1. A missile hoop release mechanism, comprising: the device comprises a base, a hoop component, a driving piece, a limiting component and a driving component;

the hoop component comprises a left hoop and a right hoop, and the left hoop and the right hoop are respectively hinged to two sides of the base through hinge components;

the driving piece is rotationally connected to the base;

the hoop component has a holding state and a releasing state:

when the hoop component is in a tightly holding state, two ends of the driving piece are respectively abutted against the left hoop and the right hoop and used for limiting the rotation of the left hoop and the right hoop so as to tightly hold the missile;

when the hoop component is in a release state, the driving piece is separated from the left hoop and the right hoop so as to release the missile;

the limiting assembly is arranged on the hoop assembly and used for limiting the driving piece when the limiting assembly is effective so that the hoop assembly is in a holding state;

the driving assembly is in transmission connection with the driving piece and used for driving the driving piece to rotate when the limiting assembly fails, and therefore the hoop assembly is in a release state.

2. The missile hoop release mechanism of claim 1, wherein the limiting assembly comprises an electromagnet, the electromagnet is fixedly connected to the hoop assembly or the base, and the driving member is connected to the electromagnet in an adsorbing manner.

3. The missile hoop release mechanism of claim 2, wherein the drive assembly comprises a first link, a second link, and a first spring;

the first connecting piece is fixedly connected to the base, the second connecting piece is fixedly connected to the driving piece, and the first spring is fixedly connected between the first connecting piece and the second connecting piece;

the first spring has pretightening force, so that the driving piece has a tendency of rotating towards the direction of the first connecting piece.

4. The missile hoop release mechanism of any one of claims 1 to 3, wherein a top plate is fixedly connected to the upper end of the base, and second springs are arranged between the top plate and the left and right hoops;

the second spring has a pretightening force, and when the hoop component is in a release state, the second spring drives the left hoop and the right hoop to rotate, so that the distance between the left hoop and the right hoop is maximum.

5. The missile hoop releasing mechanism of claim 4, wherein the left hoop and the right hoop are structurally identical and comprise a driving plate and a fastening plate, the driving plate is a straight plate, the fastening plate is an arc-shaped plate, the driving plate is fixedly connected to the upper end of the fastening plate, the driving part abuts against the driving plate, and the arc-shaped plate is used for clasping and releasing a missile.

6. An unmanned aerial vehicle comprising a fuselage, a wing and a missile hoop release mechanism as claimed in any one of claims 1 to 5, the missile hoop release mechanism being fixedly attached beneath the wing.

Background

At present, the fixed wing unmanned aerial vehicle has developed fairly maturity, has convenient to use, and the economic nature is higher, and the operation requirement is low grade characteristics for it is by a large amount of wide application. In practical application, a fixed wing unmanned aerial vehicle is often used as a platform for carrying a small missile, and missile throwing and releasing are carried out under the condition of a certain height and speed.

Most of the existing missiles are carried on airplanes, and the release devices of the existing missiles have the problems of complex structure, high manufacturing cost, high maintenance cost and the like.

Disclosure of Invention

The invention aims to: the utility model provides a small-size guided missile release mechanism based on unmanned aerial vehicle platform, has solved the problem that release mechanism structure is complicated.

The technical scheme adopted by the invention is as follows:

a missile hoop release mechanism comprising: the device comprises a base, a hoop component, a driving piece, a limiting component and a driving component;

the hoop component comprises a left hoop and a right hoop, and the left hoop and the right hoop are respectively hinged to two sides of the base through hinge components;

the driving piece is rotationally connected to the base;

the hoop component has a holding state and a releasing state:

when the hoop component is in a tightly holding state, two ends of the driving piece are respectively abutted against the left hoop and the right hoop and used for limiting the rotation of the left hoop and the right hoop so as to tightly hold the missile;

when the hoop component is in a release state, the driving piece is separated from the left hoop and the right hoop so as to release the missile;

the limiting assembly is arranged on the hoop assembly and used for limiting the driving piece when the limiting assembly is effective so that the hoop assembly is in a holding state;

the driving assembly is in transmission connection with the driving piece and used for driving the driving piece to rotate when the limiting assembly fails, and therefore the hoop assembly is in a release state.

