolt assembly is arranged in the buckling piece, and automatic clamping is achieved by clamping a bolt into the lateral clamping groove. The connecting rod principle is combined with the self-locking bolt, a double-safety locking mechanism of the vehicle arm is formed, the folding and unfolding stability of the vehicle arm is guaranteed, meanwhile, rapid operation and effective looseness prevention are achieved, and the requirement for the machining tolerance of parts is lowered.

Description

Technical Field

[0001] This invention belongs to the field of aircraft technology, specifically relating to an aircraft arm with a self-locking folding mechanism. Background Technology

[0002] The arm folding mechanism is a crucial component in aircraft design, bearing the load and functioning of the arm during folding. Currently, there are various types of arm folding mechanisms. One method involves manually tightening nuts to secure the folding section. This method is time-consuming during each folding and unfolding operation and is only suitable for small-diameter arm tubes. Another method uses a manual rotating disc. The disc is located at the fixed end of the arm. After the arm unfolds and the two ends are aligned, the disc is manually rotated to ensure its limiting plate engages precisely in the limiting groove of the folding end. However, this method requires very strict control over the dimensional tolerances of the machined parts. If the fixed and folding ends are not fully aligned when the arm is unfolded, the disc's limiting plate may not easily engage in the limiting groove.

[0003] The folding section of the arm is tightened manually by tightening the nuts. The disadvantage of this method is that it is time-consuming each time it is folded and unfolded, and this mechanism is only suitable for small-diameter arm tubes. Another method uses a manual rotating disc, located at the fixed end of the arm. After the arm is unfolded and the two ends are aligned, the disc is manually swung to ensure its limiting plate is precisely engaged in the limiting groove of the folding end. However, this method requires very strict control of the machined parts' dimensional tolerances. If the fixed end and the folding end are not fully aligned when the arm is unfolded, the limiting plate of the rotating disc may not easily engage in the limiting groove of the folding end.

[0004] In view of this, this solution was developed. Summary of the Invention

[0005] In view of the shortcomings of the prior art, the technical problem to be solved by the present invention is to provide an aircraft arm with a self-locking folding mechanism. It adopts a double-insurance locking mechanism and ensures the stability of the arm during folding and unfolding. One method is to use the principle of linkage to lock the arm. On this basis, another self-locking pin assembly is added to form a double-insurance locking mechanism for the arm.

[0006] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is: an aircraft arm with a self-locking folding mechanism, including a fixing sleeve, a folding sleeve, a buckle and a self-locking pin assembly; The fixed sleeve is fitted onto the first arm. The fixed sleeve has a frame on the side facing the folding sleeve. The frame has a notch. The frame has first rotating holes on the upper and lower sides near the notch. The fixed sleeve has a first hinge point on the side away from the notch. The folding sleeve is fitted onto the second arm. A mounting ring is formed on the side of the folding sleeve facing the fixed sleeve. One side of the mounting ring extends into the notch and is hinged through the first rotating hole via the first rotating shaft. A first hinge plate is formed on the side wall of the folding sleeve corresponding to the first hinge point. The first hinge plate has a lateral groove. The fastener includes a fastener plate with a receiving groove. The first hinge point is located at one end of the receiving groove and is hinged through a second pivot. The other end of the receiving groove is hinged to the first hinge plate through a connecting rod, and the connecting rod is hinged to the receiving groove. The self-locking pin assembly is disposed in the receiving groove and the operating end is located on the outward side of the buckle plate. The self-locking pin assembly is locked by the pin being inserted into the lateral slot.

[0007] Furthermore, the first hinge plate includes a base, the lateral slot is located on the side of the base facing the second arm, the surface of the base is provided with a vertical plate, the vertical plate is hinged to the first hinge rod, and the total height of the vertical plate and the base is less than the height of the receiving slot.

[0008] Furthermore, the self-locking pin assembly includes a pin base, a pin, and a compression spring. The pin base has a sliding groove, and the sliding groove has an extension hole on its side facing the first arm. The pin slides within the sliding groove. The side of the pin facing the extension hole has a pin member, and the pin can extend out of the extension hole. The compression spring is located between the sliding groove and the pin.

