CN113086207B - Low-cost airborne hanging rack mechanism - Google Patents
Low-cost airborne hanging rack mechanism Download PDFInfo
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- CN113086207B CN113086207B CN202110365950.4A CN202110365950A CN113086207B CN 113086207 B CN113086207 B CN 113086207B CN 202110365950 A CN202110365950 A CN 202110365950A CN 113086207 B CN113086207 B CN 113086207B
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- safety
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- 230000000149 penetrating effect Effects 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/06—Rocket or torpedo launchers for rockets from aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/15—UAVs specially adapted for particular uses or applications for conventional or electronic warfare
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Emergency Lowering Means (AREA)
- Clamps And Clips (AREA)
Abstract
The invention discloses a low-cost airborne hanger mechanism, which comprises: a base; the embracing unit comprises a first embracing frame and a second embracing frame; the outer support is fixed on the outer side of the first holding frame; the safety plate is connected with the outer side support in an elastic and rotating mode through a fulcrum shaft of the safety plate; the safety component is arranged on the outer side of the first holding frame; one end of the binding belt is connected with the second holding frame; the other end of the binding belt is sleeved on the bottom hook part of the safety plate in a state that the missile is not released, so that the first holding frame and the second holding frame clamp the missile, and the safety part locks the flat plate part of the safety plate; the safety component unlocks the flat plate part of the safety plate in the state of releasing the missile, and the safety plate outwards rotates under the elastic force of the elastic rotating connection part of the safety plate so that the bottom hook part is completely separated from the other end of the binding belt. By adopting the scheme of the invention, the missile can be reliably clamped and released, and the cost is lower.
Description
Technical Field
The invention relates to the technical field of airborne auxiliary equipment, in particular to a missile hanger clamping mechanism for a low-cost unmanned aerial vehicle.
Background
The main task of the unmanned aerial vehicle is to provide short-distance air support for ground troops, and can also perform permanent monitoring and reconnaissance tasks in mountainous areas and dangerous areas. Unmanned aerial vehicles are increasingly widely used in local conflicts, and missile-borne unmanned aerial vehicles are weapons with high cost performance. In order to reduce the cost, except for an unmanned aerial vehicle, the guided missile is also a huge consumable, a traditional guided missile hanger is provided with a slide rail or a lifting lug, and the small guided missile is short and small in appearance, the support lug or the slide rail occupies a part of installation space of the guided missile after installation, the strength and other tactical indexes of the small guided missile are influenced, and the traditional guided missile hanger mechanism is relatively high in cost, so that a hanger releasing mechanism suitable for the small guided missile of a multi-rotor or fixed-wing unmanned aerial vehicle is necessary to be designed.
Disclosure of Invention
The invention aims to provide a low-cost airborne hanger mechanism which can reliably clamp and release missiles and has low cost.
The purpose of the invention is realized as follows: a low cost airborne pylon mechanism comprising:
a base suspended and fixedly connected to the lower side of the wing;
the embracing unit comprises a first embracing frame and a second embracing frame which are rotatably connected with the base, the first embracing frame and the second embracing frame are arranged in a relatively rotating mode, rotating shafts of the first embracing frame and the second embracing frame are positioned at the upper sides of the first embracing frame and the second embracing frame, opening and closing gears are coaxially arranged on the rotating shafts of the first embracing frame and the second embracing frame, and the opening and closing gears of the first embracing frame and the opening and closing gears of the second embracing frame are meshed with each other;
the outer support is fixed on the outer side of the first holding frame;
the safety plate is provided with a fulcrum shaft serving as a rotation central shaft of the safety plate, is elastically and rotatably connected with the outer support through the fulcrum shaft of the safety plate, and is divided into a flat plate part forming a main body part of the safety plate and a bottom hook part forming the bottom of the safety plate by taking the fulcrum shaft as a reference;
the safety component is arranged on the outer side of the first holding frame and used for locking and unlocking the flat plate part of the safety plate;
one end of the binding belt is connected with the second holding frame;
the other end of the binding belt is sleeved on the bottom hook part of the safety plate under the state that the missile is not released, so that the missile is clamped by the first holding frame and the second holding frame, and the safety part locks the flat plate part of the safety plate; and the safety component unlocks the flat plate part of the safety plate under the state of releasing the missile, and the safety plate outwards rotates under the elastic force of the elastic rotating connection part of the safety plate so as to enable the bottom hook part to be completely separated from the other end of the binding belt.
