Automatic vertical fin unfolding mechanism of patrolling device, patrolling device and patrolling device set
By combining the design of the vertical tail mounting base, torsion spring limiting shell, torsion spring and limiting mechanism, the problem of compact storage of the loitering munition's vertical tail before launch and smooth deployment after launch is solved, realizing the loitering munition's rapid response and high-reliability flight.
Patent Information
- Application Number
- CN202520535845.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-25
- Publication Date
- 2026-01-16
- Estimated Expiration
- 2035-03-25
AI Technical Summary
The existing loitering munitions' vertical tail deployment mechanism design is difficult to fit compactly into the fuselage before launch, and vibration and control problems are prone to occur during deployment, causing the loitering munitions to be unable to quickly enter flight mode after launch.
The design employs a combination of a vertical tail mounting base, a torsion spring limiting shell, a torsion spring, a vertical tail pivot, and a limiting mechanism. The vertical tail is automatically deployed by the rotational force of the torsion spring, and the rotation angle is limited by the limiting mechanism to ensure that the vertical tail can be deployed smoothly and accurately after launch.
It enables compact storage and transportation of the loitering rovers, and allows them to quickly enter flight mode after launch, improving the storage and operation efficiency of the loitering rovers, reducing operating costs, and ensuring flight flexibility and adaptability.
Smart Images
Figure CN223803839U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aerospace technology, specifically to an automatic deployment mechanism for the vertical tail of a loitering pod, a loitering pod, and a loitering pod kit. Background Technology
[0002] A loitering munition is a type of munition (or submunition) that utilizes existing weapons for deployment, enabling it to patrol the target area and perform single or multiple missions such as surveillance, reconnaissance, battle damage assessment, airborne radio relay, and target attack. It consists of a warhead, guidance system, propulsion system, control system (including wings), and stabilization system (including tail fins or parachute). Loitering munitions require good structural compactness for use within limited launch / deployment platforms. The design of the vertical tail deployment and folding mechanism must ensure that the wings and vertical tail can be compactly housed within the fuselage before launch to reduce size and weight. The vertical tail deployment and folding mechanism needs to complete the deployment of the wings and vertical tail in a short time to ensure the loitering munition can quickly enter flight after launch. This requires the mechanism design to be characterized by rapid response and high reliability. During deployment, the mechanism must ensure that the wings and vertical tail deploy smoothly and accurately, avoiding vibration and control problems.
[0003] In summary, there is an urgent need to design an automatic deployment mechanism for the vertical tail of a loitering pod, as well as the loitering pod itself and a loitering pod kit, to overcome the aforementioned technical problems. Utility Model Content
[0004] The purpose of this invention is to provide an automatic deployment mechanism for the vertical tail of a loitering pod, the loitering pod itself, and a loitering pod kit, which features rapid response and high reliability.
[0005] To achieve the above objectives, the technical solution adopted by this utility model is: an automatic deployment mechanism for the vertical tail of a loitering glider, comprising:
[0006] Vertical tail mounting base, torsion spring limiting shell, torsion spring, vertical tail pivot, vertical tail and limiting mechanism;
[0007] The vertical tail mounting base is fixedly installed on the side wall of the fuselage;
[0008] The torsion spring limiting shell is fixedly installed on the surface of the tail mounting base, and a torsion spring is provided inside it;
[0009] The vertical tail pivot is inserted into and rotatably connected to the center of the vertical tail mounting base and the torsion spring limiting shell. The torsion spring is sleeved on the outer wall of the vertical tail pivot and its two ends are fixedly connected to the torsion spring limiting shell and the vertical tail pivot respectively. The end of the vertical tail pivot exposed outside the fuselage is fixedly connected to the vertical tail. The torsion spring has a rotational force that causes the vertical tail to unfold.
[0010] The limiting mechanism is used to limit the rotation angle of the vertical tail shaft.
[0011] The purposes and technical problems of the utility model can also be further realized by the following technical measures.
[0012] Optionally, the limiting mechanism comprises a limiting sheet installed on the vertical tail rotating shaft and a limiting pin fixed on the torsional spring limiting shell, and the limiting sheet and the limiting pin abut when the vertical tail is unfolded to a position.