[0009] Furthermore, there are two sliding grooves spaced apart, and two sliders are formed on the lower surface of the pin. The two sliders are located in the two sliding grooves respectively, and the pin is located on the side of the slider.

[0010] Furthermore, a push plate is formed on the surface of the pin.

[0011] Furthermore, a holding plate is formed at the end of the buckle plate facing the second arm.

[0012] Furthermore, a first hinge seat is formed at the first hinge point position. The first hinge seat extends into the receiving groove and is hinged through a second rotating shaft. A torsion spring is provided on the second rotating shaft, and the torsion spring is used to reset the buckle plate.

[0013] Furthermore, the fixing sleeve includes a mounting part and a hinge part. The mounting part is connected to the first machine arm. A through hole is formed on the surface of the mounting part. An inner liner is provided at the through hole. A threaded hole is formed on the inner liner.

[0014] Compared with the prior art, the present invention has the following beneficial effects: 1. The folding of the first and second arms adopts a double-safety locking mechanism, which ensures the stability of the arms during folding and unfolding while locking. One mechanism uses the principle of linkage to lock the arms, and on this basis, another mechanism of pin locking is added to form a double-safety locking mechanism for the arms.

[0015] 2. This double-locking mechanism enables the arm to be folded and unfolded quickly without any automatic loosening.

[0016] 3. This double-safety locking mechanism does not have very strict requirements on the machining tolerances of the parts. When locking using the linkage principle, the optimal locking function can be achieved by finely adjusting the length of the connecting rod.

[0017] 4. A double-safety locking mechanism is adopted. When the arm is extended and the buckle is swinging, the side slot on the first hinge plate will automatically move backward after contacting the self-locking pin assembly. When the buckle is in place, the self-locking pin assembly will automatically insert the pin on the pin into the side slot using the compression spring. Attached Figure Description

[0018] Figure 1 This is a three-dimensional structural diagram of an aircraft arm with a self-locking folding mechanism according to the present invention. Figure 2 This is a three-dimensional structural diagram of the self-locking pin assembly in this invention; Figure 3 This is a three-dimensional structural diagram of the present invention from another direction; Figure 4 This is a three-dimensional structural diagram of the internal structure of the fixing sleeve in this invention.

[0019] The markings in the diagram are: 1. Fixed sleeve; 2. Folding sleeve; 3. First pivot; 4. Buckle plate; 5. Self-locking pin assembly; 6. Second pivot; 7. Third pivot; 8. Connecting rod; 9. Pin; 91. Pin; 10. Compression spring; 11. Pin base; 12. Torsion spring; 13. Fish eye hole; 14. Fourth pivot; 15. Lining. Detailed Implementation

[0020] To make the above features and advantages of the present invention more apparent and understandable, specific embodiments are described below in conjunction with the accompanying drawings for detailed explanation.

[0021] like Figures 1-4 As shown, this embodiment provides an aircraft arm with a self-locking folding mechanism, including a fixed sleeve 1, a folding sleeve 2, a buckle and a self-locking pin assembly 5.

[0022] The fixing sleeve 1 is fitted onto the first machine arm. Specifically, the fixing sleeve 1 includes a mounting part and a hinge part. The mounting part is connected to the first machine arm. A through hole is formed on the surface of the mounting part. An inner liner 15 is provided at the through hole. A threaded hole is formed on the inner liner 15. A screw passes through the threaded hole of the inner liner 15 and is connected to the adapter hole on the machine arm.

[0023] The fixed sleeve 1 has a frame on the side facing the folding sleeve 2. The frame mentioned here is the hinge part. The frame has a notch. The upper and lower sides of the frame near the notch have first rotating holes. The fixed sleeve 1 has a first hinge point on the side away from the notch. A first hinge seat is formed at the first hinge point.