Furthermore, the number of the outer side supports is two, the safety plate is movably arranged between the two outer side supports, the fulcrum shaft is fixedly connected with the safety plate in a penetrating mode, and two shaft ends of the fulcrum shaft are respectively connected with the two outer side supports in an elastic rotating mode.
Further, the safety component includes:
the safety pin is movably connected with the outer support in a penetrating way, abuts against and locks the flat plate part of the safety plate in the state that the guided missile is not released, and is separated from the flat plate part of the safety plate in the state that the guided missile is released;
and the linear driving component drives the safety pin to axially extend and retract.
Furthermore, the first holding frame and the second holding frame are both designed to be V-shaped plate structures, the V-shaped groove of the first holding frame is opposite to the V-shaped groove of the second holding frame, and the missile is clamped by the V-shaped groove of the first holding frame and the V-shaped groove of the second holding frame in the state that the missile is not released.
Furthermore, the linear driving assembly of the safety component comprises a driving motor, a driving gear, a rack and a rack sliding supporting seat, the driving motor is controlled by an airborne control system and an electric control system of the missile, the driving motor and the rack sliding supporting seat are installed on the outer side of the first holding frame, the driving gear is sleeved on a main shaft of the driving motor, the tooth-shaped side of the rack is meshed with the driving gear, the tooth-free side of the rack is in sliding connection with the rack sliding supporting seat, one end of the safety pin is fixedly connected with the rack, and the length direction of the safety pin is parallel to the length direction of the rack.
Further, the driving motor is a worm gear speed reduction motor.
The invention has the beneficial effects that:
1. the missile can be reliably and safely released, in the state of releasing the missile, the drive motor is started through the airborne control system, the safety pin retracts through the transmission of the drive gear and the rack, so that the safety part is unlocked to the safety plate, the safety plate rotates outwards under the elastic force of elastic rotary connection of the safety plate, so that the bottom hook part is completely separated from the binding belt, the first holding frame and the second holding frame are in a movable state, the first holding frame and the second holding frame are propped open by the dead weight of the missile, the first holding frame and the second holding frame rotate outwards in opposite directions, and the missile enters an open state, so that the missile can be quickly and reliably released;
2. the missile can be reliably and safely clamped, the missile cannot be damaged, the binding belt is sleeved on the bottom hook part of the safety plate in a state that the missile is not released, the first holding frame and the second holding frame are in a static state, the first holding frame and the second holding frame are driven to stably clamp the missile, and the safety part can lock the safety plate, so that the first holding frame and the second holding frame can reliably and safely clamp the missile;
3. simple structure, easy to use, the lightweight design of being convenient for is with compatible small-size many rotors or fixed wing unmanned aerial vehicle.
Drawings
Fig. 1 is a perspective view of the present invention.
FIG. 2 is a state diagram of an unreleased missile.
FIG. 3 is a state diagram of the released missile.
Detailed Description
The invention will be further described with reference to the accompanying figures 1-3 and specific examples. The missile 14 referred to in this embodiment is a small missile, specifically mounted on a low cost drone.
As shown in fig. 1-3, a low cost airborne pylon mechanism for a low cost unmanned aerial vehicle, comprising:
a base 1 suspended and fixedly connected to the lower side of the wing;
the embracing unit comprises a first embracing frame 2 and a second embracing frame 3 which are rotatably connected with the base 1, the first embracing frame 2 and the second embracing frame 3 are arranged in a relatively rotating mode, rotating shafts of the first embracing frame 2 and the second embracing frame 3 are positioned at the upper sides, opening and closing gears 4 are coaxially arranged on the rotating shafts of the first embracing frame 2 and the second embracing frame 3, and the opening and closing gears 4 of the first embracing frame 2 and the opening and closing gears 4 of the second embracing frame 3 are meshed with each other, so that the first embracing frame 2 and the second embracing frame 3 can keep a synchronous state during rotation;
the outer support 8 is fixed on the outer side of the first holding frame 2;
a rotatable safety plate 6, the safety plate 6 having a fulcrum shaft 7 as a rotation center shaft thereof, the safety plate 6 being elastically and rotatably connected to an outer support 8 through the fulcrum shaft 7 thereof, the safety plate 6 being divided into a flat plate portion constituting a main body portion thereof with the fulcrum shaft 7 as a reference, and a bottom hook portion 6a constituting a bottom portion thereof;
the safety component is arranged on the outer side of the first holding frame 2 and used for locking and unlocking the flat plate part of the safety plate 6;
the binding belt 5 is elastic, and one end of the binding belt 5 is connected with the second holding frame 3.