[0013] Optionally, the vertical tail mounting seat is installed on the inner side of the fuselage side wall, the torsional spring limiting shell is installed on the side of the vertical tail mounting seat away from the fuselage side wall, and the vertical tail rotating shaft penetrates through the fuselage side wall, the vertical tail mounting seat and the torsional spring limiting shell.
[0014] The limiting sheet is fixedly installed on the end of the vertical tail rotating shaft away from the vertical tail, and the limiting pin is installed on the end of the torsional spring limiting shell away from the vertical tail.
[0015] Optionally, the limiting sheet comprises a round sheet fixedly connected with the end of the vertical tail rotating shaft and a blocking pin integrally connected with the outer edge of one side of the round sheet.
[0016] Optionally, the torsional spring limiting shell and the vertical tail mounting seat are respectively provided with a first through hole and a second through hole for inserting the vertical tail rotating shaft in the middle, and the outer diameter of the round sheet is greater than the inner diameter of the first through hole.
[0017] Optionally, the limiting mechanism further comprises a limiting wire, the limiting wire is arranged at the wing tip of the vertical tail, the limiting wire extends towards one side of the fuselage, and the limiting wire is arranged on the upper surface of the fuselage when the vertical tail is folded to the side of the fuselage.
[0018] A kind of flying vehicle, comprising the fuselage, wing and the flying vehicle vertical tail automatic unfolding mechanism of the flying vehicle;
[0019] The wing is arranged on the two sides of the fuselage, and the flying vehicle vertical tail automatic unfolding mechanism is arranged on the two sides of the tail of the fuselage.
[0020] A kind of flying vehicle set, comprising the flying vehicle and the transport cabin for accommodating the flying vehicle;
[0021] When the flying vehicle is accommodated in the transport cabin, the vertical tail of the flying vehicle is folded on the two sides of the fuselage of the flying vehicle.
[0022] When the flying vehicle leaves the transport cabin, the vertical tail is automatically unfolded.
[0023] Compared with the prior art, the utility model has the advantages that:
[0024] 1. The vertical tail automatic unfolding mechanism of the flying device, which is characterized in that: the vertical tail mounting seat connected with the fuselage is arranged, the torsional spring limiting shell is arranged on one side of the vertical tail mounting seat, the torsional spring is arranged in the torsional spring limiting shell, the vertical tail rotating shaft is rotationally connected between the vertical tail mounting seat and the torsional spring limiting shell, and the vertical tail is fixedly arranged at the outer end of the vertical tail rotating shaft; the vertical tail can be rotated to the side wall of the fuselage through the rotation of the vertical tail rotating shaft, so that the size of the flying device is reduced, the flying device is conveniently stored in the transport cabin, and the space occupied during transportation and parking is reduced; further, the limiting mechanism is arranged, the rotating angle of the vertical tail rotating shaft is limited, the flying device folded and stored in the transport cabin can be unfolded automatically under the action of the torsional spring accumulated during folding at the moment of being launched, and the vertical state with the fuselage is maintained, so that the flying device can fly stably.
[0025] 2. The vertical tail automatic unfolding mechanism of the flying device, which is characterized in that: the limiting wire is arranged on the upper end of the tail of the vertical tail; when the vertical tail is completely rotated to one side of the fuselage, the limiting wire is just arranged on the upper surface of the fuselage, so that the vertical tail is prevented from rotating downward excessively, the vertical tail can be folded on the side wall of the fuselage, and the limiting effect of the limiting sheet and the limiting pin is combined, so that the vertical tail can only rotate within a certain angle, and the storage, folding and automatic unfolding after launching of the vertical tail are facilitated. BRIEF DESCRIPTION OF DRAWINGS
[0026] Figure 1 is a sectional structure schematic view of the vertical tail automatic unfolding mechanism of the flying device provided by the utility model;
[0027] Figure 2 is a top view structure schematic view of the vertical tail automatic unfolding mechanism of the flying device provided by the utility model;
[0028] Figure 3 is an overall structure schematic view of the vertical tail automatic unfolding mechanism and the vertical tail provided by the utility model;
[0029] Figure 4 is a local top view of the vertical tail and the fuselage in the embodiment of the utility model;
[0030] Figure 5 is a local structure schematic view of the limiting wire arranged on the surface of the fuselage in the embodiment of the utility model;
[0031] Figure 6 is an overall structure schematic view of the vertical tail in the folded state in the embodiment of the utility model;
[0032] Figure 7 is the whole structure schematic diagram of the vertical tail unfolded state in the embodiment of the utility model;
[0033] Mark explanation:
[0034] 1, limit piece; 11, round piece; 12, stop pin;
[0035] 2, torsion spring;
[0036] 3, torsion spring limit shell; 31, first through hole;
[0037] 4, vertical tail mounting seat; 41, second through hole;
[0038] 5, vertical tail rotating shaft;
[0039] 6, vertical tail;
[0040] 7, limit pin;
[0041] 8, limit wire;
[0042] 9, fuselage; 91, fuselage side wall. DETAILED DESCRIPTION
[0043] In order to make the purpose, technical scheme and advantage of the utility model more clearly, the following will be further described in detail by combining with the drawings and examples. It should be understood that the specific examples described here are only used to explain the utility model, and are not used to limit the utility model.