[0024] Connection between folding sleeve 2 and the second arm: Folding sleeve 2 is fitted onto the second arm. The side of folding sleeve 2 facing fixed sleeve 1 is provided with a mounting ring, which extends into the notch of the frame of fixed sleeve 1, and the two are pivotally connected by the first rotating shaft 3 passing through the first rotating hole.

[0025] On the sidewalls corresponding to the first hinge seat of the folding sleeve 2 and the fixed sleeve 1, a first hinge plate is provided. The first hinge plate includes a seat body, a lateral slot located on the side of the seat body facing the second arm, and two spaced vertical plates on the surface of the seat body. A connecting rod 8 extends between the two vertical plates for hinge connection. The total height of the vertical plates and the seat body is less than the height of the receiving groove. The fastener includes a fastening plate 4, which has a receiving groove inside. A holding plate is formed at the end of the fastening plate 4 facing the second arm. The first hinge seat extends into one end of the receiving groove and is hinged through the second rotating shaft 6. The other end of the receiving groove is connected to the first hinge plate through the connecting rod 8. The two ends of the connecting rod 8 are respectively hinged to the receiving groove and the vertical plates on the first hinge plate. Specifically, holes are formed on both sides of the receiving groove, and the end of the connecting rod 8 has a fisheye hole 13. The two are hinged to the nut after passing through the holes and the fisheye hole 13 through the third rotating shaft 7. The other end of the connecting rod 8 is connected by inserting a fourth rotating shaft 14, which is existing technology and will not be described in detail here.

[0026] A locking assembly is provided between the buckle plate 4 and the second arm or folding sleeve 2. The locking assembly commonly used in existing buckle structures can be used.

[0027] To achieve a "double-safety" locking mechanism, this invention integrates a self-locking pin assembly 5 within the buckle receiving groove. The bottom of the receiving groove has an operation clearance hole corresponding to the self-locking pin assembly 5. The self-locking pin assembly 5 includes a pin base 11, a pin 9, and a compression spring 10. The pin base 11 forms a sliding groove, and the side of the sliding groove facing the first arm forms an extension hole. The pin 9 slides within the sliding groove. The side of the pin 9 facing the extension hole has a pin 91, allowing the pin 9 to extend out of the extension hole. The compression spring 10 is located between the sliding groove and the pin 9. Specifically, there are two sliding grooves spaced apart. Two sliders are formed on the lower surface of the pin 9, each located within one of the two sliding grooves. The pin 91 is located on the side of the slider. A push plate is formed on the surface of the pin 9. A strip-shaped hole is provided at the bottom of the sliding groove. A connecting hole is formed on the inward-facing side of the pin 9. A screw passes through the strip-shaped hole and screws into the connecting hole, with the screw head locking against the outside of the strip-shaped hole. This arrangement ensures that the pin 9 will not dislodge from the sliding groove.

[0028] Locking principle: The pin base 11 has an extension hole on its side facing the first arm. The slider side of the pin 9 has a pin 91, which can extend through the extension hole. The compression spring 10 is located between the sliding groove and the pin 9, and always provides an outward preload force.

[0029] Unfolding and Locking Process: 1. Rotate the second arm to make the folding sleeve 2 fit against the fixed sleeve 1. At this time, the latch will rotate outward and the connecting rod 8 will move towards the receiving groove closer to the first arm until it enters; 2. Swing the latch towards the second arm. At this time, under the limit of the torsion spring 12 on the second rotating shaft 6 and the latch, the connecting rod 8 achieves the first locking by utilizing the mechanical principle of the connecting rod 8 mechanism. 3. During the swinging of the latch into position, the pin 91 of the self-locking pin assembly 5 contacts the first hinge plate. The pin 91 is pressed back, and when the latch is fully in position, the pin 91 automatically springs into the lateral slot on the first hinge plate under the action of the compression spring 10. At this time, the pin 9 automatically engages, forming the second locking safety, effectively preventing the latch from accidentally loosening.

