Folding wing auxiliary device and aircraft

Abstract

The invention provides a folding wing auxiliary device and an aircraft, and relates to the technical field of aircrafts, the folding wing auxiliary device comprises an actuating mechanism arranged in the abdomen of the aircraft and a limiting mechanism arranged in a folding wing of the aircraft, a bottom plate of the abdomen of the aircraft is provided with a pair of through holes; the actuating mechanism comprises a pair of locking rods which are oppositely arranged in the abdomen of the aircraft and a driving assembly for driving the pair of locking rods to move in the opposite direction and / or the reverse direction; the limiting mechanism comprises grooves formed in the surfaces of the two folding wings of the aircraft respectively, limiting blocks movably arranged in the grooves and elastic components, the two limiting blocks correspond to the two through holes respectively, a lock hole matched with the lock rod is formed in one end of each limiting block, and the other end of each limiting block is rotationally matched with the groove wall of the corresponding groove; the elastic component is connected with the limiting block and the groove wall of the groove and used for providing elastic force for the limiting block to reset the limiting block into the groove. The problem that in the prior art, a folding wing located on the abdomen of an aircraft lacks a simple and reliable locking and releasing device is solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft, and more specifically, relates to a folding wing auxiliary device and an aircraft. Background Art

[0002] At present, the folding wing technology of small aircraft at home and abroad has become very mature, with advantages such as high reliability, practicality, and economy.

[0003] However, the folding wing technology of current aircraft also has areas that need improvement. Among them, most folding wings located on the aircraft's belly lack simple and reliable locking and releasing devices.

[0004] Therefore, the present invention provides a simple and reliable limiting, fixing, and unfolding and releasing device, which has certain progressive significance in this field. Summary of the Invention

[0005] The purpose of the present invention is to provide a folding wing auxiliary device to address the deficiencies in the prior art and to solve the problem that the folding wings located on the belly of the aircraft in the prior art lack simple and reliable locking and releasing devices.

[0006] In order to achieve the above object, the present invention provides a folding wing auxiliary device, comprising:

[0007] An actuating mechanism is provided in the belly of the aircraft and a limiting mechanism is provided in the folding wings of the aircraft. A pair of through holes is provided on the bottom plate of the belly of the aircraft:

[0008] The actuating mechanism comprises a pair of locking rods arranged opposite to each other in the belly of the aircraft and a driving assembly for driving the pair of locking rods to move toward and / or in opposite directions;

[0009] The limiting mechanism includes grooves respectively arranged on the surfaces of the two folding wings of the aircraft, a limiting block movably arranged in the groove and an elastic component, the two limiting blocks respectively correspond to the two through holes, one end of the limiting block is provided with a locking hole that cooperates with the locking rod, and the other end of the limiting block is rotatably matched with the groove wall of the groove, the elastic component is connected to the limiting block and the groove wall of the groove, and is used to provide the limiting block with elastic force to reset it into the groove.

[0010] Optionally, the actuating mechanism further includes:

[0011] Two connecting rods, each of which is L-shaped, and one end of each connecting rod is vertically connected to one of the locking rods;

[0012] At least one pair of guide seats is connected to the inner side of the belly bottom plate of the aircraft. Guide holes are provided in the guide seats, and the guide holes are matched with the connecting rod or the locking rod.

[0013] Optionally, the drive assembly includes:

[0014] a gear, the gear being rotatably disposed between the two connecting rods;

[0015] a rack portion, provided at one end of each connecting rod away from the locking rod, the rack portion being engaged with the gear;

[0016] A telescopic component is connected to one of the connecting rods.

[0017] Optionally, the gear is a sector gear and includes two sector portions that are arranged opposite to each other, and the two sector portions are respectively matched with the two rack portions.

[0018] Optionally, the elastic component is a torsion spring, and the torsion spring is a U-shaped rod structure. The edges on both sides of the opening of the torsion spring are respectively embedded in the groove wall of the groove and the limiting block.

[0019] Optionally, the groove is open on one side close to the belly of the aircraft, and a first mounting groove is provided on both side walls of the groove, and a second mounting groove is provided on both sides of the other end of the limit block, and the edges on both sides of the opening of the torsion spring are respectively embedded in the first mounting groove and the second mounting groove.

[0020] Optionally, an assembly groove is provided at the other end of the limiting block, an assembly cover is detachably connected to the assembly groove, and the second installation groove is formed between the assembly cover and the assembly groove.

[0021] Optionally, the telescopic component is an electromagnetic actuator.

[0022] The present invention also provides an aircraft, comprising the above-mentioned folding wing auxiliary device.

[0023] Optionally, the folding wings of the aircraft are rotatably connected to both sides below the belly of the aircraft, and the folding wings are provided with elastic unfolding devices.

[0024] The present invention provides a folding-wing auxiliary device and an aircraft, the beneficial effects of which are: the folding-wing auxiliary device has an actuating mechanism located in the belly of the aircraft and a limiting mechanism located on the folding wing, the limiting block of the limiting mechanism can rotate in a groove so that it stands up in the groove, and one end of the limiting block passes through a through hole into the belly of the aircraft, at which time the locking rod of the actuating mechanism can be inserted into the locking hole to lock the folding wing, and when the folding wing needs to be released, the two locking rods are driven out of the locking hole at the same time by the driving assembly of the actuating mechanism, and under the action of the elastic component, the limiting block automatically resets to the groove and releases the lock of the folding wing under the belly of the aircraft, at which time the folding wing can be unfolded, the folding-wing auxiliary device has a simple structure and good reliability, and can realize the locking and synchronous release of the folding state of the folding wing under the belly of the aircraft.

[0025] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention with reference to the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0027] Figure 1 A structural schematic diagram showing a locked state of a folding wing auxiliary device according to an embodiment of the present invention is shown.

[0028] Figure 2 A schematic diagram of the exploded structure of a folding wing auxiliary device according to an embodiment of the present invention is shown.

[0029] Figure 3 A schematic structural diagram of an actuating mechanism of a folding wing auxiliary device according to an embodiment of the present invention is shown.

[0030] Figure 4 A schematic structural diagram of a limiting mechanism of a folding wing auxiliary device according to an embodiment of the present invention is shown.

[0031] Figure 5 A schematic diagram of the exploded structure of a limiting mechanism of a folding wing auxiliary device according to an embodiment of the present invention is shown.

[0032] Figure 6 A schematic structural diagram of a folding wing auxiliary device before unlocking according to an embodiment of the present invention is shown.

[0033] Figure 7 A schematic structural diagram of a folding wing auxiliary device after unlocking is shown according to an embodiment of the present invention.

[0034] Figure 8 A schematic structural diagram of unfolding the folding wings of a folding wing auxiliary device according to an embodiment of the present invention is shown.

[0035] Description of reference numerals:

[0036] 1. Aircraft; 2. Folding wing auxiliary module; 3. Folding wings;

[0037] 2-1, pin; 2-2, electromagnetic actuator; 2-3, retaining spring; 2-4, connecting rod; 2-5, sector gear; 2-6, rotating shaft; 2-7, first guide seat; 2-8, second guide seat;

[0038] 3-1. Groove; 3-2. First mounting groove; 3-3. Limit block; 3-4. Torsion spring; 3-5. Assembly cover; 3-6. Screw. DETAILED DESCRIPTION

[0039] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. Instead, these embodiments are provided to make the present invention more thorough and complete and to fully convey the scope of the present invention to those skilled in the art.

[0040] like Figure 1 As shown, the present invention provides a folding wing auxiliary device, comprising:

[0041] The actuating mechanism is provided in the belly of the aircraft 1 and the limiting mechanism is provided in the folding wing 3 of the aircraft 1. A pair of through holes is provided on the bottom plate of the belly of the aircraft 1:

[0042] The actuating mechanism comprises a pair of locking rods disposed oppositely in the belly of the aircraft 1 and a driving assembly for driving the pair of locking rods to move toward and / or in opposite directions;

[0043] The limiting mechanism includes grooves 3-1 respectively arranged on the surfaces of the two folding wings 3 of the aircraft 1, a limiting block 3-3 movably arranged in the groove 3-1 and an elastic component. The two limiting blocks 3-3 correspond to the two through holes respectively. One end of the limiting block 3-3 is provided with a locking hole that cooperates with the locking rod, and the other end of the limiting block 3-3 is rotatably matched with the groove wall of the groove 3-1. The elastic component is connected to the limiting block 3-3 and the groove wall of the groove 3-1, and is used to provide the limiting block 3-3 with elastic force to reset it to the groove 3-1.

[0044] The folding wing 3 is locked and released when the folding wing 3 is in the unlocked position, and the folding wing 3 is unlocked when the folding wing 3 is in the unlocked position.

[0045] Optionally, the actuating mechanism further includes:

[0046] Two connecting rods 2-4, each connecting rod 2-4 is L-shaped, and one end of each connecting rod 2-4 is vertically connected to a locking rod;

[0047] At least one pair of guide seats is connected to the inner side of the belly bottom plate of the aircraft 1, and guide holes are provided in the guide seats, which cooperate with the connecting rods 2-4 or the locking rods.

[0048] Specifically, such as Figure 2 and Figure 3 As shown, each connecting rod 2-4 includes a first rod and a second rod connected perpendicularly to each other to form an L-shaped structure, the first rod is longer than the second rod, the second rod is perpendicularly connected to the locking rod, and a U-shaped structure is formed at the end of the first rod near the second rod. The axes of the two locking rods are collinear, and the two first rods are respectively arranged on both sides of the axes of the two locking rods, so that a gap is formed between the two first rods, and each pair of guide seats is respectively slidably matched with the two first rods or the two locking rods to provide guidance for the movement of the two locking rods.

[0049] In this embodiment, two pairs of guide seats are provided, a pair of first guide seats 2-7 and a pair of second guide seats 2-8, and the first guide seats 2-7 and the second guide seats 2-8 cooperate with the connecting rod 2-4 and the locking rod respectively.

[0050] Optionally, the drive assembly includes:

[0051] Gear, the gear rotation is set between the two connecting rods 2-4;

[0052] A rack portion is provided at an end of each connecting rod 2-4 away from the locking rod, and the rack portion is engaged with the gear;

[0053] The telescopic part is connected with a connecting rod 2-4.

[0054] Specifically, the gear is located between the first rods of the two connecting rods 2-4. By meshing the gear with the rack portions on the first rods of the two connecting rods 2-4, the two connecting rods 2-4 can be synchronously moved through the transmission of the gear when the telescopic part is extended or retracted, which not only saves power components but also ensures that the two folding wings 3 are unlocked synchronously.

[0055] Optionally, the gear is a sector gear 2-5, and includes two sector portions arranged opposite to each other, and the two sector portions are respectively matched with the two rack portions.

[0056] Specifically, the provision of the sector gears 2 - 5 can reduce the weight of the device and the aircraft 1 as a whole.

[0057] In this embodiment, a rotating shaft 2-6 is provided on the upper side of the bottom plate of the belly of the aircraft 1, and the gear is rotatably mounted on the rotating shaft 2-6 and is clamped and limited by a retaining spring 2-3.

[0058] Optionally, the elastic component is a torsion spring 3-4, which is a U-shaped rod structure, and the edges on both sides of the opening of the torsion spring 3-4 are respectively embedded in the groove wall of the groove 3-1 and the limit block 3-3.

[0059] Specifically, such as Figure 4 and Figure 5 As shown, the U-shaped torsion spring 3-4 is embedded in the groove wall of the groove 3-1 and the limit block 3-3 through the edges on both sides of its opening, and the function of the torsion spring 3-4 is realized by the relative torsion between the rod-shaped portion of its closed end and the edges on both sides of its opening. This design allows the limit block 3-3 to be rotatably installed in the groove 3-1 without the need for a rotating shaft 2-6. When the folding wing 3 is locked, the limit block 3-3 can be rotated to stand in the groove 3-1 and allow the locking rod to pass through the lock hole. When the locking rod is out of the lock hole, the elastic force of the torsion spring 3-4 can be used to automatically reset the limit block 3-3 to the groove 3-1, thereby realizing embedding in the groove 3-1.

[0060] In this embodiment, when the limiting block 3 - 3 is reset under the action of the elastic component, the limiting block 3 - 3 fills the groove 3 - 1 to maintain the integrity of the aerodynamic shape of the folding wing 3 .

[0061] Optionally, the groove 3-1 is open on one side close to the belly of the aircraft 1, and a first mounting groove 3-2 is provided on both side walls of the groove 3-1, and a second mounting groove is provided on both sides of the other end of the limit block 3-3, and the edges on both sides of the opening of the torsion spring 3-4 are respectively embedded in the first mounting groove 3-2 and the second mounting groove.

[0062] Specifically, one side of the torsion spring 3 - 4 is inserted into the first groove 3 - 1 , and the other side of the torsion spring 3 - 4 is embedded in the second groove 3 - 1 , thereby achieving the installation of the torsion spring 3 - 4 .

[0063] Optionally, the other end of the limiting block 3-3 is provided with an assembly groove, in which an assembly cover 3-5 is detachably connected, and a second installation groove is formed between the assembly cover 3-5 and the assembly groove.

[0064] Specifically, the detachable setting of the assembly cover 3-5 can further facilitate the installation of the torsion spring 3-4 and the limit block 3-3.

[0065] In this embodiment, mounting holes are provided on the assembly cover 3-5 and the limiting block 3-3, and the assembly cover 3-5 is mounted on the limiting block 3-3 by screws 3-6.

[0066] Optionally, the telescopic component is an electromagnetic actuator 2-2.

[0067] Specifically, the electromagnetic actuator 2-2 is connected to a connecting rod 2-4 to drive it to move, and through the drive of the gear, the two connecting rods 2-4 move synchronously towards each other or synchronously in opposite directions.

[0068] In this embodiment, a connecting rod 2-4 is provided with a pin hole at one end close to its rack portion and the telescopic end of the telescopic component, and the pin 2-1 passes through the pin hole to achieve the connection between the telescopic component and the connecting rod 2-4.

[0069] In summary, when assembling the folding wing auxiliary device 2 provided by the present invention, the actuating mechanism is assembled first. First, the connecting rod 2-4 is installed on the bottom plate of the belly of the aircraft 1 through the guide seat, and then the gear is installed on the rotating shaft 2-6, and fixed with the retaining ring 2-3 at the upper end, and then the electromagnetic actuator 2-2 is connected to the connecting rod 2-4 through the pin 2-1; then the limiting mechanism is assembled, first, the limiting block 3-3 is installed into the groove 3-1 of the folding wing 3, and then the two torsion springs 3-4 are installed into the first installation groove 3-2, and fit well with the bottom of the assembly groove of the limiting block 3-3, and then the assembly cover 3-5 is installed on the limiting block 3-3 by the screw 3-6.

[0070] After the assembly is completed, the folded folding wings 3 are locked, such as Figure 6 As shown, first rotate the limit block 3-3 to the vertical position, then the electromagnetic actuator 2-2 performs a contraction action, and the sector gear 2-5 simultaneously drives the two connecting rods 2-4 to pass through the lock hole on the limit block 3-3 and complete the connection with it, thereby achieving the limit and fixation of the folding wing 3. When the folding wing 3 needs to be unfolded, as shown Figure 7 and Figure 8 As shown, the electromagnetic actuator 2-2 pushes the connecting rod 2-4 to operate, the locking rod withdraws from the matching limit block 3-3, and drives the two connecting rods 2-4 to move simultaneously through the sector gear 2-5, and at the same time releases the lock of the two limit blocks 3-3. The limit blocks 3-3 are folded inwardly under the action of the torsion spring 3-4. At this time, the folding wings 3 are unfolded under the drive of their power source.

[0071] The present invention also provides an aircraft, comprising the above-mentioned folding-wing auxiliary device 2 .

[0072] Specifically, when the folding wing 3 of the aircraft 1 is folded, the limit block 3-3 stands up in the groove 3-1, and the locking rod is passed through the locking hole to reliably lock the folding wing 3. When the folding wing 3 needs to be unfolded, the actuating mechanism drives the two locking rods to move synchronously and disengage from the locking hole. The folding wing 3 is unlocked, and under the action of the elastic component, the limit block 3-3 rotates and resets to the groove 3-1.

[0073] Optionally, the folding wings 3 of the aircraft 1 are rotatably connected to both sides below the belly of the aircraft 1 , and the folding wings 3 are provided with elastic unfolding devices.

[0074] Specifically, the folding wings 3 of the aircraft 1 are unfolded by an elastic unfolding device. When the folding wing auxiliary device 2 releases the lock on the folding wings 3, the folding wings 3 are automatically unfolded, which is very convenient.

[0075] While various embodiments of the present invention have been described above, the above description is intended to be illustrative, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A folding wing auxiliary device, characterized in that: include: An actuating mechanism is provided in the belly of the aircraft and a limiting mechanism is provided in the folding wings of the aircraft. A pair of through holes is provided on the bottom plate of the belly of the aircraft: The actuating mechanism comprises a pair of locking rods arranged opposite to each other in the belly of the aircraft and a driving assembly for driving the pair of locking rods to move toward and / or in opposite directions; The limiting mechanism includes grooves respectively arranged on the surfaces of the two folding wings of the aircraft, a limiting block movably arranged in the groove and an elastic component, the two limiting blocks respectively correspond to the two through holes, one end of the limiting block is provided with a locking hole that cooperates with the locking rod, and the other end of the limiting block is rotatably matched with the groove wall of the groove, the elastic component is connected to the limiting block and the groove wall of the groove, and is used to provide the limiting block with elastic force to reset it into the groove.

2. The folding wing assist device according to claim 1, characterized in that: The actuating mechanism further comprises: Two connecting rods, each of which is L-shaped, and one end of each connecting rod is vertically connected to one of the locking rods; At least one pair of guide seats is connected to the inner side of the belly bottom plate of the aircraft. Guide holes are provided in the guide seats, and the guide holes are matched with the connecting rod or the locking rod.

3. The folding wing assist device according to claim 2, characterized in that: The drive assembly includes: a gear, the gear being rotatably disposed between the two connecting rods; a rack portion, provided at one end of each connecting rod away from the locking rod, the rack portion being engaged with the gear; A telescopic component is connected to one of the connecting rods.

4. The folding wing assist device according to claim 3, characterized in that: The gear is a sector gear and includes two sector parts that are arranged opposite to each other. The two sector parts are matched with the two rack parts respectively.

5. The folding wing assist device according to claim 1, characterized in that: The elastic component is a torsion spring, which is a U-shaped rod structure. The edges on both sides of the opening of the torsion spring are respectively embedded in the groove wall of the groove and the limiting block.

6. The folding wing assist device according to claim 5, characterized in that: The groove is open on one side close to the belly of the aircraft, and a first mounting groove is provided on both side walls of the groove. Second mounting grooves are provided on both sides of the other end of the limit block, and the edges on both sides of the opening of the torsion spring are respectively embedded in the first mounting groove and the second mounting groove.

7. The folding wing assist device according to claim 6, characterized in that: The other end of the limiting block is provided with an assembly groove, an assembly cover is detachably connected to the assembly groove, and the second installation groove is formed between the assembly cover and the assembly groove.

8. The folding wing assist device according to claim 3, characterized in that: The telescopic component is an electromagnetic actuator.

9. An aircraft, characterized in that: The invention comprises the folding wing auxiliary device according to any one of claims 1 to 8.

10. The aircraft according to claim 9, characterized in that The folding wings of the aircraft are rotatably connected to both sides of the lower abdomen of the aircraft, and the folding wings are provided with elastic unfolding devices.

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