Preferably, the limiting assembly comprises an electromagnet, the electromagnet is fixedly connected to the hoop assembly or the base, and the driving piece is connected with the electromagnet in an adsorption mode.

Preferably, the drive assembly comprises a first link, a second link and a first spring;

the first connecting piece is fixedly connected to the base, the second connecting piece is fixedly connected to the driving piece, and the first spring is fixedly connected between the first connecting piece and the second connecting piece;

the first spring has pretightening force, so that the driving piece has a tendency of rotating towards the direction of the first connecting piece.

Preferably, the upper end of the base is fixedly connected with a top plate, and second springs are arranged between the top plate and the left and right hoops;

the second spring has a pretightening force, and when the hoop component is in a release state, the second spring drives the left hoop and the right hoop to rotate, so that the distance between the left hoop and the right hoop is maximum.

Preferably, left staple bolt with and right staple bolt structure is unanimous, including drive plate and mounting plate, the drive plate is straight board, the mounting plate is the arc, drive plate fixed connection be in the mounting plate upper end, the driving piece with the drive plate supports and leans on, the arc is used for embracing tightly and releasing the guided missile.

An unmanned aerial vehicle comprises a body, wings and a missile hoop releasing mechanism, wherein the missile hoop releasing mechanism is fixedly connected below the wings.

In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:

when the limiting assembly is in a failure state, the driving assembly drives the driving piece to rotate, so that the driving piece relieves the limitation on the hoop assembly, and the hoop assembly rotates under the action of the gravity of the missile, so that the hoop assembly is in a release state, and the missile is released; when the limiting assembly is effective, the two ends of the driving piece are respectively abutted against the hoop assembly, so that the hoop assembly is in a tightly holding state. The device completes the release of the guided missile through a simple mechanical structure, and has the advantages of high reliability, low maintenance cost, convenience and simplicity in use and the like.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a first isometric view of the missile hoop release mechanism of the present invention;

FIG. 2 is a second isometric view of the missile hoop release mechanism of the present invention;

FIG. 3 is a schematic structural view of the missile hoop releasing mechanism of the present invention when a missile is clamped;

FIG. 4 is a schematic structural view of the missile hoop release mechanism of the present invention releasing a missile;

FIG. 5 is a schematic structural view of a base according to the present invention;

fig. 6 is a schematic structural diagram of the unmanned aerial vehicle of the present invention.

The labels in the figure are: 1-base, 101-lug boss, 2-hoop component, 201-left hoop, 202-right hoop, 3-missile, 4-base, 5-threaded rod, 6-driving piece, 7-strut, 8-top plate, 9-second spring, 10-connecting column, 11-first connecting piece, 12-second connecting piece, 13-first spring, 14-electromagnet seat, 15-power-off electromagnet, 16-fuselage and 17-wing.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.

In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

Example one

As shown in fig. 1 to 5, the missile hoop releasing mechanism disclosed in this embodiment includes: the device comprises a base 1, a hoop component 2, a driving component 6, a limiting component and a driving component; the hoop component 2 comprises a left hoop 201 and a right hoop 202, and the left hoop 201 and the right hoop 202 are respectively hinged to two sides of the base 1 through hinge components; the driving piece 6 is rotationally connected to the base 1; the hoop component 2 has a holding state and a releasing state: when the hoop component 2 is in a tightly-holding state, two ends of the driving element 6 respectively abut against the left hoop 201 and the right hoop 202, and the driving element is used for limiting the rotation of the left hoop 201 and the right hoop 202 to tightly hold the missile 3; when the hoop assembly 2 is in a release state, the driving piece 6 is separated from the left hoop 201 and the right hoop 202 to release the missile 3; the limiting assembly is arranged on the hoop assembly 2 and used for limiting the driving piece 6 to be fixed when the limiting assembly is effective, so that the hoop assembly 2 is in a holding state; the driving assembly is in transmission connection with the driving piece 6 and is used for driving the driving piece 6 to rotate when the limiting assembly fails, and therefore the hoop assembly 2 is in a release state.