[0044] As shown in Figures 1 to 7 A vertical tail automatic unfolding mechanism of a flying vehicle, comprising:
[0045] Vertical tail mounting seat 4, torsion spring limit shell 3, torsion spring 2, vertical tail rotating shaft 5, vertical tail 6 and limit mechanism;
[0046] The vertical tail mounting seat 4 is fixedly installed on the side wall of the fuselage 9;
[0047] The torsion spring limit shell 3 is fixedly installed on the surface of the vertical tail mounting seat 4, and the inside is provided with the torsion spring 2;
[0048] The vertical tail rotating shaft 5 is inserted and rotationally connected at the center of the vertical tail mounting seat 4 and the torsion spring limit shell 3, the torsion spring 2 is sleeved on the outer wall of the vertical tail rotating shaft 5 and the two ends thereof are fixedly connected with the torsion spring limit shell 3 and the vertical tail rotating shaft 5 respectively, one end of the vertical tail rotating shaft 5 exposed outside the fuselage 9 is fixedly connected with the vertical tail 6, and the torsion spring 2 has a rotating force for unfolding the vertical tail 6;
[0049] The limit mechanism is used for limiting the rotation angle of the vertical tail rotating shaft 5.
[0050] In the utility model, the vertical tail 6 is rotated to the side wall of the fuselage through the rotation of the vertical tail rotating shaft 5, so that the size of the flying vehicle is reduced, the flying vehicle is conveniently stored in the transport cabin, and the space occupied during transportation and parking is reduced; through the setting of the limiting mechanism, the rotation angle of the vertical tail rotating shaft 5 can be limited, so that the flying vehicle (flying bomb) stored in the transport cabin in a folded state is automatically unfolded under the action of the torsional spring 2 which has stored energy during folding in the instant after being launched, and the vertical tail maintains a vertical state with the fuselage, so that the flying vehicle can fly stably. The connection between the vertical tail mounting seat 4 and the fuselage 9, the connection between the torsional spring limiting shell 3 and the vertical tail mounting seat 4 and the connection between the vertical tail 6 and the vertical tail rotating shaft 5 in the mechanism can be installed and connected in a screw fixing mode.
[0051] Optionally, the limiting mechanism comprises a limiting piece 1 installed on the vertical tail rotating shaft 5 and a limiting pin 7 fixed on the torsional spring limiting shell 3, when the vertical tail 6 is unfolded to the position, the limiting piece 1 abuts against the limiting pin 7, so as to ensure the accuracy of the unfolded position of the vertical tail. The limiting piece 1 can be fixed and installed on the end of the vertical tail rotating shaft 5 through a screw, when the limiting piece 1 rotates along with the vertical tail rotating shaft 5, the torsional spring limiting shell 3 and the limiting pin 7 do not rotate, when the vertical tail 6 is automatically unfolded under the action of the torsional spring 2, the limiting piece 1 is just blocked by the limiting pin 7 and does not rotate any more, so as to limit the continuous rotation of the vertical tail 6 and ensure that the vertical tail 6 can be unfolded stably and accurately.