The other end of the binding belt 5 is sleeved on a bottom hook part 6a of the safety plate 6 under the state that the guided missile 14 is not released, so that the guided missile 14 is clamped by the first holding frame 2 and the second holding frame 3, and the flat plate part of the safety plate 6 is locked by the safety part; the safety member unlocks the flat plate portion of the safety plate 6 in a state where the missile 14 is released, and the safety plate 6 is rotated outward by the elastic force of the elastic rotation joint thereof to completely separate the bottom hook portion 6a from the other end of the binding belt 5.
The first holding frame 2 and the second holding frame 3 are both designed to be V-shaped plate structures, the V-shaped groove of the first holding frame 2 is opposite to the V-shaped groove of the second holding frame 3, and the missile 14 is clamped by the V-shaped groove of the first holding frame 2 and the V-shaped groove of the second holding frame 3 under the state that the missile 14 is not released, so that a better clamping effect is formed on the missile 14.
The number of the outer side supports 8 is two, the safety plate 6 is movably arranged between the two outer side supports 8, the fulcrum shaft 7 is fixedly connected with the safety plate 6 in a penetrating mode, and two shaft ends of the fulcrum shaft 7 are respectively connected with the two outer side supports 8 in an elastic rotating mode.
The safety member includes:
the safety pin 12 is used for locking the safety plate 6, the safety pin 12 is movably connected with the outer support 8 in a penetrating mode, the safety pin 12 abuts against the outer side face of the flat plate part of the safety plate 6 in the state that the guided missile 14 is not released, so that the safety plate 6 is locked, and the safety pin 12 is separated from the flat plate part of the safety plate 6 in the state that the guided missile 14 is released, so that unlocking is achieved;
a linear drive assembly for actuating the arming pin 12 to axially extend and retract.
The linear driving assembly comprises a driving motor 9, a driving gear 10, a rack 11 and a rack sliding support seat 13, the driving motor 9 is controlled by an airborne control system and an electric control system of a missile 14, the driving motor 9 is a worm gear speed reduction motor, the driving motor 9 and the rack sliding support seat 13 are installed on the outer side of the first holding frame 2, the driving gear 10 is sleeved on a main shaft of the driving motor 9, the tooth-shaped side of the rack 11 is meshed with the driving gear 10, the tooth-free side of the rack 11 is connected with the rack sliding support seat 13 in a sliding mode, one end of a safety pin 12 is fixedly connected with the rack 11, and the length direction of the safety pin 12 is parallel to the length direction of the rack 11.
As shown in fig. 2, the binding belt 5 is sleeved on the bottom hook portion 6a of the safety plate 6 in a state that the missile 14 is not released, so that the first holding frame 2 and the second holding frame 3 are in a stationary state, and the first holding frame 2 and the second holding frame 3 are driven to stably clamp the missile 14, and since the safety pin 12 can lock the safety plate 6, the safety pin 12 abuts against the outer side surface of the flat plate portion of the safety plate 6, the safety plate 6 can be well locked, and the first holding frame 2 and the second holding frame 3 can reliably and safely clamp the missile 14.
As shown in fig. 3, which illustrates the principle of releasing the missile 14, after the drone or missile 14 receives the target lock signal, the mechanical separation signal of the unmanned aerial vehicle and the guided missile starts to be activated, the forward rotation delay circuit of the driving motor 9 operates, the safety pin 12 retracts through the transmission of the driving gear 10 and the rack 11, thereby unlocking the safety member from locking the safety plate 6, the safety plate 6 is rotated outward by the elastic force of its elastic rotation connection to completely disengage the bottom hook portion 6a from the binding belt 5, the first holding frame 2 and the second holding frame 3 are in a movable state, and then the first holding frame 2 and the second holding frame 3 are propped open by the dead weight of the missile 14, the first holding frame 2 and the second holding frame 3 are simultaneously rotated outwards in opposite directions through the mutual meshing action of the two opening and closing gears 4, so that the missile 14 can be released quickly and reliably.