In this embodiment, the hinge assembly includes two bases 4 fixedly connected to the hoop assembly 2, a protrusion 101 disposed on the base 1, and a threaded rod 5, the protrusion 101 is inserted between the two bases 4, then inserted into the base 4, the protrusion 101, and the other base 4 in sequence through a bolt rod, and finally screwed into a nut for fixing, and at this time, the hoop assembly 2 can rotate around the threaded rod 5 through the bases 4. Of course, other hinge assemblies can be adopted, as long as the hoop assembly 2 does not interfere with the base 1 when rotating.

In the present embodiment, a pillar 7 is fixedly connected to the base 1, the pillar 7 is disposed perpendicular to the base 1, the driving member 6 is rotatably connected to the pillar 7, the driving member 6 is rotatable around the pillar 7, and the pillar 7 is located at the center of the driving member 6.

In this embodiment, place guided missile 3 to between staple bolt subassembly 2 under staple bolt subassembly 2 is in the release state, then drive the staple bolt and rotate, make staple bolt subassembly 2 be in and hold the state tightly and hug guided missile 3, then drive driving piece 6 rotates, makes the both ends of driving piece 6 and staple bolt subassembly 2 counterbalance and lean on, the restriction staple bolt subassembly 2 rotates, then the rotation of driving piece 6 is restricted through spacing subassembly again, accomplishes guided missile 3's installation this moment. When the missile 3 needs to be released, the limiting assembly is firstly in an invalid state, then the driving assembly drives the driving piece 6 to rotate, so that the driving piece 6 relieves the limitation on the hoop assembly 2, and the hoop assembly 2 rotates under the action of the gravity of the missile 3 at the moment, so that the hoop assembly 2 is in a release state, and the missile 3 is released.

Preferably, the limiting assembly comprises an electromagnet, the electromagnet is fixedly connected to the hoop assembly 2 or the base 1, and the driving piece 6 is connected with the electromagnet in an adsorption mode.

In this embodiment, the electromagnet is fixedly connected to the hoop assembly 2 through the electromagnet seat 14.

In this embodiment, the electromagnet is a power-off electromagnet 15, and when the power-off electromagnet 15 is not powered on, the power-off electromagnet 15 has a function of magnetically attracting the driving member 6; when the power-loss electromagnet 15 is energized, the power-loss electromagnet 15 loses magnetism and stops adsorbing the driving member 6.

Preferably, the driving assembly comprises a first link 11, a second link 12 and a first spring 13; the first connecting piece 11 is fixedly connected to the base 1, the second connecting piece 12 is fixedly connected to the driving piece 6, and the first spring 13 is fixedly connected between the first connecting piece 11 and the second connecting piece 12; the first spring 13 has a pre-tightening force, so that the driving member 6 tends to rotate toward the first connecting member 11, and the pre-tightening force of the first spring 13 is smaller than the magnetic force of the power-off electromagnet 15.

In this embodiment, since the preload of the first spring 13 is smaller than the magnetic force of the power-off electromagnet 15, when the power-off electromagnet 15 attracts the driving member 6, the driving member 6 is not driven by the first spring 13. When the power-off type electromagnet 15 is powered on, the power-off type electromagnet 15 loses magnetic force, and at the moment, the first spring 13 drives the driving piece 6 to rotate.

In the present embodiment, the power-off electromagnet 15 and the first spring 13 are disposed on the same side of the driving member 6, and the power-off electromagnet 15 and the first spring 13 are respectively disposed at two ends of the pillar 7. The driving member 6 does not interfere with the deenergized electromagnet 15 when rotating.