[0052] Optionally, the vertical tail mounting seat 4 is installed on the inner side of the side wall of the fuselage 9, the torsional spring limiting shell 3 is installed on the side of the vertical tail mounting seat 4 away from the side wall of the fuselage 9, and the vertical tail rotating shaft 5 penetrates the side wall of the fuselage 9, the vertical tail mounting seat 4 and the torsional spring limiting shell 3. Figure 1 As shown in FIG. 1, 91 represents the side wall of the fuselage 9, the upper side of the side wall 91 in the drawing is the inner side of the fuselage, and the lower side of the side wall 91 in the drawing is the outer side of the fuselage, wherein the vertical tail mounting seat 4 is installed on the inner side of the fuselage 9, that is, the upper side of the side wall 91 of the fuselage shown in FIG. 1. Figure 1 As shown in FIG. 1, 91 represents the side wall of the fuselage 9, the upper side of the side wall 91 in the drawing is the inner side of the fuselage, and the lower side of the side wall 91 in the drawing is the outer side of the fuselage, wherein the vertical tail mounting seat 4 is installed on the inner side of the fuselage 9, that is, the upper side of the side wall 91 of the fuselage shown in FIG. 1.
[0053] The limiting piece 1 is fixedly installed on the end of the vertical tail rotating shaft 5 away from the vertical tail 6, and the limiting pin 7 is installed on the end of the torsional spring limiting shell 3 away from the vertical tail 6. Installing the torsional spring limiting shell 3 and the limiting piece 1 in the side wall of the fuselage 9 can reduce the distance between the vertical tail 6 and the fuselage 9, so that the vertical tail 6 can be unfolded more stably.
[0054] Optionally, the limiting sheet 1 comprises a round sheet 11 fixedly connected with the end of the vertical tail rotating shaft 5 and a blocking pin 12 integrally connected with the outer edge of one side of the round sheet 11, the round sheet 11 can rotate with the vertical tail rotating shaft 5, the protruding blocking pin 12 is blocked by the limiting pin 7 after rotating by a certain angle, and no longer rotates, thereby limiting the rotating angle of the vertical tail rotating shaft 5 and the vertical tail 6.
[0055] Optionally, the torsional spring limiting shell 3 and the vertical tail mounting seat 4 are respectively provided with a first through hole 31 and a second through hole 41 for inserting the vertical tail rotating shaft 5, and the outer diameter of the round sheet 11 is greater than the inner diameter of the first through hole 31, so that the round sheet 11 can limit the movement of the vertical tail rotating shaft 5 in the length direction, and the rotating connection of the vertical tail rotating shaft 5 with the torsional spring limiting shell 3 and the vertical tail mounting seat 4 is more stable.
[0056] Optionally, the limiting mechanism further comprises a limiting wire 8 arranged at the wing tip of the vertical tail 6, the limiting wire 8 extends towards one side of the fuselage 9, and the limiting wire 8 is arranged on the upper surface of the fuselage 9 when the vertical tail 6 is folded to the side of the fuselage 9. When the vertical tail 6 is completely rotated to the side of the fuselage 9, the limiting wire 8 is just arranged on the upper surface of the fuselage 9, so that the vertical tail 6 is prevented from rotating downward excessively, the vertical tail 6 can be just folded on the side wall of the fuselage 9, and the limiting wire 8 is matched with the limiting effect of the limiting sheet 1 and the limiting pin 7, so that the vertical tail 6 can only rotate within a certain angle, the vertical tail 6 is convenient to store, fold and automatically expand after being launched. The limiting wire 8 is used for ensuring that the vertical tail 6 is folded in place, and preventing the vertical tail 6 from being excessively folded and damaging the internal parts of the vertical tail automatic expansion mechanism.
[0057] An embodiment of the utility model further provides a kind of flying vehicle, including the fuselage 9, wing and the flying vehicle vertical tail automatic expansion mechanism described above;
[0058] The wing is arranged on the two sides of the fuselage, and the flying vehicle vertical tail automatic expansion mechanism is arranged on the two sides of the tail of the fuselage.
[0059] Another embodiment of the utility model further provides a kind of flying vehicle set, including the flying vehicle described above and the transport cabin for storing the flying vehicle;
[0060] When the flying vehicle is stored in the transport cabin, the vertical tail 6 of the flying vehicle is folded on the two sides of the fuselage of the flying vehicle.