[0030] Folding and unlocking process: 1. Manually move the push plate on the surface of the buckle plate 4 to overcome the spring force of the compression spring 10, causing the pin 91 to disengage from the lateral slot of the first hinge plate. 2. Pull the buckle outward (this can be done through the gripping plate at the end of the buckle plate 4) to release the clamping force on the folding sleeve 2 via the connecting rod 8. 3. Rotate the second arm around the first pivot 3 to complete the folding of the arm.

[0031] This embodiment solves the problems of long processing time and excessively high machining tolerance requirements of traditional folding mechanisms by combining the locking of link 8 and the self-locking pin 9. The length of link 8 can be finely adjusted to compensate for machining errors, while the self-locking pin 9 ensures that the folding part of the arm can still maintain structural stability and will not automatically loosen even in high-vibration flight environments.

[0032] The foregoing has shown and described the basic principles and main features of the present invention, as well as its advantages. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the present invention. Various changes and modifications can be made to the present invention without departing from its spirit and scope. All such changes and modifications fall within the scope of the present invention as claimed, which is defined by the appended claims and their equivalents.

Claims

1. An aircraft arm with a self-locking folding mechanism, characterized in that: Includes a fixing sleeve, a folding sleeve, a snap fastener, and a self-locking pin assembly; The fixed sleeve is fitted onto the first arm. The fixed sleeve has a frame on the side facing the folding sleeve. The frame has a notch. The frame has first rotating holes on the upper and lower sides near the notch. The fixed sleeve has a first hinge point on the side away from the notch. The folding sleeve is fitted onto the second arm. A mounting ring is formed on the side of the folding sleeve facing the fixed sleeve. One side of the mounting ring extends into the notch and is hinged through the first rotating hole via the first rotating shaft. A first hinge plate is formed on the side wall of the folding sleeve corresponding to the first hinge point. The first hinge plate has a lateral groove. The fastener includes a fastener plate with a receiving groove. The first hinge point is located at one end of the receiving groove and is hinged through a second pivot. The other end of the receiving groove is hinged to the first hinge plate through a connecting rod, and the connecting rod is hinged to the receiving groove. The self-locking pin assembly is disposed in the receiving groove and the operating end is located on the outward side of the buckle plate. The self-locking pin assembly is locked by the pin being inserted into the lateral slot.

2. The aircraft arm with a self-locking folding mechanism according to claim 1, characterized in that: The first hinge plate includes a base, the lateral slot is located on the side of the base facing the second arm, the surface of the base is provided with a vertical plate, the vertical plate is hinged to the first hinge rod, and the total height of the vertical plate and the base is less than the height of the receiving slot.

3. The aircraft arm with a self-locking folding mechanism according to claim 2, characterized in that: The self-locking pin assembly includes a pin base, a pin, and a compression spring. The pin base has a sliding groove, and the sliding groove has an extension hole on its side facing the first arm. The pin slides within the sliding groove. The side of the pin facing the extension hole has a pin member, and the pin can extend out of the extension hole. The compression spring is located between the sliding groove and the pin.

4. The aircraft arm with a self-locking folding mechanism according to claim 3, characterized in that: The sliding grooves are two in number and spaced apart. Two sliders are formed on the lower surface of the pin. The two sliders are located in the two sliding grooves respectively, and the pin is located on the side of the slider.

5. An aircraft arm with a self-locking folding mechanism according to claim 3, characterized in that: A push plate is formed on the surface of the pin.

6. The aircraft arm with a self-locking folding mechanism according to claim 1, characterized in that: The buckle plate has a holding plate at the end facing the second arm.

7. The aircraft arm with a self-locking folding mechanism according to claim 1, characterized in that: A first hinge seat is formed at the first hinge point. The first hinge seat extends into the receiving groove and is hinged by a second rotating shaft. A torsion spring is provided on the second rotating shaft. The torsion spring is used to reset the buckle plate.

8. The aircraft arm with a self-locking folding mechanism according to claim 1, characterized in that: The fixing sleeve includes a mounting part and a hinge part. The mounting part is connected to the first machine arm. A through hole is formed on the surface of the mounting part. An inner liner is provided at the through hole. A threaded hole is formed on the inner liner.

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