In other embodiments, the power-off electromagnet 15 and the first spring 13 are respectively disposed on two sides of the driving member 6, and the power-off electromagnet 15 and the first spring 13 are respectively disposed on the same side of the pillar 7. With this arrangement, the driving member 6 also does not interfere with the deenergized electromagnet 15 when rotating.

Preferably, the upper end of the base 1 is fixedly connected with a top plate 8, and a second spring 9 is arranged between the top plate 8 and the left and right anchor ears 201 and 202; the second spring 9 has a pre-tightening force, and when the hoop assembly 2 is in a release state, the second spring 9 drives the left hoop 201 and the right hoop 202 to rotate, so that the distance between the left hoop 201 and the right hoop 202 is the largest.

In the present embodiment, the top plate 8 is fixedly connected to the base 1 through at least one connecting column 10, and it should be particularly noted that the pillar 7 may also be fixedly connected to the top plate 8 as one of the connecting columns 10, and the stability of the pillar 7 can be enhanced after the pillar 7 is fixedly connected to the top plate 8.

In this embodiment, when the hoop assembly 2 is released from the limit of the driving member 6, the hoop assembly 2 is opened by the elastic force of the second spring 9 to release the projectile 3. It should be particularly noted here that the second spring 9 only plays a role of assisting in opening the hoop assembly 2, and it is mentioned above that the missile 3 itself can also open the hoop assembly 2 by its own gravity, but when the second spring 9 assists in opening, the posture of the missile 3 when releasing can be ensured, and the energy loss caused when the missile 3 itself opens the hoop assembly 2 can be prevented from affecting the flying distance of the missile 3 after releasing.

Preferably, left staple bolt 201 with and right staple bolt 202 structure is unanimous, including drive plate and mounting plate, the drive plate is straight board, the mounting plate is the arc, drive plate fixed connection be in the mounting plate upper end, driving piece 6 with the drive plate supports and leans on, the arc is used for embracing tightly and releases guided missile 3.

Example two

Fig. 6 shows a unmanned aerial vehicle disclosed in this embodiment, which includes a fuselage 16, a wing 17, and a missile hoop releasing mechanism, where the missile hoop releasing mechanism is fixedly connected below the wing 17.

In the embodiment, the missile hoop release mechanism is fixedly connected with the wing 17 through the top plate 8.

The working principle is as follows:

step one, installing a missile 3: firstly, the power-off electromagnet 15 is electrified, the power-off electromagnet 15 loses magnetism, the driving piece 6 is driven to rotate through the first spring 13, after the hoop component 2 is separated from the limit of the driving piece 6, the hoop component 2 is driven to rotate and open through the second spring 9, then the missile 3 is put into the hoop component 2, the hoop component 2 is driven to rotate, the hoop component 2 is enabled to be in a tightly holding state to tightly hold the missile 3, meanwhile, the power-off electromagnet 15 is stopped to be electrified, the power-off electromagnet 15 exerts a suction force on the driving piece 6 to drive the driving piece 6 to rotate, when the driving piece 6 abuts against the power-off electromagnet 15, the two ends of the driving piece 6 abut against the hoop component 2, and the rotation of the hoop component 2 is limited. The entire release mechanism is then fixed to the wing 17 of the drone, although it is also possible to fix the entire release mechanism to the wing 17 and then install the missile 3.

And step two, releasing the missile 3: after installation guided missile 3, unmanned aerial vehicle takes off, calculate the required height and the speed of flying of unmanned aerial vehicle, after the position of arriving required release guided missile 3, with 15 circular telegrams of the type of losing electricity electro-magnet, 15 lose magnetism of losing the type of losing electricity electro-magnet, drive driving piece 6 through first spring 13 and rotate, staple bolt subassembly 2 has broken away from behind the restriction of driving piece 6, drive staple bolt subassembly 2 under the auxiliary action of second spring 9 and rotate and open, then release guided missile 3, guided missile 3 is the parabola and launches this moment.

The above description is only a preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.

In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.