While the preferred embodiments of the present invention have been described, those skilled in the art will appreciate that various changes and modifications can be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (6)
1. The utility model provides a low-cost machine carries stores pylon mechanism, includes and hangs, and fixed connection is in base (1) of wing downside, its characterized in that still includes:
the embracing unit comprises a first embracing frame (2) and a second embracing frame (3) which are rotatably connected with the base (1), wherein the first embracing frame (2) and the second embracing frame (3) are arranged in a relatively rotating mode, rotating shafts of the first embracing frame (2) and the second embracing frame (3) are positioned at the upper sides of the first embracing frame and the second embracing frame, opening and closing gears (4) are coaxially arranged on the rotating shafts of the first embracing frame (2) and the second embracing frame (3), and the opening and closing gears (4) of the first embracing frame (2) and the opening and closing gears (4) of the second embracing frame (3) are mutually meshed;
the outer support (8) is fixed on the outer side of the first holding frame (2);
the safety guard (6) is rotatable, the safety guard (6) is provided with a fulcrum shaft (7) serving as a rotation central shaft of the safety guard, the safety guard (6) is elastically and rotatably connected with an outer support (8) through the fulcrum shaft (7), and the safety guard (6) is divided into a flat plate part forming a main body part of the safety guard and a bottom hook part (6a) forming the bottom of the safety guard with the fulcrum shaft (7) as the standard;
the safety component is arranged on the outer side of the first holding frame (2) and used for locking and unlocking the flat plate part of the safety plate (6);
an elastic binding belt (5), wherein one end of the binding belt (5) is connected with the second holding frame (3);
the other end of the binding belt (5) is sleeved on a bottom hook part (6a) of the safety plate (6) under the state that the missile (14) is not released, so that the missile (14) is clamped by the first holding frame (2) and the second holding frame (3), and the safety part locks a flat plate part of the safety plate (6); the safety component unlocks the flat plate part of the safety plate (6) in the state of releasing the guided missile (14), and the safety plate (6) rotates outwards under the elastic force of the elastic rotating connection part of the safety plate so that the bottom hook part (6a) is completely separated from the other end of the binding belt (5).
2. The low-cost airborne hanging rack mechanism according to claim 1, characterized in that the number of the outer side supports (8) is two, the safety plate (6) is movably arranged between the two outer side supports (8), the fulcrum shaft (7) is fixedly connected with the safety plate (6) in a penetrating way, and two shaft ends of the fulcrum shaft (7) are respectively connected with the two outer side supports (8) in an elastic and rotating way.
3. A low cost on-board hanger mechanism according to claim 1, said safety component comprising:
the safety pin (12) is used for locking the safety plate (6), the safety pin (12) movably penetrates through the outer support (8), the safety pin (12) abuts against and locks the flat plate part of the safety plate (6) in the state that the guided missile (14) is not released, and the safety pin (12) is separated from the flat plate part of the safety plate (6) in the state that the guided missile (14) is released;
and the linear driving component drives the safety pin (12) to axially extend and retract.
4. A low-cost airborne hanging rack mechanism according to claim 1, characterized in that the first holding rack (2) and the second holding rack (3) are both designed as V-shaped plate structures, and the V-shaped groove of the first holding rack (2) is opposite to the V-shaped groove of the second holding rack (3), and the missile (14) is clamped by the V-shaped groove of the first holding rack (2) and the V-shaped groove of the second holding rack (3) in the state that the missile (14) is not released.
5. A low cost on-board pylon mechanism according to claim 3 wherein the linear drive assembly of the safety member comprises a drive motor (9), a drive gear (10), a rack (11) and a rack slide bearing (13), the driving motor (9) is controlled by an onboard control system and an electric control system of the missile (14), the driving motor (9) and the rack sliding supporting seat (13) are arranged on the outer side of the first holding frame (2), the driving gear (10) is sleeved on a main shaft of the driving motor (9), the tooth-shaped side of the rack (11) is meshed with the driving gear (10), the toothless side of the rack (11) is connected with a rack sliding supporting seat (13) in a sliding way, one end of the safety pin (12) is fixedly connected with the rack (11), and the length direction of the safety pin (12) is parallel to the length direction of the rack (11).
6. A low cost airborne pylon mechanism according to claim 5 wherein the drive motor (9) is configured as a worm gear reduction motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110365950.4A CN113086207B (en) | 2021-04-06 | 2021-04-06 | Low-cost airborne hanging rack mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110365950.4A CN113086207B (en) | 2021-04-06 | 2021-04-06 | Low-cost airborne hanging rack mechanism |
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| Publication Number | Publication Date |
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| CN113086207A CN113086207A (en) | 2021-07-09 |
| CN113086207B true CN113086207B (en) | 2022-05-10 |
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| CN202110365950.4A Active CN113086207B (en) | 2021-04-06 | 2021-04-06 | Low-cost airborne hanging rack mechanism |
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| CN113086207A (en) | 2021-07-09 |
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