[0061] When the flying vehicle leaves the transport cabin, the vertical tail 6 is automatically expanded.
[0062] The above describes the utility model in combination with embodiments, but the utility model is not limited to the above-mentioned embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the purpose of the utility model.
Claims
1. A vertical tail automatic deployment mechanism for a flying wing aircraft, comprising: The utility model relates to a vertical tail automatic unfolding mechanism of a loitering munition, which comprises a vertical tail mounting seat (4), a torsion spring limiting shell (3), a torsion spring (2), a vertical tail rotating shaft (5), a vertical tail (6) and a limiting mechanism. The vertical tail mounting seat (4) is fixedly installed on the side wall of the fuselage (9). The torsion spring limiting shell (3) is fixedly installed on the surface of the vertical tail mounting seat (4), and the torsion spring (2) is arranged in the torsion spring limiting shell (3). The vertical tail rotating shaft (5) is inserted and rotatably connected to the center of the vertical tail mounting seat (4) and the torsion spring limiting shell (3), the torsion spring (2) is sleeved on the outer wall of the vertical tail rotating shaft (5), and the two ends of the torsion spring (2) are fixedly connected to the torsion spring limiting shell (3) and the vertical tail rotating shaft (5) respectively, one end of the vertical tail rotating shaft (5) exposed outside the fuselage (9) is fixedly connected to the vertical tail (6), and the torsion spring (2) has a rotating force for unfolding the vertical tail (6). The limiting mechanism is used for limiting the rotating angle of the vertical tail rotating shaft (5). The limiting mechanism comprises a limiting piece (1) installed on the vertical tail rotating shaft (5) and a limiting pin (7) fixedly installed on the torsion spring limiting shell (3), and the limiting piece (1) abuts against the limiting pin (7) when the vertical tail (6) is unfolded to the position.
2. The vertical tail automatic deployment mechanism of the flying-vehicle according to claim 1, wherein, The vertical tail mounting seat (4) is installed on the inner side of the side wall of the fuselage (9), the torsion spring limiting shell (3) is installed on the side of the vertical tail mounting seat (4) away from the side wall of the fuselage (9), and the vertical tail rotating shaft (5) penetrates the side wall of the fuselage (9), the vertical tail mounting seat (4) and the torsion spring limiting shell (3).
3. The vertical tail automatic deployment mechanism of the flying-vehicle according to claim 2, wherein, The limiting piece (1) is fixedly installed on the end of the vertical tail rotating shaft (5) away from the vertical tail (6), and the limiting pin (7) is installed on the end of the torsion spring limiting shell (3) away from the vertical tail (6). The limiting piece (1) comprises a round piece (11) fixedly connected to the end of the vertical tail rotating shaft (5) and a blocking pin (12) integrally connected to the outer edge of one side of the round piece (11).
4. The vertical tail automatic deployment mechanism of the flying-vehicle according to claim 2, wherein, The torsion spring limiting shell (3) and the vertical tail mounting seat (4) are respectively provided with a first through hole (31) and a second through hole (41) for inserting the vertical tail rotating shaft (5), and the outer diameter of the round piece (11) is greater than the inner diameter of the first through hole (31).
5. The vertical tail automatic deployment mechanism of the flying-vehicle according to claim 4, wherein, The limiting mechanism further comprises a limiting wire (8), the limiting wire (8) is arranged at the wing tip of the vertical tail (6), the limiting wire (8) extends towards one side of the fuselage (9), and the limiting wire (8) is arranged on the upper surface of the fuselage (9) when the vertical tail (6) is folded to the side of the fuselage (9).
6. The vertical tail automatic deployment mechanism of any one of claims 1-5, wherein, The utility model relates to a loitering munition and a transport cabin for accommodating the loitering munition.
7. A loitering munition characterized in that: When the loitering munition is accommodated in the transport cabin, the vertical tail (6) of the loitering munition is folded on the two sides of the fuselage of the loitering munition. When the loitering munition leaves the transport cabin, the vertical tail (6) is automatically unfolded.
8. A flitter kit, characterized by: